[ { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/ytzcd-nm557", "eprint_id": 62399, "eprint_status": "archive", "datestamp": "2023-08-19 04:44:55", "lastmod": "2023-10-25 17:07:40", "type": "teaching_resource", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "F. E." } } ] }, "title": "Spacecraft Propulsion", "ispublished": "unpub", "full_text_status": "public", "note": "Space Technology Summer Institute. ST-3 (NsG-598). \n\nA program sponsored by the National Aeronautics and Space Administration under Grant No. NsG-598 and given by the California Institute of Technology in cooperation with the Jet Propulsion Laboratory.\n\n
Submitted - ST-3.pdf
", "abstract": "[no abstract]", "date": "2015-11-24", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151124-152119107", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151124-152119107", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "NASA", "grant_number": "NsG-598" } ] }, "collection": "CaltechAUTHORS", "primary_object": { "basename": "ST-3.pdf", "url": "https://authors.library.caltech.edu/records/ytzcd-nm557/files/ST-3.pdf" }, "resource_type": "teaching_resource", "pub_year": "2015", "author_list": "Marble, F. E." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/hbw48-1ky59", "eprint_id": 62066, "eprint_status": "archive", "datestamp": "2023-08-22 01:23:07", "lastmod": "2023-10-25 16:49:32", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } } ] }, "title": "Non-Uniform Flow in Multistage Axial Compressors", "ispublished": "unpub", "full_text_status": "public", "keywords": "Compressor; Stall; Inlet Distortion", "note": "Final Report Grant No. AFOSR-75-2819. Air Force Office of Scientific Research Air Force Systems Command. USAF.\n\nSubmitted - Non-Uniform_Flow_in_MultistageAxial_Compressors.pdf
", "abstract": "It has been suggested by the author that some aspects of\nseverely distorted flow into multistage compressors may be examined utilizing an integral technique. The general idea of the proposed technique is clear enough; the appropriate equations of motion and energy are integrated peripherally and radially, using reasonable assumptions for the distributions of velocity and thermodynamic\nproperties, and thereby reduced to ordinary non-linear differential equations for the parameters that describe the distributions. The questions that arise are whether the cascade characteristics may be described appropriately over wide variations of inlet angle, including stall, and whether the profiles may be characterized by a\nsufficiently small number of parameters to make the technique attractive.\n\nThe present paper examines a specific example of distorted\ninlet flow through the two-dimensional annulus of a multistage compressor which can be solved completely. It is shown that the essential features of this exact solution, including stall, may be described by a two-parameter family of profiles and that an integral technique,\nutilizing these elementary profiles, will yield essentially the same results. While it is not clear that comparable success would hold for the three-dimensional problem, the results confirm the contention that the two-dimensional problem may be treated with acceptable\naccuracy by an integral technique.", "date": "2015-11-18", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151111-165514089", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151111-165514089", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "Air Force Office of Scientific Research (AFOSR)", "grant_number": "AFOSR-75-2819" } ] }, "primary_object": { "basename": "Non-Uniform_Flow_in_MultistageAxial_Compressors.pdf", "url": "https://authors.library.caltech.edu/records/hbw48-1ky59/files/Non-Uniform_Flow_in_MultistageAxial_Compressors.pdf" }, "resource_type": "monograph", "pub_year": "2015", "author_list": "Marble, Frank E." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/j3e5y-9rj36", "eprint_id": 51800, "eprint_status": "archive", "datestamp": "2023-08-19 17:25:58", "lastmod": "2023-10-18 17:10:46", "type": "book_section", "metadata_visibility": "show", "creators": { "items": [ { "id": "Culick-F-E-C", "name": { "family": "Culick", "given": "F. E. C." } }, { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } }, { "id": "Zukoski-E-E", "name": { "family": "Zukoski", "given": "E. E." } } ] }, "title": "Research on Mechanisms of Exciting Pressure Oscillations in Ramjet Engines", "ispublished": "unpub", "full_text_status": "public", "note": "AFOSR Grant Number: AFOSR-84-0286", "abstract": "An analytical and experimental study is being made of the role of combustion in large vortical structures in the mechanism of unsteady and unstable burning in air-breathing engines. A large body of experimental evidence supports the contention that these periodic fluctuations are themselves generated by the nonsteady flow over the flame holders and other surfaces. The mechanism itself is relatively independent of the acoustic configuration of the\npowerplant and its installation and hence constitutes the\nfundamental element of the combustion instability process. Whether or not the mechanism is excited does, however, depend upon the detailed acoustic properties of the combustion chamber and its environment and in many circumstances it is apparent that non-linear\nacoustics plays an essential role. As a consequence, the program includes detailed analytical studies of linear and non-linear acoustics in combustion configurations as a means of coupling the instability mechanism to a particular environment. The effective separation of the instability process into i) its mechanism and ii)\nits environment is aimed at eventually providing means of rational scaling of laboratory size experiments.", "date": "2014-11-15", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20141114-143821228", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20141114-143821228", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "Air Force of Scientific Research (AFOSR)", "grant_number": "AFOSR-84-0286" } ] }, "local_group": { "items": [ { "id": "GALCIT" } ] }, "primary_object": { "basename": "culick.pdf", "url": "https://authors.library.caltech.edu/records/j3e5y-9rj36/files/culick.pdf" }, "resource_type": "book_section", "pub_year": "2014", "author_list": "Culick, F. E. C.; Marble, Frank E.; et el." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/6gmq7-q4c82", "eprint_id": 22011, "eprint_status": "archive", "datestamp": "2023-08-20 05:53:12", "lastmod": "2023-10-23 15:36:24", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Budzinski-J-M", "name": { "family": "Budzinski", "given": "J. M." } }, { "id": "Marble-F-E", "name": { "family": "Marble", "given": "F. E." } }, { "id": "Zukoski-E-E", "name": { "family": "Zukoski", "given": "E. E." } } ] }, "title": "An experimental study of the flow after shock interactions with cylindrical helium inhomegeneities", "ispublished": "unpub", "full_text_status": "public", "note": "\u00a9 1995, Los Alamos Laboratory.\n\nAccepted Version - 375_Budzinski_JM.pdf
", "abstract": "A shock traveling in air interacts with a laminar jet of\nhelium flowing normal to the direction of shock\npropagation. Planar laser Rayleigh scattering is used\nto study the deformation and motion of the originally\ncircular jet cross-section. The velocity of the jet\nbefore the shock interaction is much less than the\nvelocities generated by the shock wave. Thus, the\nhelium jet serves to create a cylindrical bubble of a\nlighter density gas imbedded in a heavier one. Four\ndifferent shock Mach numbers (1.066, 1.14, 1.5, and\n2.0) are studied. Two different jet/air density ratios\nare examined by using pure helium in the jet in one\ncase, and a mixture of airlhelium in the other. After\nthe shock interaction, a vortex pair forms from the baroclinically generated vorticity. The experiments\nmeasure the velocity of the helium relative to the\nsurrounding air, the spacing between the vortex\ncores, and the circulation of the vortices.\nExperiments viewing the reflected shock interaction\nare also performed. Excellent agreement is found\nwith previous computational studies.", "date": "1995-05-12", "date_type": "published", "publisher": "Los Alamos National Laboratory", "id_number": "CaltechAUTHORS:20110204-100414048", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20110204-100414048", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "other_numbering_system": { "items": [ { "id": "LA-UR-95-317", "name": "Los Alamos" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "primary_object": { "basename": "375_Budzinski_JM.pdf", "url": "https://authors.library.caltech.edu/records/6gmq7-q4c82/files/375_Budzinski_JM.pdf" }, "resource_type": "monograph", "pub_year": "1995", "author_list": "Budzinski, J. M.; Marble, F. E.; et el." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/fq7kp-sgw33", "eprint_id": 21003, "eprint_status": "archive", "datestamp": "2023-08-20 04:06:30", "lastmod": "2023-10-20 23:40:09", "type": "article", "metadata_visibility": "show", "creators": { "items": [ { "id": "Ton-V-T", "name": { "family": "Ton", "given": "V. T." } }, { "id": "Karagozian-Ann-R", "name": { "family": "Karagozian", "given": "A. R." } }, { "id": "Marble-F-E", "name": { "family": "Marble", "given": "F. E." } }, { "id": "Osher-Stanley-J", "name": { "family": "Osher", "given": "S. J." } }, { "id": "Engquist-B-E", "name": { "family": "Engquist", "given": "B. E." } } ] }, "title": "Numerical Simulations of High-Speed Chemically Reacting Flow", "ispublished": "pub", "full_text_status": "restricted", "note": "\u00a9 1994 Springer-Verlag. \n\nReceived 12 March 1993 and accepted 10 September 1993. \n\nCommunicated by Ashwani Kapila. \n\nThis work has been supported by the Aerospace Corporation through a Corporate Fellowship, by NASA Dryden Flight Research Center under Grant NCC 2-374, by ONR Grant N00014-86-K-0691, by NSF Grant DMS 88-11863, and by a DARPA Grant in the ACMP Program.", "abstract": "The essentially nonoscillatory (ENO) shock-capturing scheme for the solution of hyperbolic\nequations is extended to solve a system of coupled conservation equations governing\ntwo-dimensional, time-dependent, compressible chemically reacing flow with full chemistry. The\nthermodynamic properties of the mixture are modeled accurately, and stiff kinetic terms are\nseparated from the fluid motion by a fractional step algorithm. The methodology is used to study\nthe concept of shock-induced mixing and combustion, a process by which the interaction of a\nshock wave with a jet of low-density hydrogen fuel enhances mixing through streamwise vorticity\ngeneration. Test cases with and without chemical reaction are explored here. Our results indicate\nthat, in the temperature range examined, vorticity generation as well as the distribution of atomic\nspecies do not change significantly with the introduction of a chemical reaction and subsequent\nheat release. The actual diffusion of hydrogen is also relatively unaffected by the reaction process.\nThis suggests that the fluid mechanics of this problem may be successfully decoupled from the\ncombustion processes, and that computation of the mixing problem (without combustion chemistry)\ncan elucidate much of the important physical features of the flow.", "date": "1994-04", "date_type": "published", "publication": "Theoretical and Computational Fluid Dynamics", "volume": "6", "number": "2-3", "publisher": "Springer", "pagerange": "161-179", "id_number": "CaltechAUTHORS:20101123-142807198", "issn": "0935-4964", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20101123-142807198", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "Aerospace Corporation" }, { "agency": "NASA", "grant_number": "NCC 2-374" }, { "agency": "Office of Naval Research (ONR)", "grant_number": "N00014-86-K-0691" }, { "agency": "NSF", "grant_number": "DMS 88-11863" }, { "agency": "Defense Advanced Research Projects Agency (DARPA)" } ] }, "other_numbering_system": { "items": [ { "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "doi": "10.1007/BF00312347", "resource_type": "article", "pub_year": "1994", "author_list": "Ton, V. T.; Karagozian, A. R.; et el." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/en7k6-b5996", "eprint_id": 21006, "eprint_status": "archive", "datestamp": "2023-08-20 03:29:38", "lastmod": "2023-10-20 23:40:26", "type": "article", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } } ] }, "title": "Gasdynamic enhancement of nonpremixed combustion", "ispublished": "pub", "full_text_status": "restricted", "note": "\u00a9 1994 Combustion Institute Published by Elsevier B.V. Publication History: Formerly known as Symposium on Combustion and Flame, and Explosion Phenomena; Continued as Proceedings of the Combustion Institute.", "abstract": "To promote efficient performance of very high speed air-breathing propulsion systems, the combustor Mach number must be of the order of six for a flight Mach number of 18. Because of this high gas speed through the combustor, mixing rates of hydrogen fuel with air must be very rapid in order to allow a combustor of reasonable length. It is proposed to enhance the rate of mixing and combustion of hydrogen and air, and thereby reduce combustor length, through the introduction of streamwise vorticity generated by the interaction of a weak oblique shock wave with the density gradient between air and a cylindrical jet of hydrogen.\n\nBecause of the high Mach number flow in the combustor, the oblique shock traverses the jet at a small angle with respect to the free stream direction, and the principle of slender body theory allows one conceptually to replace the three-dimensional steady flow with a two-dimensional unsteady flow. As a consequence, two-dimensional time-dependent computational studies and an extensive experimental shock tube investigation were employed to assess mixing rates for the steady flow in the combustor. The results indicated that under realistic conditions, adequate mixing could be accomplished within 1 ms, a rate that was technologically interesting.\n\nEncouraged by these experiments, a \"practical\" injector, utilizing shock-enhanced mixing, was designed for a combustor having a free stream Mach number of 6.0. A detailed aerodynamic and mixing investigation was carried out in the Mach 6 High Reynolds Number Tunnel at the NASA-Langley Research Center. The results confirmed both the details and the overall effectiveness of the shock-enhanced mixing concept.", "date": "1994", "date_type": "published", "publication": "Symposium (International) on Combustion", "volume": "25", "number": "1", "publisher": "Elsevier", "pagerange": "1-12", "id_number": "CaltechAUTHORS:20101123-150925263", "issn": "0082-0784", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20101123-150925263", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "other_numbering_system": { "items": [ { "id": "372", "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "doi": "10.1016/S0082-0784(06)80621-1", "resource_type": "article", "pub_year": "1994", "author_list": "Marble, Frank E." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/j4w57-8hy62", "eprint_id": 20994, "eprint_status": "archive", "datestamp": "2023-08-20 03:20:29", "lastmod": "2023-10-20 23:39:34", "type": "article", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } } ] }, "title": "Aerospace Propulsion Technology\u2014A Fertile Source of Issues in Basic Fluid Mechanics", "ispublished": "pub", "full_text_status": "public", "note": "\u00a9 1993 American Society of Mechanical Engineers. Richard L. and Dorothy M. Hayman Professor Emeritus, Mechanical Engineering and Jet Propulsion, California Institute of Technology, Pasadena, CA.\n\nPublished - 361_Marble_FE_1993.pdf
", "abstract": "[No abstract]", "date": "1993-12", "date_type": "published", "publication": "Journal of Fluids Engineering", "volume": "115", "number": "4", "publisher": "American Society of Mechanical Engineers", "pagerange": "545-546", "id_number": "CaltechAUTHORS:20101123-134419710", "issn": "0098-2202", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20101123-134419710", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "collection": "CaltechAUTHORS", "other_numbering_system": { "items": [ { "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center", "value": "Guggenheim Jet Propulsion Center" } ] }, "doi": "10.1115/1.2910176", "primary_object": { "basename": "361_Marble_FE_1993.pdf", "url": "https://authors.library.caltech.edu/records/j4w57-8hy62/files/361_Marble_FE_1993.pdf" }, "resource_type": "article", "pub_year": "1993", "author_list": "Marble, Frank E." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/m125p-ja609", "eprint_id": 20991, "eprint_status": "archive", "datestamp": "2023-08-20 03:20:26", "lastmod": "2023-10-20 23:39:24", "type": "article", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "F. E." } } ] }, "title": "Response of a Thin Airfoil Encountering a Strong Density\n Discontinuity", "ispublished": "pub", "full_text_status": "public", "note": "\u00a9 1993, The American Society of Mechanical Engineers. \n\nDedicated to Professor W. R Sears on the occasion of his 80th birthday. Contributed by the Fluids Engineering Division for publication in the JOURNAL OF FLUIDS ENGINEERING. Manuscript received by the Fluids Engineering Division June 29, 1993; revised manuscript received September 23, 1993. Associate Technical Editor: D. P. Telionis.\n\nPublished - 360_Marble_FE_1993.pdf
", "abstract": "Airfoil theory for unsteady motion has been developed extensively assuming the undisturbed medium to be of uniform density, a restriction accurate for motion in the atmosphere, Glauert (1929), Burgers (1935), Theodorsen (1935), Kussner (1936), Karman and Sears (1938), Kinney and Sears (1975). In some instances, notably for airfoils comprising fan, compressor and turbine blade rows, the undisturbed medium may carry density variations or \"spots,\" resulting from non-uniformaties in temperature or composition, of a size comparable to the blade chord. This condition existsfor turbine blades, Marble (1975), Giles and Krouthen (1988), immediately downstream of the main burner of a gas turbine engine where the density fluctuations of the order of 50 percent may occur. Disturbances of a somewhat smaller magnitude arise from the ingestion of hot boundary layers into fans, Wortman (1975), and exhaust into hovercraft. Because these regions of non-uniform density convect with the moving medium, the airfoil experiences a time varying load and moment which we propose to calculate.", "date": "1993-12", "date_type": "published", "publication": "Journal of Fluids Engineering", "volume": "115", "number": "4", "publisher": "American Society of Mechanical Engineers", "pagerange": "580-589", "id_number": "CaltechAUTHORS:20101123-132225533", "issn": "0098-2202", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20101123-132225533", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "other_numbering_system": { "items": [ { "id": "360", "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "doi": "10.1115/1.2910183", "primary_object": { "basename": "360_Marble_FE_1993.pdf", "url": "https://authors.library.caltech.edu/records/m125p-ja609/files/360_Marble_FE_1993.pdf" }, "resource_type": "article", "pub_year": "1993", "author_list": "Marble, F. E." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/j63pr-mrn65", "eprint_id": 21031, "eprint_status": "archive", "datestamp": "2023-08-20 01:27:36", "lastmod": "2024-01-13 00:06:55", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Budzinski-J-M", "name": { "family": "Budzinski", "given": "John M." } }, { "id": "Zukoski-E-E", "name": { "family": "Zukoski", "given": "Edward E." } }, { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } } ] }, "title": "Rayleigh Scattering Measurements of Shock Enhanced Mixing", "ispublished": "unpub", "full_text_status": "public", "note": "\u00a9 1992 by John Budzinski. Published by the American Institute of Aeronautics and Astronautics, Inc. with permission.\n\nPublished - 332_Budzinski_JM_1992.pdf
", "abstract": "This investigation was concerned with the nuxmg\nwhich occurs after the unsteady interaction of a shock\nwave with a laminar jet of helium. The jet of helium was\ninjected normal to the direction of the propagation of the\nshock. The primary diagnostic, planar Rayleigh\nscattering, had sufficient spatial and temporal resolution\nto resolve the smallest diffusion scales present and\nallowed helium mole fractions to be measured in twodimensional\nplanes normal to the original jet flow\ndirection. The amount of molecular mixing was\nevaluated with a mass distribution function at increasing\ntimes after the shock interaction. The total masses of\nhelium contained in regions where the molar\nconcentration of helium was at least 30% and 50% were\nalso calculated. The shock Mach number was varied, and\nthe effect of a reflected shock was studied. It was found\nthat shock interactions can significantly increase the\nmixing between the air and helium. A rough collapse of\nthe mixing data occurs when time is normalized by the jet\nradius divided by the change in velocity of the air behind\nthe shock. An increase in the enhancement of mixing\noccurred after the interaction with the reflected shock.", "date": "1992-07", "date_type": "published", "publisher": "American Institute of Aeronautics and Astronautics", "id_number": "CaltechAUTHORS:20101129-084947901", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20101129-084947901", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "other_numbering_system": { "items": [ { "id": "1992-3546", "name": "AIAA" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "primary_object": { "basename": "332_Budzinski_JM_1992.pdf", "url": "https://authors.library.caltech.edu/records/j63pr-mrn65/files/332_Budzinski_JM_1992.pdf" }, "resource_type": "monograph", "pub_year": "1992", "author_list": "Budzinski, John M.; Zukoski, Edward E.; et el." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/1s1ng-kxc10", "eprint_id": 21069, "eprint_status": "archive", "datestamp": "2023-08-20 00:55:01", "lastmod": "2024-01-13 00:07:03", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Waitz-I-A", "name": { "family": "Waitz", "given": "Ian A." } }, { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } }, { "id": "Zukoski-E-E", "name": { "family": "Zukoski", "given": "Edward E." } } ] }, "title": "A Systematic Experimental and Computational Investigation of a Class of Contoured Wall Fuel Injectors", "ispublished": "unpub", "full_text_status": "public", "note": "\u00a9 1992 American Institute of Aeronautics and Astronautics. Inc. All rights reserved. Funding for this work was provided largely through NASA Grant NAG 1-842. The fundamentals of shock-enhanced mixing were developed earlier under Contract F49620-86-C-0113 administered by the Air Force Office of Scientific Research. The authors wish to thank many members of the technical staff at NASA Langley Research Center, particularly D. Bushnell, S. Robinson. M. Walsh, members of the Experimental Flow Physics Branch, and members of the Computational Methods Branch. The planar Rayleigh scattering data alluded to at several points in the discussion were the product of a collaborative effort with the Optical Spectroscopy Section of NASA Langley's Instrument Research Division. Supercomputing support was provided by the San Diego Supercomputer Center via a National Science Foundation Grant, the NASA Ames NAS facilities, the JPL/Caltech Cray, and the NASA Langley supercomputing facilities.\n\nPublished - 328_Waitz_IA_1992.pdf
", "abstract": "The performance of a particular class of fuel injectors for\nscramjet engine applications is addressed. The contoured\nwall injectors were aimed at augmenting mixing through\naxial vorticity production arising from interaction of the\nfueVair interface with an oblique shock. Helium was used to\nsimulate hydrogen fuel and was injected at Mach 1.7 into a\nMach 6 airstream. The effects of incoming boundary layer\nheight. injector spacing, and injectant to freestream pressure and velocity ratios were investigated. Results from threedimensional flow field surveys and Navier-Stokes\nsimulations are presented. Performance was judged in\nterms of mixing, loss generation and jet penetration.\nInjector performance was strongly dependent on the\ndisplacement effect of the hypersonic boundary layer which\nacted to modify the effective wall geometry. The impact of\nthe boundary layer varied with injector array spacing.\nWidely-spaced arrays were more resilient to the detrimental\neffects of large boundary layers. Strong dependence on\ninjectant to free stream pressure ratio was also displayed.\nPressure ratios near unity were most conducive to losseffective mixing and strong jet penetration. Effects due to variation in mean shear associated with non-unity velocity ratios were found to be secondary within the small range of values tested.", "date": "1992-01", "date_type": "published", "publisher": "American Institute of Aeronautics and Astronautics", "id_number": "CaltechAUTHORS:20101130-132815278", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20101130-132815278", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "other_numbering_system": { "items": [ { "id": "92-0625", "name": "AIAA" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "primary_object": { "basename": "328_Waitz_IA_1992.pdf", "url": "https://authors.library.caltech.edu/records/1s1ng-kxc10/files/328_Waitz_IA_1992.pdf" }, "resource_type": "monograph", "pub_year": "1992", "author_list": "Waitz, Ian A.; Marble, Frank E.; et el." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/pg1n6-a6682", "eprint_id": 20934, "eprint_status": "archive", "datestamp": "2023-08-20 00:42:27", "lastmod": "2024-01-13 00:06:46", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Waitz-I-A", "name": { "family": "Waitz", "given": "Ian A." } }, { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } }, { "id": "Zukoski-E-E", "name": { "family": "Zukoski", "given": "Edward E." } } ] }, "title": "Vorticity Generation by Contoured Wall Injectors", "ispublished": "unpub", "full_text_status": "public", "note": "\u00a9 1992 American Institute of Aeronautics and Astronautics,\nInc. Funding for this work was provided largely through NASA\nGrant NAG 1-842. The fundamentals of shock-enhanced\nmixing were developed earlier under Contract F49620-86-C-\n0113 administered by the Air Force Office of Scientific\nResearch. The authors wish to thank many members of the\ntechnical staff at NASA Langley Research Center,\nparticularly D. Bushnell, S. Robinson, M. Walsh, members\nof the Experimental Flow Physics Branch, and members of\nthe Computational Methods Branch. Supercomputing\nsupport was provided by the San Diego Supercomputer\nCenter via a National Science Foundation Grant, the NASA\nAmes NAS facilities, the JPL/Caltech Cray, and the NASA\nLangley supercomputing facilities.\n\nPublished - 336_Waitz_IA_1992.pdf
", "abstract": "A class of contoured wall fuel injectors was designed to\nenable shock-enhancement of hypervelocity mixing for\nsupersonic combustion ramjet applications. Previous\nstudies of these geometries left unresolved questions\nconcerning the relative importance of various axial vorticity\nsources in mixing the injectant with the freestream. The\npresent study is a numerical simulation of two generic fuel\ninjectors which is aimed at elucidating the relative roles of\naxial vorticity sources including: baroclinic torque through\nshock-impingement, cross-stream shear, turning of\nboundary layer vorticity, shock curvature, and diffusive flux.\nBoth the magnitude of the circulation, and the location of\nvorticity with respect to the mixing interface were\nconsidered. Baroclinic torque and cross-stream shear were\nfound to be most important in convectively mixing the\ninjectant with the freestream, with the former providing for\ndeposition of vorticity directly on the fue1/air interface.", "date": "1992", "date_type": "published", "publisher": "American Institute of Aeronautics and Astronautics", "id_number": "CaltechAUTHORS:20101122-094355204", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20101122-094355204", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "NASA", "grant_number": "NAG 1-842" }, { "agency": "Air Force Office of Scientific Research", "grant_number": "F49620-86-C-0113" }, { "agency": "NSF" }, { "agency": "NASA Ames NAS facilities" }, { "agency": "JPL/Caltech Cray" }, { "agency": "NASA Langley supercomputing facilities" } ] }, "other_numbering_system": { "items": [ { "id": "92-3550", "name": "AIAA" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "primary_object": { "basename": "336_Waitz_IA_1992.pdf", "url": "https://authors.library.caltech.edu/records/pg1n6-a6682/files/336_Waitz_IA_1992.pdf" }, "resource_type": "monograph", "pub_year": "1992", "author_list": "Waitz, Ian A.; Marble, Frank E.; et el." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/yh17a-hdm31", "eprint_id": 21058, "eprint_status": "archive", "datestamp": "2023-08-20 00:05:34", "lastmod": "2024-01-13 00:07:01", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Waitz-I-A", "name": { "family": "Waitz", "given": "Ian-A" } }, { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } }, { "id": "Zukoski-E-E", "name": { "family": "Zukoski", "given": "Edward E." } } ] }, "title": "An investigation of a contoured wall injector for hypervelocity mixing augmentation", "ispublished": "unpub", "full_text_status": "public", "note": "\u00a9 1991 American Institute of Aeronautics and Astronautics, Inc. All rights reserved. For permission to copy or republish, contact American Institute of Aeronautics and Astronautics. Funding for this work was provided largely through NASA Grant NAG 1-842. The authors wish to thank\nmany members of the technical staff at NASA Langley\nResearch Center. particularly Dennis Bushnell. members\nof the Experimental Flow Physics Branch, and members\nof the Computational Methods Branch. The Rayleigh\nscattering data were obtained through a collaborative\neffort with B. Shirinzadeh. J. Balla. M. Hillard and R.\nExton of the Instrument Research Division's Optical\nSpectroscopy Section. Supercomputing support was\nprovided by the San Diego Supercomputer Center via a\nNational Science Foundation Grant. the NASA Ames\nNAS facilities. the JPL/Caltech Cray. and the NASA\nLangley supercomputing facilities.\n\nPublished - 321_Waitz_IA_1991.pdf
", "abstract": "An experimental and computational investigation of a\ncontoured wall fuel injector is presented. The injector\nwas aimed at enabling shock-enhanced mixing for the\nsupersonic combustion ramjet engines currently envisioned for applications on hypersonic vehicles. Three-dimensional flow field surveys, and temporally resolved planar Rayleigh scattering measurements are presented for Mach 1.7 helium injection into Mach 6 air. These experimental data are compared directly with a three-dimensional Navier-Stokes simulation of the flow about the injector array. Two dominant axial vorticity sources are identified and characterized. The axial vorticity produced strong convective mixing of the injectant with the freestream. Shock-impingement was particularly effective as it assured seeding of baroclinic vorticity directly on the helium/air interface. The vorticity coalesced into a counter-rotating vortex pair of a sense which produced migration of the helium away from the wall. The influences of spatial averaging on the representation of the flow field as well as the importance of the fluctuating component of the flow in producing molecularly-mixed fluid are addressed.", "date": "1991-06", "date_type": "published", "publisher": "American Institute of Aeronautics and Astronautics", "id_number": "CaltechAUTHORS:20101130-101649129", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20101130-101649129", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "NASA", "grant_number": "NAG 1-842" }, { "agency": "NSF" } ] }, "other_numbering_system": { "items": [ { "id": "91-2265", "name": "AIAA" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "primary_object": { "basename": "321_Waitz_IA_1991.pdf", "url": "https://authors.library.caltech.edu/records/yh17a-hdm31/files/321_Waitz_IA_1991.pdf" }, "resource_type": "monograph", "pub_year": "1991", "author_list": "Waitz, Ian-A; Marble, Frank E.; et el." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/4b59h-1v374", "eprint_id": 21280, "eprint_status": "archive", "datestamp": "2023-08-19 22:07:02", "lastmod": "2024-01-13 00:07:48", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "F. E." } }, { "id": "Zukoski-E-E", "name": { "family": "Zukoski", "given": "E. E." } }, { "id": "Jacobs-J-W", "name": { "family": "Jacobs", "given": "J. W." } }, { "id": "Hendricks-G-J", "name": { "family": "Hendricks", "given": "G. J." } }, { "id": "Waitz-I-A", "name": { "family": "Waitz", "given": "I. A." } } ] }, "title": "Shock enhancement and control of hypersonic mixing and combustion", "ispublished": "unpub", "full_text_status": "public", "note": "\u00a9 1990 American Institute of Aeronautics and Astronautics. \n\nThis work was carried out under grants from URI and AFOSR with the support of Dr. Julian Tishkoff, and from NASA with the support of Mr. Dennis Bushnell. The computations have been carried out with\ncode support from Dr.'s P. J. Boris and E. S. Oran at the Naval Research Laboratory, and the Computational Branch, NASA Langley RC. Computing support has been obtained from NAS Facility at NASA Ames RC, the JPL/Caltech Cray X-MP, and the San Diego Supercomputer Center, NSF.\n\nPublished - 316_Marble_FE_1981.pdf
", "abstract": "The possibility that shock enhanced mixing can\nsubstantially increase the rate of mixing between\ncoflowing streams of hydrogen and air has been\nstudied in experimental and computational investigations.\nEarly numerical computations indicated that\nthe steady interaction between a weak shock in air\nwith a coflowing hydrogen jet can be well approximated\nby the two-dimensional time-dependent interaction\nbetween a weak shock and an initially circular\nregion filled with hydrogen imbedded in air. An experimental\ninvestigation of the latter process has been\ncarned out in the Caltech 17 Inch Shock Tube in experiments\nin which the laser induced fluorescence of\nbyacetyl dye is used as a tracer for the motion of the\nhelium gas after shock waves have passed across the\nhelium cylinder. The flow field has also been studied\nusing an Euler code computation of the flow field.\nBoth investigations show that the shock impinging\nprocess causes the light gas cylinder to split into two\nparts. One of these mixes rapidly with air and the\nother forms a stably stratified vortex pair which mixes\nmore slowly; about 60% of the light gas mixes rapidly\nwith the ambient fluid. The geometry of the flow field\nand the mixing process and scaling parameters are\ndiscussed here. The success of this program encouraged\nthe exploration of a low drag injection system in\nwhich the basic concept of shock generated streamwise\nvorticity could be incorporated in an injector for\na Scramjet combustor at Mach numbers between 5\nand 8. The results of a substantial computational\nprogram and a description of the wind tunnel model and preliminary experimental results obtained in the\nHigh Reynolds Number Mach 6 Tunnel at NASA Langley\nResearch Center are given here.", "date": "1990", "date_type": "published", "publisher": "American Institute of Aeronautics and Astronautics", "id_number": "CaltechAUTHORS:20101209-134118457", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20101209-134118457", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "URI" }, { "agency": "Air Force Office of Scientific Research (AFOSR)" }, { "agency": "NASA" } ] }, "other_numbering_system": { "items": [ { "id": "90-1981", "name": "AIAA" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "primary_object": { "basename": "316_Marble_FE_1981.pdf", "url": "https://authors.library.caltech.edu/records/4b59h-1v374/files/316_Marble_FE_1981.pdf" }, "resource_type": "monograph", "pub_year": "1990", "author_list": "Marble, F. E.; Zukoski, E. E.; et el." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/yzft0-jps07", "eprint_id": 21145, "eprint_status": "archive", "datestamp": "2023-08-19 21:35:37", "lastmod": "2023-10-20 23:47:36", "type": "article", "metadata_visibility": "show", "creators": { "items": [ { "id": "Sobota-T-H", "name": { "family": "Sobota", "given": "Thomas H." } }, { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } } ] }, "title": "Swirling flows in an annular-to-rectangular transition section", "ispublished": "pub", "full_text_status": "restricted", "note": "\u00a9 1989 American Institute of Aeronautics and Astronautics, Inc. \nPresented as Paper 87-2108 at the AIAA/SAE/ASME/ASEE 23rd Joint Propulsion Conference. San Diego, CA, June 29-July 2, 1987; received Aug. 3, 1987; revision received May 9, 1988.", "abstract": "Mechanisms for generation of axial vorticity by swirling flows in rectangular nozzles have been investigated\nexperimentally and computationally. A detailed experimental investigation is described that demonstrates the\nformation of axial vortices in the nozzle is dependant on the vorticity distribution at the turbine exhaust. Further,\nmechanisms providing for the formation of axial vortices are identified. A parallel computational investigation was\ncarried out that not only confirmed the relationship between the turbine exhaust vorticity and the vortex patterns\nformed in the nozzle, but also provided details of the flowfield between the turbine discharge and the nozzle exit.\nOn the basis of this more detailed understanding, it is now possible to \"tailor\" the vortex distribution at the nozzle\nexit by design of the turbine discharge and the intervening passage.", "date": "1989-05", "date_type": "published", "publication": "Journal of Propulsion and Power", "volume": "5", "number": "3", "publisher": "AIAA", "pagerange": "334-340", "id_number": "CaltechAUTHORS:20101203-094947244", "issn": "0748-4658", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20101203-094947244", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "other_numbering_system": { "items": [ { "id": "87-2108", "name": "AIAA" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "doi": "10.2514/3.23157", "resource_type": "article", "pub_year": "1989", "author_list": "Sobota, Thomas H. and Marble, Frank E." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/b42fw-gck40", "eprint_id": 105940, "eprint_status": "archive", "datestamp": "2023-08-22 06:12:14", "lastmod": "2024-01-15 18:12:57", "type": "book_section", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } }, { "id": "Hendricks-G-J", "name": { "family": "Hendricks", "given": "Gavin J." } }, { "id": "Zukoski-E-E", "name": { "family": "Zukoski", "given": "Edward E." } } ] }, "title": "Progress Toward Shock Enhancement of Supersonic Combustion Processes", "ispublished": "unpub", "full_text_status": "restricted", "keywords": "Shock Wave; Shear Layer; Shock Tube; Diffusion Flame; Adverse Pressure Gradient", "note": "\u00a9 Springer-Verlag New York Inc. 1989.", "abstract": "In air breathing propulsion systems for flight at Mach numbers 7 to 20, it is generally accepted that the combustion processes will be carried out at supersonic velocities with respect to the engine. The resulting brief residence time places a premium on rapid mixing of the fuel and air. To address this issue we are investigating a mechanism for enhancing the rate of mixing between air and hydrogen fuel over rates that are expected in shear layers and jets. \n\nThe mechanism rests upon the strong vortiCity induced at the interface between a light and heavy gas by an intense pressure gradient. The specific phenomenon under investigation is the rapid mixing induced by interaction of a weak oblique shock with a cylindrical jet of hydrogen embedded in air. The status of our investigations is described in three parts: a) shock tube investigation of the distortion and mixing induced by shock waves impinging on cylindric of hydrogen embedded in air, b) the molecular mixing and chemical reaction in large vortices, periodically formed in a channel, and c) two-dimensional non-steady and three-dimensional steady numerical studies of shock interaction with cylindrical volumes of hydrogen in air.", "date": "1989", "date_type": "published", "publisher": "Springer US", "place_of_pub": "New York, NY", "pagerange": "932-950", "id_number": "CaltechAUTHORS:20201008-131242789", "isbn": "9780387968872", "book_title": "Turbulent Reactive Flows", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20201008-131242789", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "contributors": { "items": [ { "id": "Borghi-R", "name": { "family": "Borghi", "given": "R." } }, { "id": "Murthy-S-N-B", "name": { "family": "Murthy", "given": "S. N. B." } } ] }, "doi": "10.1007/978-1-4613-9631-4_43", "resource_type": "book_section", "pub_year": "1989", "author_list": "Marble, Frank E.; Hendricks, Gavin J.; et el." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/twwae-s8609", "eprint_id": 21131, "eprint_status": "archive", "datestamp": "2023-08-19 20:01:31", "lastmod": "2023-10-20 23:46:48", "type": "article", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } }, { "id": "Hendricks-G-J", "name": { "family": "Hendricks", "given": "Gavin J." } } ] }, "title": "Structure and behavior of diffusion flames in a pressure gradient", "ispublished": "pub", "full_text_status": "restricted", "note": "\u00a9 1988 Combustion Institute; Published by Elsevier Inc. Twenty-First Symposium (International on Combustion). Available online 14 July 2007. The authors are grateful for several illuminating discussions with Professor T. Kubota.\nThis work was supported in part by AFOSR grant AFOSR-84-0286 under Dr. Julian M. Tishkoff, Directorate of Aerospace Sciences. The second author has also been supported by\na Charles Lee Powell fellowship.", "abstract": "The structure of a diffusion flame embedded in a flow field parallel to the flame is studied under conditions where this external flow imposes an adverse pressure gradient. It is convenient to think of the physical problem as a flame lying along the flow direction of a divergent channel.\nThe mathematical problem is reduced to a set of ordinary differential equations by (i) employing the Howarth transformation to eliminate the variable density and (ii) introducing a similarity solution somewhat in the manner of the Falkner-Skan treatment of boundary layer flows.\nBecause the low-density gas near the flame responds more readily to the pressure gradient than does the higher density gas, a reverse flow develops in the low density region which severely affects both the structure of the flame and the fuel consumption rate. For a flame with unit stoichiometry, the reverse flow eventually leads to extinction of the flame by separating the two shear layers that bound the fuel and oxidizer streams. For stoichiometry\ncorresponding to methane-air, the flame situates itself near the oxidizer side of the reverse flow and has no tendency toward extinguishment.", "date": "1988", "date_type": "published", "publication": "Symposium International on Combustion", "volume": "21", "number": "1", "publisher": "Elsevier", "pagerange": "1321-1327", "id_number": "CaltechAUTHORS:20101202-142309487", "issn": "0082-0784", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20101202-142309487", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "Air Force of Scientific Research (AFOSR)", "grant_number": "AFOSR-84-0286" }, { "agency": "Charles Lee Powell Foundation" } ] }, "other_numbering_system": { "items": [ { "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "doi": "10.1016/S0082-0784(88)80363-1", "resource_type": "article", "pub_year": "1988", "author_list": "Marble, Frank E. and Hendricks, Gavin J." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/y7w3d-08a25", "eprint_id": 21159, "eprint_status": "archive", "datestamp": "2023-08-19 19:02:53", "lastmod": "2024-01-13 00:07:25", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Sobota-T-H", "name": { "family": "Sobota", "given": "Thomas H." } }, { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } } ] }, "title": "An Experimental and Numerical Investigation of Swirling Flows in a Rectangular Nozzle", "ispublished": "unpub", "full_text_status": "public", "note": "\u00a9 American Institute of Aeronautics and Astronautics, Inc., 1987.\n\nPublished - 352_Sobota_TH_1987.pdf
", "abstract": "The high thrust to weight ratios now possible for military aircraft have made thrust vector pitch control more attractive and versatile than aerodynamic surface pitch control. Use of a rectangular nozzle is a natural consequence because articulation and sealing problems are less formidable than for conventional circular ones. The rectangular nozzle offers the additional possibility that the exhaust may mix rapidly with the ambient air and thereby reduce the radiative signature of the exhaust. A detailed experimental investigation is described, which demonstrates that the formation of axial vortices in the nozzle is dependent on the vorticity distribution at the turbine exhaust. Further, three mechanisms which provide for the formation of axial vortices are identified. A parallel computational investigation was carried out which not only confirmed the relationship between the turbine exhaust vorticity and the vortex pattern formed in the nozzle but also provided details of the flow field between the turbine discharge and the nozzle exit. On the basis of this more detailed understanding, it is now possible to tailor the vortex distribution at the nozzle exit by design of the turbine discharge and the intervening passage.", "date": "1987", "date_type": "published", "publisher": "American Institute of Aeronautics and Astronautics", "id_number": "CaltechAUTHORS:20101203-145603258", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20101203-145603258", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "other_numbering_system": { "items": [ { "id": "87-2108", "name": "AIAA" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "primary_object": { "basename": "352_Sobota_TH_1987.pdf", "url": "https://authors.library.caltech.edu/records/y7w3d-08a25/files/352_Sobota_TH_1987.pdf" }, "resource_type": "monograph", "pub_year": "1987", "author_list": "Sobota, Thomas H. and Marble, Frank E." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/q52jm-t0410", "eprint_id": 21097, "eprint_status": "archive", "datestamp": "2023-08-19 19:02:32", "lastmod": "2024-01-13 00:07:09", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } }, { "id": "Hendricks-G-J", "name": { "family": "Hendricks", "given": "Gavin J." } }, { "id": "Zukoski-E-E", "name": { "family": "Zukoski", "given": "Edward E." } } ] }, "title": "Progress toward shock enhancement of supersonic combustion processes", "ispublished": "unpub", "full_text_status": "public", "note": "\u00a9 1987, AIAA.\n\nPublished - 295_Marble_FE_1987.pdf
", "abstract": "In air breathing propulsion systems for flight at Mach numbers 7 to 20, it is generally accepted that the combustion processes will be carried out at supersonic velocities with respect to the engine. The resulting brief residence time places a premium on rapid mixing of the\nfuel and air. To address this issue we &re investigating a mechanism for enhancing the rate of mixing between air and hydrogen fuel over rates that are expected in shear layers and jets. The mechanism rests upon the strong vorticity induced at the interface between a light and heavy gas by an intense pressure gradient. The specific phenomenon under investigation is the rapid mixing induced by interaction of a weak oblique shock with a cylindrical jet of hydrogen embedded in air. The status of our investigations is described in three parts: a) shock tube investigation of the distortion and mixing induced by shock waves\nimpinging on cylindric of hydrogen embedded in air, b) the molecular mixing and chemical reaction in large vortices, periodically formed in a channel, and c) two-dimensional non-steady and three-dimensional steady numerical studies of shock interaction with cylindrical volumes of hydrogen in air.", "date": "1987", "date_type": "published", "publisher": "American Institute of Aeronautics and Astronautics", "id_number": "CaltechAUTHORS:20101201-110408219", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20101201-110408219", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "other_numbering_system": { "items": [ { "id": "87-1880", "name": "AIAA" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "primary_object": { "basename": "295_Marble_FE_1987.pdf", "url": "https://authors.library.caltech.edu/records/q52jm-t0410/files/295_Marble_FE_1987.pdf" }, "resource_type": "monograph", "pub_year": "1987", "author_list": "Marble, Frank E.; Hendricks, Gavin J.; et el." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/gwfaj-34k40", "eprint_id": 21144, "eprint_status": "archive", "datestamp": "2023-08-19 18:35:04", "lastmod": "2023-10-20 23:47:28", "type": "article", "metadata_visibility": "show", "creators": { "items": [ { "id": "Darabiha-N", "name": { "family": "Darabiha", "given": "N." } }, { "id": "Candel-S-M", "name": { "family": "Candel", "given": "S. M." } }, { "id": "Marble-F-E", "name": { "family": "Marble", "given": "F. E." } } ] }, "title": "The Effect of Strain Rate on a Premixed Laminar Flame", "ispublished": "pub", "full_text_status": "restricted", "note": "\u00a9 1986 by N. Darabiha, S. M. Candel, and F. E. Marble.\nPublished by Elsevier Science Publishing Co., Inc. Received 2 May 1985; revised 30 October 1985. This work has been supported by a CNRS ATP and an SNECMA contract. Part of this study was performed while one of us\n(F.E.M.) was on a sabbatical at Ecole Centrale. N. Darabiha and S. M. Candel wish to thank Y. Sadallah for his help in the initial development of the computer code used in this paper. All calculations were performed on an IBM 4341 computer made available to us by the IBM Co.", "abstract": "The structure of a strained premixed laminar flame is examined. The flame is formed in the vicinity of a\nstagnation point established by the counterflow of fresh mixture and hot combustion products. This ideal\nconfiguration analyzed by Libby and Williams [18] with activation energy asymptotics is here examined\nnumerically. This allows an exact description of flame and flow structure and a calculation of the mass rate of\nreaction per unit flame area for the whole range of strain rates. Previous results obtained for intermediate and\nhigh strain rates are confirmed. However, for low strain rates the mass rate of reaction per unit flame area\ndiffers from that determined with large activation energy asymptotics. The present calculations also provide\nthe exact value of the strain rate (or Damkiihler number) for which the partial extinction regime appears. If the\nstrain rate is increased beyond that value the flame front develops on the hot side of the stagnation point. The\nreactive front first moves away from the stagnation point and then moves back toward that point for the very\nlarge values of the strain rate.", "date": "1986-05", "date_type": "published", "publication": "Combustion and Flame", "volume": "64", "number": "2", "publisher": "Elsevier", "pagerange": "203-217", "id_number": "CaltechAUTHORS:20101203-093502119", "issn": "0010-2180", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20101203-093502119", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "Centre National de la Recherche Scientifique (CNRS)" }, { "agency": "ATP" }, { "agency": "Soci\u00e9t\u00e9 Nationale d'\u00c9tude et de Construction de Moteurs d'Aviation (SNECMA)" } ] }, "other_numbering_system": { "items": [ { "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "doi": "10.1016/0010-2180(86)90057-X", "resource_type": "article", "pub_year": "1986", "author_list": "Darabiha, N.; Candel, S. M.; et el." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/knxj3-vw617", "eprint_id": 21081, "eprint_status": "archive", "datestamp": "2023-08-19 18:10:34", "lastmod": "2023-10-20 23:44:54", "type": "article", "metadata_visibility": "show", "creators": { "items": [ { "id": "Karagozian-A-R", "name": { "family": "Karagozian", "given": "Ann R." } }, { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } } ] }, "title": "Study of a Diffusion Flame in a Stretched Vortex", "ispublished": "pub", "full_text_status": "restricted", "note": "\u00a9 1986 Gordon and Breach Science Publishers, Inc. Received October 15, 1984; in final form March 27, 1985.", "abstract": "The time dependent interaction of a laminar diffusion flame with a single plane vortex and with a stretched line vortex is examined with the aim of determining the flame configuration and the augmentation to the reactant consumption rate resulting from the interaction. Elements\nof the resulting curved flame sheets behave essentially as isolated flames until the neighboring flame sheets become so closely spaced that they interact and consume the intervening reactant. This process creates a core of combustion products with external isolated flame surfaces. The augmentation of the reactant consumption rate results both from the local straining of the flame in its own plane and from the overall increase in flame surface area. Three examples are treated in detail. The first is the plane problem in which an initially straight flame is distorted by a vortex. In the second, the situation is similar except that the problem is expanded to three dimensions\nand the vortex line is being stretched along its own axis. Finally, the effects of the density change resulting from the heat release are examined.", "date": "1986", "date_type": "published", "publication": "Combustion Science and Technology", "volume": "45", "number": "1-2", "publisher": "Taylor & Francis", "pagerange": "65-84", "id_number": "CaltechAUTHORS:20101201-080248569", "issn": "0010-2202", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20101201-080248569", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "other_numbering_system": { "items": [ { "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "doi": "10.1080/00102208608923842", "resource_type": "article", "pub_year": "1986", "author_list": "Karagozian, Ann R. and Marble, Frank E." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/g3zd0-7n623", "eprint_id": 21207, "eprint_status": "archive", "datestamp": "2023-08-19 17:20:28", "lastmod": "2023-10-20 23:50:50", "type": "book_section", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "F. E." } } ] }, "title": "Growth of a Diffusion Flame in the Field of a Vortex", "ispublished": "unpub", "full_text_status": "public", "keywords": "COMBUSTIBLE FLOW | DIFFUSION FLAMES | FLAME PROPAGATION | FUEL COMBUSTION | VORTICES | FUEL CONSUMPTION | REACTION KINETICS | REYNOLDS NUMBER | SCHMIDT NUMBER", "note": "\u00a9 1985, New York, Plenum Press. This work was supported, in part, by grant AFOSR-80-0265 and by NASA grant NAG 3-70.\n\nPublished - 344_Marble_FE_1985.pdf
", "abstract": "A simple diffusion flame with fast chemical kinetics is\ninitiated along the horizontal axis between a fuel occupying the upper half-plane and an oxidizer below. Simultaneously a vortex of circulation T is established at the origin. As time progresses the flame is extended and \"wound up\" by the vortex flow field and the viscous core\nof the vortex spreads, converting the motion in the core to a solid-body rotation. The kinematics of the flame extension and distortion is described and the effect of the local-flow field upon local-flame structure is analyzed in detail. It is shown that the combustion field consists of a\ntotally reacted core region, whose radius is time dependent, and an external flame region consisting of a pair of spiral arms extending off at large radii toward their original positions on the horizontal axis. The growth of the reacted core, and the reactant-consumption rate augmentation by the vortex field in both core and outer-flame regions were determined for values of the Reynolds number (T/2\u03c0v) between 1 and 10^3 and for a wide range of Schmidt numbers (v / D) covering both gas and liquid reactions. For large values of Reynolds number the radius r _* of the reactant grows much more rapidly than the viscous core so that only the nearly inviscid portion of the flow is involved. The more accurate condition for this behavior is that R(Sc)^(1/2)>50 and, under this restriction, the\nsimilarity rule for the core radius growth is shown to be r _*(T^(2/3)D^(1/3)t)^(1/2)=0.5092+O(D/T)^(1/2) In this case also the reactant consumption rate becomes independent of\ntime and, for the complete diffusion flame in the vortex field, the augmentation of reactant-consumption rate due to the vortex field satisfies Augmented consumption rate == 1. 2327 ,-1.4527(D/T)^(1/6) + O(D/T)^(1/2) T^(2/3) D^(1/3) Both of these similarity rules are, as is appropriate for high Reynolds number, independent of kinematic viscosity.", "date": "1985", "date_type": "published", "publisher": "Plenum Press", "place_of_pub": "New York", "pagerange": "395-413", "id_number": "CaltechAUTHORS:20101207-085326836", "isbn": "0306410796", "book_title": "Recent advances in the aerospace sciences", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20101207-085326836", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "Air Force Office of Scientific Research (AFOSR)", "grant_number": "AFOSR-80-0265" }, { "agency": "NASA", "grant_number": "NAG 3-70" } ] }, "other_numbering_system": { "items": [ { "id": "A85-47304 23-31", "name": "CSA Illumina" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "primary_object": { "basename": "344_Marble_FE_1985.pdf", "url": "https://authors.library.caltech.edu/records/g3zd0-7n623/files/344_Marble_FE_1985.pdf" }, "resource_type": "book_section", "pub_year": "1985", "author_list": "Marble, F. E." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/an2gy-r1y81", "eprint_id": 21983, "eprint_status": "archive", "datestamp": "2023-08-19 15:31:18", "lastmod": "2023-10-23 15:34:34", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Zukoski-E-E", "name": { "family": "Zukoski", "given": "Edward E." } }, { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } } ] }, "title": "Experiments concerning the mechanism of flame blowoff from bluff bodies", "ispublished": "unpub", "full_text_status": "public", "note": "\u00a9 1983. The work described herein was performed at the Jet Propulsion Laboratory with financial support of the Ordnance Corps, U.S. Army.\n\nSubmitted - 82a_Zukoski_EE.pdf
", "abstract": "The general problem of flame stabilization on bluff objects centers about the determination of the maximum stream velocity at which stable combustion may be achieved for various flame holder geometries, gas mixtures and conditions of the approaching combustible stream. Since the process involves both gas dynamic problems and chemical kinetic problems of great complexity, the most reasonable approach is one of similarity, that is, to determine under what conditions the behavior of one flame holder is similar to the behavior of another one. Because a very large number of physical and chemical variables is involved in a combustion problem, similarity conditions can be formulated most easily after experimental investigations have indicated which parameters or groups exert little influence on the mechanism and hence may be neglected. The experiments\ndescribed in this paper were conducted with the object\nof clarifying the role of the more important parameters\nin the flame holding mechanism. The results indicate\nthat a relatively simple formulation of the similarity conditions may be obtained in which the fluid mechanical\nparameters and chemical parameters are effectively separated.", "date": "1983", "date_type": "published", "publisher": "Caltech Library", "id_number": "CaltechAUTHORS:20110203-125953778", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20110203-125953778", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U. S. Army Ordnance Corps" } ] }, "other_numbering_system": { "items": [ { "id": "82A", "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "primary_object": { "basename": "82a_Zukoski_EE.pdf", "url": "https://authors.library.caltech.edu/records/an2gy-r1y81/files/82a_Zukoski_EE.pdf" }, "resource_type": "monograph", "pub_year": "1983", "author_list": "Zukoski, Edward E. and Marble, Frank E." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/rmgmj-djj95", "eprint_id": 21255, "eprint_status": "archive", "datestamp": "2023-08-22 02:14:20", "lastmod": "2024-01-13 00:07:42", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } } ] }, "title": "Theoretical Analysis of Nitric Oxide Production in a Methane/Air Turbulent Diffusion Flame", "ispublished": "unpub", "full_text_status": "public", "keywords": "Flames; Nitrogen oxide(NO); Combustion; Air pollution; Turbulence; Diffusion flames; Mathematical models; Methane; Shear flow", "note": "\u00a9 1980, National Service Center for Environmental Publications (NSCEP). The authors wish to acknowledge an essential contribution of the technical staff of the Energy and Environmental Research Corporation to this work. \n\n[EPA] Contract No. 68-02-2613\nProgram Element No. INE829\nEPA Project Officer: W.S. Lanier\n\nPublished - 268_Marble_FE_1980.pdf
", "abstract": "The coherent flame model is applied to the methane-air turbulent diffusion flame with the objective of describing the production of nitric oxide. The example of a circular jet of methane discharging into a stationary air atmosphere is used to illustrate application of the model. In the model, the chemical reactions take place in laminar flame elements which are lengthened by the turbulent fluid motion and shortened when adjacent flame segments consume intervening reactant. The rates with which methane and\nair are consumed and nitric oxide generated in the strained laminar flame are computed numerically in an independent calculation. The model predicts nitric oxide levels of approximately 80 parts per million at the end of the flame generated by a 30.5 cm (1 foot) diameter jet of methane issuing at 3.05 x 10^3 cm/sec (100 ft/sec). The model also\npredicts that this level varies directly with the fuel jet diameter and inversely with the jet velocity. A possibly important nitric oxide production mechanism, neglected in\nthe present analysis, can be treated in a proposed extension to the model.", "date": "1980-01", "date_type": "published", "publisher": "Environmental Protection Agency", "id_number": "CaltechAUTHORS:20101209-090337380", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20101209-090337380", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "Environmental Protection Agency", "grant_number": "68-02-2613" } ] }, "other_numbering_system": { "items": [ { "id": "600/7-80-018", "name": "EPA" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "primary_object": { "basename": "268_Marble_FE_1980.pdf", "url": "https://authors.library.caltech.edu/records/rmgmj-djj95/files/268_Marble_FE_1980.pdf" }, "resource_type": "monograph", "pub_year": "1980", "author_list": "Marble, Frank E." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/kafrt-byz19", "eprint_id": 21850, "eprint_status": "archive", "datestamp": "2023-08-19 11:48:02", "lastmod": "2023-10-23 15:26:08", "type": "article", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } }, { "id": "Candel-S-M", "name": { "family": "Candel", "given": "Sebastien M." } } ] }, "title": "An analytical study of the non-steady behavior of large combustors", "ispublished": "pub", "full_text_status": "restricted", "note": "\u00a9 1979 Combustion Institute; Published by Elsevier B.V. \nAvailable online 5 May 2007.", "abstract": "The transient response of large burners depends primarily upon fluid mechanical adjustment rather than in time delays associated with transient chemical response. Examples of this behavior are the non-steady behavior of burners in utility boilers, and the low-frequency response of after burners in aircraft gas turbines. The non-steady behavior of a flame stabilized by a single-flame holder at the center of a long two-dimensional duct is investigated analytically when it is excited by periodic acoustic\ndisturbances that approach the flame zone from either the upstream or downstream direction. The flame zone itself is considered acoustically compact. The problem is treated by an integral technique in which relevant equations are integrated across high-density and low-density portions of the gas separately; the two fields are then coupled across the thin flame front, the determination of its shape being part of the solution. Transmission and reflection coefficients were calculated for a range of flame velocities, burner inlet flow velocities, combustion temperature ratio and imposed acoustic frequency.\nThe results showed that a considerably stronger pressure wave passed upstream of the flame than downstream, in the sense that could be expected from the different acoustic impedences of the hot and cold gas. Of most significance, however, was the very large (active) response of the burner at certain characteristic frequencies which corresponded to well-defined values of \u03c9L/u_o where L is the length of the flame zone and u_o is the flow velocity upstream of the burner. It is indicated that these energetic response modes result from vorticity shed from the distorted flame which induces a propagating wave along the flame front.", "date": "1979", "date_type": "published", "publication": "Symposium (International) on Combustion", "volume": "17", "number": "1", "publisher": "Elsevier", "pagerange": "761-769", "id_number": "CaltechAUTHORS:20110121-130330771", "issn": "0082-0784", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20110121-130330771", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "other_numbering_system": { "items": [ { "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "doi": "10.1016/S0082-0784(79)80074-0", "resource_type": "article", "pub_year": "1979", "author_list": "Marble, Frank E. and Candel, Sebastien M." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/t2737-xyc09", "eprint_id": 21327, "eprint_status": "archive", "datestamp": "2023-08-19 10:58:21", "lastmod": "2023-10-20 23:56:36", "type": "article", "metadata_visibility": "show", "creators": { "items": [ { "id": "Cumpsty-N-A", "name": { "family": "Cumpsty", "given": "N. A." } }, { "id": "Marble-F-E", "name": { "family": "Marble", "given": "F. E." } } ] }, "title": "The Interaction of Entropy Fluctuations with Turbine Blade Rows; A Mechanism of Turbojet Engine Noise", "ispublished": "pub", "full_text_status": "public", "note": "\u00a9 1977, Royal Society. Communicated by Sir William Hawthorne, F.R.S. Received 23 November 1976. The authors wish to express their gratitude for the assistance provided by the Boeing Airplane Company, Pratt & Whitney Aircraft, and Rolls-Royce Ltd., in making data available. They would also like to express the individual assistance by D. S. Whitehead of Cambridge University as well as R. R. Dils and E. M. Greitzer of Pratt and Whitney Aircraft.\n\nPublished - 243_Cumpsty_NA_1977.pdf
", "abstract": "The theory relating to the interaction of entropy fluctuations ('hot spots'), as well as vorticity and pressure, with blade rows is described. A basic feature of the model is that the blade rows have blades of sufficiently short chord that this is negligible in comparison with the wavelength of the disturbances. For the interaction of entropy with a blade row to be important, it is essential that the steady pressure change across the blade row should be large, although all unsteady perturbations are assumed small. A number of idealized examples have been calculated, beginning with isolated blade rows, progressing to single and then to several turbine stages. Finally, the model has been used to predict the low-frequency rearward-radiated acoustic power from a commercial turbojet engine. Following several assumptions, together with considerable empirical data, the correct trend and level are predicted, suggesting the mechanism to be important at low jet velocities.", "date": "1977-11-04", "date_type": "published", "publication": "Proceedings of the Royal Society A: Mathematical, physical, and engineering sciences", "volume": "357", "number": "1690", "publisher": "Royal Society of London", "pagerange": "323-344", "id_number": "CaltechAUTHORS:20101213-114306465", "issn": "1364-5021", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20101213-114306465", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "other_numbering_system": { "items": [ { "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "doi": "10.1098/rspa.1977.0171", "primary_object": { "basename": "243_Cumpsty_NA_1977.pdf", "url": "https://authors.library.caltech.edu/records/t2737-xyc09/files/243_Cumpsty_NA_1977.pdf" }, "resource_type": "article", "pub_year": "1977", "author_list": "Cumpsty, N. A. and Marble, F. E." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/arngp-3s557", "eprint_id": 21340, "eprint_status": "archive", "datestamp": "2023-08-19 10:52:46", "lastmod": "2023-10-20 23:57:24", "type": "article", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "F. E." } }, { "id": "Candel-S-M", "name": { "family": "Candel", "given": "S. M." } } ] }, "title": "Acoustic disturbance from gas non-uniformities convected through a nozzle", "ispublished": "pub", "full_text_status": "public", "note": "\u00a9 1977 Published by Elsevier Science Ltd. Received 6 September 1976; revised 1 July 1977. Available online 24 July 2003.", "abstract": "The non-steady flow generated by convection of gas containing non-uniform temperature regions or \"entropy spots\" through a nozzle is examined analytically as a source of acoustic disturbance. The first portion of the investigation treats the \"compact nozzle\", the case\nwhere all wave lengths are much longer than the nozzle. Strengths of transmitted and reflected one-dimensional waves are given for supersonic and subsonic nozzles and for one configuration of supersonic nozzle with normal shock at the outlet. In addition to a wave reflected from the nozzle inlet, the supersonic nozzle discharges two waves, one facing upstream and the other facing downstream. For reasonable values of the nozzle inlet Mach number, the pressure amplitude of each wave increases directly as the discharge Mach number. The acoustic perturbations from a supercritical nozzle of finite length, in which the\nundisturbed gas velocity increases linearly through the nozzle, are analyzed for several inlet and discharge Mach number values and over a wide frequency range. The results,\nwhich agree with the compact analysis for low frequency, deviate considerably as the frequency rises, achieving pressure fluctuation levels of several times the compact values. It is shown that this result originates in a phase shift between the two waves emitted downstream and that the pressure fluctuations for moderate frequencies may be approximated from the compact analysis with an appropriate phase shift. In all cases, the pressure fluctuations caused by a 2% fluctuation in absolute inlet temperature are large enough to require consideration in acoustic analysis of nozzles or turbine blade channels.", "date": "1977-09-22", "date_type": "published", "publication": "Journal of Sound and Vibration", "volume": "55", "number": "2", "publisher": "Elsevier", "pagerange": "225-243", "id_number": "CaltechAUTHORS:20101214-073952475", "issn": "0022-460X", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20101214-073952475", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "other_numbering_system": { "items": [ { "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "doi": "10.1016/0022-460X(77)90596-X", "resource_type": "article", "pub_year": "1977", "author_list": "Marble, F. E. and Candel, S. M." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/tfn80-39y50", "eprint_id": 21339, "eprint_status": "archive", "datestamp": "2023-08-19 10:52:39", "lastmod": "2023-10-20 23:57:19", "type": "article", "metadata_visibility": "show", "creators": { "items": [ { "id": "Cumpsty-N-A", "name": { "family": "Cumpsty", "given": "N. A." } }, { "id": "Marble-F-E", "name": { "family": "Marble", "given": "F. E." } } ] }, "title": "Core noise from gas turbine exhausts", "ispublished": "pub", "full_text_status": "public", "note": "\u00a9 1977 Published by Elsevier Ltd. Received 10 October 1974, and in revised frm 27 May 1977. This work has been heavily dependent on the co-operation of the aeronautics industry.\nThe authors wish to thank Rolls-Royce Limited, for aerodynamic and noise data for the Spey 512 and Olympus 593, Pratt and Whitney Aircraft for aerodynamic data on the\nJT8D, and the Boeing Commercial Airplane Company for noise measurements from the\nJT8D. They would in particular like to express their gratitude to R. R. Dils of Pratt and Whitney Aircraft whose guidance on combustion chamber behaviour was invaluable.", "abstract": "There is abundant evidence to show that the exhaust noise from gas turbines contains\ncomponents which exceed the jet mixing noise at low jet velocities. This paper describes\nresults of a theory developed to calculate the acoustic power produced by tempetature\nfluctuations from the combustor entering the turbine. With the turbine Mach numbers and\nflow directions at blade mid-height, and a typical value for the fluctuation in temperature,\nas parameters it has been possible to predict the acoustic power due to this mechanism for\nthree different engines. In all three cases the agreement with measurements of acoustic power\nat low jet velocities is very good. Similarly, based on a measured spectrum of the temperature\nfluctuation, the prediction of the acoustic power spectrum agrees quite well with that\nmeasured.", "date": "1977-09-22", "date_type": "published", "publication": "Journal of Sound and Vibration", "volume": "54", "number": "2", "publisher": "Elsevier", "pagerange": "297-309", "id_number": "CaltechAUTHORS:20101214-073031680", "issn": "0022-460X", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20101214-073031680", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "other_numbering_system": { "items": [ { "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "doi": "10.1016/0022-460X(77)90031-1", "resource_type": "article", "pub_year": "1977", "author_list": "Cumpsty, N. A. and Marble, F. E." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/k89f0-pfd09", "eprint_id": 21293, "eprint_status": "archive", "datestamp": "2023-08-19 10:24:03", "lastmod": "2023-10-20 23:55:09", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } }, { "id": "Broadwell-J-E", "name": { "family": "Broadwell", "given": "James E." } } ] }, "title": "The Coherent Flame Model for Turbulent Chemical Reactions", "ispublished": "unpub", "full_text_status": "public", "note": "\u00a9 1977, January, Other Information: Prepared in cooperation with TRW Defense and Space Systems Group, Redondo Beach, Calif. Rept. no. TRW-29314-6001-RU-00. U.S. government authored or collected reports written by Purdue Univ. Lafayette in project SQUIDHEADQUARTERS. Final rept. 1 Mar 1975-31 Jan 1977. The authors thank F. E. Fendell and D. Haflinger for making this modification and for obtaining the computer results that are presented.\n\nAccepted Version - 247_Marble_FE_1977.pdf
", "abstract": "A description of the turbulent diffusion flame is proposed in which the flame structure is composed of a distribution of laminar diffusion flame elements, whose thickness is small in comparison with the large eddies. These elements retain their identity during the flame development; they are strained in their own plane by the gas motion, a process that not only extends their surface area, but also establishes the rate at which a flame element consumes the reactants. Where this flame stretching process has produced a high flame surface density, the flame area per unit volume, adjacent flame elements may consume the intervening reactant, thereby annihilating both flame segments. This is the flame shortening mechanism which, in balance with the flame stretching process, establishes the local level of the flame density. The consumption rate of reactant is then given simply by the product of the local flame density and the reactang consumption rate per unit area of flame surface. The proposed description permits a rather complete separation of the turbulent flow structure, on one hand, and the flame structure, on the other, and in this manner permits the treatment of reactions with complex chemistry with a minimum of added labor. The structure of the strained laminar diffusion flame may be determined by analysis, numerical computation, and by experiment without significant change to the model.", "date": "1977-01", "date_type": "published", "publisher": "Project SQUID (Purdue University)", "id_number": "CaltechAUTHORS:20101210-105056861", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20101210-105056861", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "Department of Energy (DOE)", "grant_number": "N0001475C1143" }, { "agency": "Project SQUID", "grant_number": "4965-52" }, { "agency": "Project SQUID", "grant_number": "8960-18" } ] }, "other_numbering_system": { "items": [ { "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "primary_object": { "basename": "247_Marble_FE_1977.pdf", "url": "https://authors.library.caltech.edu/records/k89f0-pfd09/files/247_Marble_FE_1977.pdf" }, "resource_type": "monograph", "pub_year": "1977", "author_list": "Marble, Frank E. and Broadwell, James E." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/36jdn-22095", "eprint_id": 21405, "eprint_status": "archive", "datestamp": "2023-08-19 09:18:44", "lastmod": "2023-10-21 00:00:47", "type": "article", "metadata_visibility": "show", "creators": { "items": [ { "id": "Carrier-G-F", "name": { "family": "Carrier", "given": "G. F." } }, { "id": "Fendell-F-E", "name": { "family": "Fendell", "given": "F. E." } }, { "id": "Marble-F-E", "name": { "family": "Marble", "given": "F. E." } } ] }, "title": "The Effect of Strain Rate on Diffusion Flames", "ispublished": "pub", "full_text_status": "public", "note": "\u00a9 1975 Society for Industrial and Applied Mathematics. Received by the editors March 19, 1974. This work was supported in part by: Project SQUID, supported by the Office of Naval Research, Department of the Navy, under Contract N00014-67-A-0226-0005, NR-098-038 (F.E.F.); Office of Naval Research Contract N00014-67-A-0298-0033 and\nNational Science Foundation Contract NSF-GP-34723 (G.F.C.). Presented by invitation at an International\nSymposium on Modern Developments in Fluid Dynamics in Honor of the 70th Birthday of Sydney Goldstein held at Haifa, Israel, December 16-23, 1973. The authors are very grateful to Dr. J. Eugene Broadwell of TRW Systems, Redondo Beach, California, for advice, criticism and encouragement.\n\nPublished - 226_Carrier_GF_1975.pdf
", "abstract": "Several steady state and time-dependent solutions to the compressible conservation laws describing direct one-step near-equilibrium irreversible exothermic burning of initially unmixed gaseous reactants, with Lewis-Semenov number unity, are presented. The quantitative investigation first establishes the Burke-Schumann thin-flame solution using the Shvab-Zeldovich formulation. Real flames do not have the indefinitely thin reaction zone associated with the Burke-Schumann solution. Singular perturbation analysis is used to provide a modification of the thin-flame solution which includes a more realistic reaction zone of small but finite thickness. The particular geometry emphasized is the un bounded counterflow such that there exists a spatially constant rate of strain along the flame. While the solutions\nfor diffusion flames under a finite tangential strain rate may be of interest in and of themselves for laminar flow, the problems are motivated by the authors' belief that they are pertinent to the study of diffusion-flame burning in transitional and turbulent shear flows.", "date": "1975-03", "date_type": "published", "publication": "SIAM Journal on Applied Mathematics", "volume": "28", "number": "2", "publisher": "Society for Industrial and Applied Mathematics", "pagerange": "463-500", "id_number": "CaltechAUTHORS:20101216-133642630", "issn": "0036-1399", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20101216-133642630", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "Office of Naval Research (ONR)", "grant_number": "N00014-67-A-0226-0005" }, { "agency": "Office of Naval Research (ONR)", "grant_number": "NR-098-038" }, { "agency": "Office of Naval Research (ONR)", "grant_number": "N00014-67-A-0298-0033" }, { "agency": "NSF", "grant_number": "GP-34723" } ] }, "other_numbering_system": { "items": [ { "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "doi": "10.1137/0128038", "primary_object": { "basename": "226_Carrier_GF_1975.pdf", "url": "https://authors.library.caltech.edu/records/36jdn-22095/files/226_Carrier_GF_1975.pdf" }, "resource_type": "article", "pub_year": "1975", "author_list": "Carrier, G. F.; Fendell, F. E.; et el." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/vva2e-1yd89", "eprint_id": 21404, "eprint_status": "archive", "datestamp": "2023-08-19 09:11:11", "lastmod": "2023-10-21 00:00:45", "type": "article", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } }, { "id": "Candel-S-M", "name": { "family": "Candel", "given": "Sebastien M." } } ] }, "title": "Acoustic Attenuation in Fans and Ducts by Vaporization of Liquid Droplets", "ispublished": "pub", "full_text_status": "public", "note": "\u00a9 1975, by the American Institute of Aeronautics and Astronautics, and reprinted by permission of the copyright owner. Presented as Paper 74-526 at the AIAA 7th Fluid and Plasma Dynamics Conference, Palo Alto, California, June 17-19, 1974; submitted June 24, 1974; revision received November 5, 1974. Supported by U.S. Air Force Grant AFOSR-71 2068.\n\nPublished - 225_Marble_FE_1975.pdf
", "abstract": "A cloud of small water droplets in saturated air attenuates acoustic disturbances by viscous drag, heat transfer,\nand vapor exchange with the ambient gas. The viscous and heat transfer phenomena attenuate at frequencies\nabove 104 Hz for I-J.l droplets. The processes associated with phase exchange attenuate at a much lower frequency\nthat may he controlled by choice of the liquid mass fraction. The strength of this attenuation is proportional to the mass of water vapor in the air, a factor controlled by air temperature. For plane waves, the attenuation\nmagnitude e~ceeds 5 db!m ~t a temperature of 25\u00b0C with a cloud of 0.7 J.l radius droplets constituting 1 % of the\ngas mass. ThiS attenuation mcreases to more than 7 dbjm at frequencies above 1000 Hz where viscous and heat\ntransfer mechanisms contribute significantly. The attenuation of higher order duct modes is strongly increased over the above values, similarly to the attenuation by duct lining. When the droplet cloud occupies only a fraction of the duct height close to the walls, the droplet clond may be up to twice as elfective as the uniform cloud, and a significant saving is possible in the water required to saturate the air and furnish the water droplets.", "date": "1975", "date_type": "published", "publication": "AIAA Journal", "volume": "13", "number": "5", "publisher": "AIAA", "pagerange": "634-639", "id_number": "CaltechAUTHORS:20101216-132206855", "issn": "0001-1452", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20101216-132206855", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U.S. Air Force", "grant_number": "AFOSR-71 2068" } ] }, "other_numbering_system": { "items": [ { "id": "0001-1452", "name": "AIAA" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "doi": "10.2514/3.49777", "primary_object": { "basename": "225_Marble_FE_1975.pdf", "url": "https://authors.library.caltech.edu/records/vva2e-1yd89/files/225_Marble_FE_1975.pdf" }, "resource_type": "article", "pub_year": "1975", "author_list": "Marble, Frank E. and Candel, Sebastien M." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/my18d-yqk54", "eprint_id": 22073, "eprint_status": "archive", "datestamp": "2023-08-19 09:11:20", "lastmod": "2023-10-23 15:39:37", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } } ] }, "title": "Response of a nozzle to an entropy disturbance example of thermodynamically unsteady aerodynamics", "ispublished": "unpub", "full_text_status": "public", "note": "\u00a9 1975.\n\nSubmitted - 296_Marble_FE_1975.pdf
", "abstract": "The larger number of problems that qualify as unsteady aerodynamics\nrelate to non-uniform motion of surfaces -- such as pitching of\nairfoils -- or the correspondingly non-uniform motion of a fluid about a\nsurface -- such as a gust passing over an airfoil. Experiment and analysis\nconcerning these problems aims to determine the non-steady forces\nor surface stresses on the object. These may be thought of as \"kinematically\" non-steady problems. Another class of problems presents itself\nwhen the undisturbed gas stream temperature (or density) is non-steady\nalthough the velocity and pressure are steady; such non-uniformities are\nassociated with entropy variations from point to point of the stream. In a\nlocally adiabatic flow these entropy variations are transported with the\nstream, and when a fixed boundary -- such as an airfoil -- is encountered,\nthe flow field undergoes a non-steady change because the density variations\nalter the pressure field -- or the stresses at the boundaries. This happens\nin spite of the fact that the undisturbed free -stream velocity field and the\nsurface boundaries of the flow are independent of time. A gas turbine blade, for example, will experience a time-dependent load simply because\nof temperature fluctuations in the combustion products flowing over it, although\nthe angle of attack is independent of time. We shall call these\n\"thermodynamically\" unsteady flows in contrast with the more familiar\nkinematically unsteady flows.", "date": "1975", "date_type": "published", "publisher": "Caltech Library", "id_number": "CaltechAUTHORS:20110208-105530510", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20110208-105530510", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "other_numbering_system": { "items": [ { "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "primary_object": { "basename": "296_Marble_FE_1975.pdf", "url": "https://authors.library.caltech.edu/records/my18d-yqk54/files/296_Marble_FE_1975.pdf" }, "resource_type": "monograph", "pub_year": "1975", "author_list": "Marble, Frank E." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/mhvb2-km066", "eprint_id": 21895, "eprint_status": "archive", "datestamp": "2023-08-19 08:41:33", "lastmod": "2024-01-13 00:09:04", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Cumpsty-N-A", "name": { "family": "Cumpsty", "given": "Nicholas A." } }, { "id": "Marble-F-E", "name": { "family": "Marble", "given": "F. E." } } ] }, "title": "The generation of noise by the fluctuations in gas temperature into a turbine", "ispublished": "unpub", "full_text_status": "public", "note": "\u00a9 1974, The authors wish to thank Dr. D.S. Whitehead for his\nhelp in discussing some aspects of this work, and in particular for his assistance with the method of solution.\nThe help of Drs. R.R. Dils and E.M. Greitzer of Pratt\nand Whitney aircraft is greatly appreciated.\n\nAccepted Version - 259_Cumpsty_NA_1974.pdf
", "abstract": "An actuator disc analysis is used to calculate the pressure\nfluctuations produced by the convection of temperature\nfluctuations (entropy waves) into one or more rows of blades.\nThe perturbations in pressure and temperature must be small,\nbut the mean flow deflection and acceleration are generally\nlarge. The calculations indicate that the small temperature\nfluctuations produced by combustion chambers are sufficient\nto produce large amounts of acoustic power.\nAlthough designed primarily to calculate the effect of\nentropy waves, the method is more general and is able to\npredict the pressure and vorticity waves generated by\nupstream or downstream going pressure waves or by vorticity\nwaves impinging on blade rows.", "date": "1974", "date_type": "published", "publisher": "Caltech Library", "id_number": "CaltechAUTHORS:20110126-092110939", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20110126-092110939", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "other_numbering_system": { "items": [ { "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "primary_object": { "basename": "259_Cumpsty_NA_1974.pdf", "url": "https://authors.library.caltech.edu/records/mhvb2-km066/files/259_Cumpsty_NA_1974.pdf" }, "resource_type": "monograph", "pub_year": "1974", "author_list": "Cumpsty, Nicholas A. and Marble, F. E." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/prxwz-qvr95", "eprint_id": 21365, "eprint_status": "archive", "datestamp": "2023-08-19 08:11:20", "lastmod": "2023-10-20 23:58:46", "type": "article", "metadata_visibility": "show", "creators": { "items": [ { "id": "Quan-V", "name": { "family": "Quan", "given": "Victor" } }, { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } }, { "id": "Kliegel-J-R", "name": { "family": "Kliegel", "given": "James R." } } ] }, "title": "Nitric oxide formation in turbulent diffusion flames", "ispublished": "pub", "full_text_status": "restricted", "note": "\u00a9 1973 Combustion Institute, Published by Elsevier B.V. Available online 5 May 2007. The computer programming was performed by Mr. Robert L. Peters. The study was supported, in part, by Southern California Edison Company. Reprinted from Fourteenth Symposium (International) On Combustion.", "abstract": "Combustion and NO formation are investigated in the turbulent mixing region between\nparallel fuel and oxidant streams. Chemical reactions are divided into two classes: (i) the fast,\ndiffusion-limited combustion reaction, and (ii) the relatively slow, rate-limited NO formation.\nFor the fast reaction, the turbulent mixing zone contains fuel, oxidant, and reaction products.\nThe formation of NO is calculated separately as a trace species, since it has negligible effect\non the flowfield.\nTransport of momentum, enthalpy, and chemical species is calculated, using a mixing-length\ntheory. Because NO generation is highly temperature sensitive, the history of combustion\nproduct gases, subsequent to their formation, is decisive in determining the total NO production.\nUpper and lower bounds on NO production are obtained by considering that: (i) the combustion\nproducts remain undiluted and intact in the form of eddies as the turbulent field\ntransports them throughout the mixing layer, and (ii) the combustion products are locally\nmixed with cool oxidizer or fuel. These yield upper and lower limits, respectively.\nThe time-averaged velocity, temperature, and concentrations of fuel, oxidant, products,\nand NO distributions, are illustrated. Molecular mixing of turbulent eddies is shown to have\na great influence on the amount of NO formed, although its effect on the time-averaged fluid\nproperties is negligible. For a sample problem, the NO concentration obtained by assuming\ncomplete local molecular mixing is nearly an order-of-magnitude lower than the value predicted\nfor no mixing.", "date": "1973", "date_type": "published", "publication": "Symposium (International) on Combustion", "volume": "14", "number": "1", "publisher": "Elsevier", "pagerange": "851-860", "id_number": "CaltechAUTHORS:20101214-141112621", "issn": "0082-0784", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20101214-141112621", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "Southern California Edison Company" } ] }, "other_numbering_system": { "items": [ { "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "doi": "10.1016/S0082-0784(73)80078-5", "resource_type": "article", "pub_year": "1973", "author_list": "Quan, Victor; Marble, Frank E.; et el." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/7w1b7-kvd85", "eprint_id": 21456, "eprint_status": "archive", "datestamp": "2023-08-19 07:24:36", "lastmod": "2023-10-21 00:03:20", "type": "article", "metadata_visibility": "show", "creators": { "items": [ { "id": "Shankar-P-N", "name": { "family": "Shankar", "given": "P. N." } }, { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } } ] }, "title": "Kinetic Theory of Transient Condensation and Evaporation at a Plane Surface", "ispublished": "pub", "full_text_status": "public", "note": "\u00a9 1971 American Institute of Physics. Received 29 April 1970; final manuscript received 22 September 1970. This work was performed with the financial support\nof the Aerospace Research Laboratories,\nWright-Patterson Air Force Base, Contract No.\nF33615-69-C-1069.\n\nPublished - 206_Shankar_PN_1971.pdf
", "abstract": "The phenomenon of transient condensation onto, or evaporation from, a liquid sheet in contact\nwith its pure vapor is treated from a kinetic theory viewpoint. The Maxwell moment method is used\nto formulate the detailed transient problem. A steady surface mass flux rate exists for times large in\ncomparison with the collision time, that is, in the continuum regime, and explicit formulas are given\nfor this limit. The complete gasdynamic field, however, is nonsteady for all times. The calculations are\ncarried out utilizing four moments, and the effects of incorporating additional moments are negligible.\nFinally, the analysis is extended to incorporate imperfect mass and temperature accommodation.\nExamination of the transient solution and a matched asymptotic \"quasisteady\" solution shows that\nthe gasdynamic field consists of a diffusion process near the liquid surface coupled through an expansion\nor compression wave to the constant far field state.", "date": "1971-03", "date_type": "published", "publication": "Physics of Fluids", "volume": "14", "number": "3", "publisher": "American Institute of Physics", "pagerange": "510-516", "id_number": "CaltechAUTHORS:20101220-151620237", "issn": "1070-6631", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20101220-151620237", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "Aerospace Research Laboratories, Wright-Patterson Air Force", "grant_number": "F33615-69-C-1069" } ] }, "other_numbering_system": { "items": [ { "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "doi": "10.1063/1.1693464", "primary_object": { "basename": "206_Shankar_PN_1971.pdf", "url": "https://authors.library.caltech.edu/records/7w1b7-kvd85/files/206_Shankar_PN_1971.pdf" }, "resource_type": "article", "pub_year": "1971", "author_list": "Shankar, P. N. and Marble, Frank E." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/r094r-b2s22", "eprint_id": 8605, "eprint_status": "archive", "datestamp": "2023-08-22 00:01:24", "lastmod": "2023-10-16 21:35:11", "type": "article", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } }, { "id": "Wooten-D-C", "name": { "family": "Wooten", "given": "David C." } } ] }, "title": "Sound attenuation in a condensing vapor", "ispublished": "pub", "full_text_status": "public", "note": "\u00a91970 American Institute of Physics. \n\nReceived 24 April 1970. \n\nThis work was performed with the financial support of the Aerospace Research Laboratories, Wright-Patterson Air Force Base, Contract F33615-69-C-1069.", "abstract": "The process of acoustic attenuation in a condensing medium is investigated using a continuumlike formulation that allows for the phase-exchange process. The liquid phase is assumed sufficiently disperse so that the field may be treated as a continuum. The elementary relaxation processes associated with droplet velocity, temperature, and vapor pressure equilibration are equally important in determining the attenuation when vapor, liquid, and inert gas mass fractions are of the same order. When the liquid mass fraction is small, however, a strong attenuation band appears at low frequencies. This attenuation process involves a coupled relaxation process in which heat transfer and vaporization processes combine to change the temperature of the relatively large gas mass. This attenuation band (i) centers on a frequency that is proportional to the concentration of liquid, and (ii) has a maximum value that varies directly as the concentration of condensible vapor and roughly as the square of the latent heat of vaporization. When the concentrations of liquid and condensible vapor are both small, the low-frequency attenuation band is nearly isolated and may be described in a convenient analytical manner.", "date": "1970-11", "date_type": "published", "publication": "Physics of Fluids", "volume": "13", "number": "11", "publisher": "Physics of Fluids", "pagerange": "2657-2664", "id_number": "CaltechAUTHORS:MARpof70", "issn": "0031-9171", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:MARpof70", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "other_numbering_system": { "items": [ { "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "doi": "10.1063/1.1692847", "primary_object": { "basename": "MARpof70.pdf", "url": "https://authors.library.caltech.edu/records/r094r-b2s22/files/MARpof70.pdf" }, "resource_type": "article", "pub_year": "1970", "author_list": "Marble, Frank E. and Wooten, David C." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/a5gkn-s1p04", "eprint_id": 22084, "eprint_status": "archive", "datestamp": "2023-08-19 07:09:52", "lastmod": "2023-10-23 15:40:00", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Serdengecti-S", "name": { "family": "Serdengecti", "given": "Sedat" } }, { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } } ] }, "title": "A theory of two-dimensional airfoils with strong inlet flow on the upper surface", "ispublished": "unpub", "full_text_status": "public", "note": "This final report on Contract F33615-68-C-1013 covers work carried out at The California Institute of Technology from 1 November 1967 to 31 December 1969. This research was supported in part under the ARL In-House Independent Laboratory Research Funds. The Project Engineer monitoring this contract was Dr. K. S. Nagaraja, Hypersonic Research Laboratory, ARL. Technical contributions to\nthe work were made by Dr. S. Serdengecti, Dr. W. D. Rannie,\nDr. F. E. C. Culick, Dr. E. E. Zukoski and the Principal Investigator, Dr. Frank E. Marble.\n\nPublished - 312_Serdengecti_Marble_1970.pdf
", "abstract": "The two-dimensional theory of airfoils with arbitrarily strong inlet\nflow into the upper surface was examined with the aim of developing a thin-airfoil\ntheory which is valid for this condition. Such a theory has, in fact,\nbeen developed and reduces uniformly to the conventional thin-wing theory\nwhen the inlet flow vanishes. The integrals associated with the arbitrary\nshape, corresponding to the familiar Munk integrals, are somewhat more\ncomplex but not so as to make calculations difficult.\nTo examine the limit for very high ratios of inlet to free-stream\nvelocity, the theory of the Joukowski airfoil was extended to incorporate\nan arbitrary inlet on the upper surface. Because this calculation is exact,\nphenomena observed in the limit cannot be attributed to the linearized calculation. These results showed that airfoil theory, in the conventional sense,\nbreaks down at very large ratios of inlet to free-stream velocity. This\noccurs where the strong induced field of the inlet dominates the free-stream\nflow so overwhelmingly that the flow no longer leaves the trailing edge but\nflows toward it. Then the trailing edge becomes, in fact a leading edge\nand the Kutta condition is physically inapplicable. For the example in this\nwork, this breakdown occurred at a ratio of inlet to free-stream velocity\nof about 10. This phenomena suggests that for ratios in excess of the\ncritical value, the flow separates from the trailing edge and the circulation\nis dominated by conditions at the edges of the inlet.", "date": "1970-08", "date_type": "published", "publisher": "Caltech Library", "id_number": "CaltechAUTHORS:20110208-150155345", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20110208-150155345", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "ARL In-House Independent Laboratory Research Funds" } ] }, "other_numbering_system": { "items": [ { "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "primary_object": { "basename": "312_Serdengecti_Marble_1970.pdf", "url": "https://authors.library.caltech.edu/records/a5gkn-s1p04/files/312_Serdengecti_Marble_1970.pdf" }, "resource_type": "monograph", "pub_year": "1970", "author_list": "Serdengecti, Sedat and Marble, Frank E." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/fp41b-fs587", "eprint_id": 21451, "eprint_status": "archive", "datestamp": "2023-08-19 06:56:46", "lastmod": "2023-10-21 00:03:07", "type": "article", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } } ] }, "title": "Dynamics of Dusty Gases", "ispublished": "pub", "full_text_status": "restricted", "note": "\u00a9 1970 Annual Reviews.", "abstract": "This review deals with a certain restricted portion of the mechanics of heterogeneous media. The volume fraction of the solid-particle or droplet cloud is considered to be so small that the interaction between individual particles may be neglected or highly simplified. This limitation applies to the individual flow fields about the particles as well as to collisions, and to heat and mass transfer as well as to momentum exchange between phases. Under this circumstance, the problem of detailed transport processes between particles and gas may be treated independently of the complete dynamical problem, and this aspect, being a study of its own, will be suppressed to a considerable extent here. There are problems, such as the impact\nof particles on walls, the concentration separation in boundary layers or pipe flow, in which the distortion of the particle flow field due to a solid wall or another particle is the central physical issue. These problems therefore lie outside the scope of the review. On the other hand, the structure of shock waves, sound attenuation, and many flow-field problems can be treated within our present restrictions. The basic equations and exchange processes will be introduced first, together with the physical parameters that indicate the relative importance of the particle cloud and the limitations of the dusty-gas concept. Then several different problems will be discussed that lead to some of the significant results in the field and illustrate analytical techniques that have proven useful.", "date": "1970-01", "date_type": "published", "publication": "Annual Review of Fluid Mechanics", "volume": "2", "publisher": "Annual Reviews", "pagerange": "397-446", "id_number": "CaltechAUTHORS:20101220-141547545", "issn": "0066-4189", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20101220-141547545", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "other_numbering_system": { "items": [ { "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "resource_type": "article", "pub_year": "1970", "author_list": "Marble, Frank E." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/qa99p-1t908", "eprint_id": 21984, "eprint_status": "archive", "datestamp": "2023-08-19 06:56:51", "lastmod": "2023-10-23 15:34:37", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Zukoski-E-E", "name": { "family": "Zukoski", "given": "Edward E." } }, { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } }, { "id": "Ranie-W-D", "name": { "family": "Ranie", "given": "W. Duncan" } } ] }, "title": "Large building fires - experiments and analysis", "ispublished": "unpub", "full_text_status": "public", "note": "\u00a9 1970.\nFinal Report.\nContract CST-902-5-69.\nU. S. Department of Commerce\nNational Bureau of Standards.\n\nPublished - 208_Zukoski_EE_1970.pdf
", "abstract": "Because of its inherent complexity and detail, as well as its rather tenuous relationship to existing combustion theory, the propagation of uncontrolled fires in large buildings remains one of the unsolved problems facing our cities. On October 13, 1969 (see Appendix), a fire in a\nLos Angeles apartment claimed the lives of eight people and sent more than a score to the hospital for various degrees of burn and smoke inhalation. As the fire developed, flames spread quickly up the main stairwell, blocking exits from apartment units, forcing some to jump from upper floors. Within a matter of minutes, all three floors were so involved in fire that normal escape was impossible.\nOur lack of quantitative knowledge about the propagation of building fire has a more widespread effect than such disasters. It is a major factor in preserving archaic and inappropriate building codes; it places a severe\nlimit on architectural innovation because fire hazards in novel structures cannot be evaluated quantitatively. This is a truly serious restriction in an era where low-cost multiple dwellings are in urgent need.", "date": "1970-01", "date_type": "published", "publisher": "NTIS", "id_number": "CaltechAUTHORS:20110203-131719678", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20110203-131719678", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "other_numbering_system": { "items": [ { "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "primary_object": { "basename": "208_Zukoski_EE_1970.pdf", "url": "https://authors.library.caltech.edu/records/qa99p-1t908/files/208_Zukoski_EE_1970.pdf" }, "resource_type": "monograph", "pub_year": "1970", "author_list": "Zukoski, Edward E.; Marble, Frank E.; et el." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/1y97c-ae981", "eprint_id": 21487, "eprint_status": "archive", "datestamp": "2023-08-19 06:16:30", "lastmod": "2023-10-21 00:04:52", "type": "article", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } } ] }, "title": "Some Gasdynamic Problems in the Flow of Condensing Vapors", "ispublished": "pub", "full_text_status": "public", "note": "\u00a9 Pergamon Press 1969. Received 22 December 1968. This research was supported, in part, by the Aerospace\nResearch Laboratories, Wright-Patterson Air Force Base,\nunder contract AF33(615)-3587.\n\nPublished - 201_Marble_FE_1969.pdf
", "abstract": "Some Gasdynamic Problems in the Flow of Condensing Vapors. The general problem of the flow\nof a wet vapor, with or without an inert diluent is formulated under the assumption that the liquid phase\nis finely divided and dispersed throughout the gaseous component in droplets whose radii are nearly\nconstant in any local region. The processes of momentum transfer, heat transfer between phases are\nassumed to take place according to Stokes law and Nusselt number of unity, respectively. The mass transfer\nprocess is treated as diffusion governed in the presence of an inert diluent and kinetic governed for two\nphases of a pure substance.\nThe physical understanding of such problems, in contrast with those of conventional gas dynamics,\nrests largely in the role played by the relaxation times or equilibration lengths associated with these three\nprocesses. Consequently, both simple and coupled relaxation processes are examined rather carefully by\nspecific examples. Subsequently, the problem of near-equilibrium flow in a nozzle with phase change is solved\nunder the small-slip approximation. The structure of the normal shock in a pure substance is investigated\nand reveals three rather distinct zones: the gasdynamic shock, the vapor relaxation zone, and the thermal\nand velocity equilibration zone. The three-dimensional steady flow of the two-phase condensing continuum\nis formulated according to first order perturbation theory, and the structure of waves in such supersonic flow\nis examined. Finally, the attenuation of sound in fogs is formulated and solved accounting for the important\neffects of phase change as well as the viscous damping and heat transfer which have been included in previous\nanalyses.", "date": "1969", "date_type": "published", "publication": "Astronautica Acta", "volume": "14", "number": "6", "publisher": "Pergamon Press", "pagerange": "585-613", "id_number": "CaltechAUTHORS:20101221-140000406", "issn": "0004-6205", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20101221-140000406", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "Wright-Patterson Air Force Base", "grant_number": "AF33(615)-3587" } ] }, "other_numbering_system": { "items": [ { "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "primary_object": { "basename": "201_Marble_FE_1969.pdf", "url": "https://authors.library.caltech.edu/records/1y97c-ae981/files/201_Marble_FE_1969.pdf" }, "resource_type": "article", "pub_year": "1969", "author_list": "Marble, Frank E." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/gz0k7-20g34", "eprint_id": 21498, "eprint_status": "archive", "datestamp": "2023-08-19 05:46:28", "lastmod": "2024-01-13 00:08:20", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } } ] }, "title": "The role of approximate analytical results in the study of two-phase flow in nozzle", "ispublished": "unpub", "full_text_status": "public", "note": "Reprinted from the Proceedings of the Air Force Rocket Propulsion Laboratory Two-Phase Flow Conference 15 - 16 March 1967 Norton Air Force Base, San Bernardino, California\nEditors: L. J. Delaney, R. F. Hoglund, and 1/Lt P. W. Smith AFRPL-TR-67-223, Vol. II August 1967\n\nReprint - 188_Marble_FE_1967.pdf
", "abstract": "The small slip approxitnation to the theory of two-phase flow in rocket nozzles is reviewed to show that the inaccuracies associated with drag and heat transfer laws, and those associated with the fundamental approximation,\nare independent and that the former may be removed algebraic1y. Selected applications ofthe approximate theory are discussed to indicate that these stress the nature of the dependence of the results upon the relevant physical parameters and the possible consequence of scaling\nlaws, rather than numerical accuracy too often limited by inaccurate initial data. It is suggested that approximate analytical results may offer much more assistance to the rocket engineer than has yet been used to advantage.", "date": "1967-08", "date_type": "published", "publisher": "Caltech Library", "id_number": "CaltechAUTHORS:20101222-101345306", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20101222-101345306", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "other_numbering_system": { "items": [ { "id": "67-233", "name": "AFRPL-TR" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "corp_creators": { "items": [ "Air Force Rocket Propulstion Lab. Edwards AFB CA" ] }, "primary_object": { "basename": "188_Marble_FE_1967.pdf", "url": "https://authors.library.caltech.edu/records/gz0k7-20g34/files/188_Marble_FE_1967.pdf" }, "resource_type": "monograph", "pub_year": "1967", "author_list": "Marble, Frank E." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/30246-2c925", "eprint_id": 21492, "eprint_status": "archive", "datestamp": "2023-08-19 05:33:14", "lastmod": "2023-10-21 00:05:02", "type": "article", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } } ] }, "title": "Droplet Agglomeration in Rocket Nozzles Caused by Particle Slip and Collision", "ispublished": "pub", "full_text_status": "public", "note": "\u00a9 Pergamon Press. Received 14 June 1966. Subsequent to submitting the present paper, a numerical calculation of agglomeration in rocket nozzles was presented by CROWE, C. T. and WILLOUGHBY, P. G., A mechanism for particle growth in a rocket nozzle, AIAA J14, 1677-78 (1966).\n\nPublished - 182_Marble_FE_1966.pdf
", "abstract": "Droplet Agglomeration in Rocket Nozzles Caused by Particle Slip and Collision. The development\nof the particle mass spectrum in a rocket nozzle is investigated under the assumption that droplet growth\nby collision and agglomeration is the dominant mechanism subsequent to initial appearance of particles\nin the rocket chamber. Collisions are calculated on the basis oflinearized particle slip theory and a spectral\nintegral equation is derived describing the development of particle mass spectrum during the flow process\nalong the nozzle. This agglomeration process continues until the droplet temperature falls below the freezing\npoint of the material.\nA solution is obtained for the approximate growth in the average particle size during the expansion\nprocess. The results show that, according to this model, the particle size is strongly dependent on the\ninitial pressure in the rocket chamber and is independent of nozzle geometry.\nThese results suggest that the collision-agglomeration process is at least one of the critical factors that\naccounts for the size of solid particles in rocket exhausts.", "date": "1967", "date_type": "published", "publication": "Astronautica Acta", "volume": "13", "number": "2", "publisher": "Pergamon Press", "pagerange": "159-166", "id_number": "CaltechAUTHORS:20101222-073250075", "issn": "0004-6205", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20101222-073250075", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "other_numbering_system": { "items": [ { "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "primary_object": { "basename": "182_Marble_FE_1966.pdf", "url": "https://authors.library.caltech.edu/records/30246-2c925/files/182_Marble_FE_1966.pdf" }, "resource_type": "article", "pub_year": "1967", "author_list": "Marble, Frank E." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/7gkvs-8x881", "eprint_id": 9263, "eprint_status": "archive", "datestamp": "2023-08-21 23:26:06", "lastmod": "2023-10-16 22:02:38", "type": "article", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } } ] }, "title": "Reply to comments by S. L. Soo", "ispublished": "pub", "full_text_status": "public", "note": "\u00a9 1965 American Institute of Physics.\nReceived 10 March 1965.\n\nPublished - MARpof65.pdf
", "abstract": "If one takes due regard for the condition under which my collision model is valid, explicitly stated by Eq. (15), Ref. 1, the difficulties experienced by Soo(2) will not arise.", "date": "1965-09", "date_type": "published", "publication": "Physics of Fluids", "volume": "8", "number": "9", "publisher": "American Institute of Physics", "pagerange": "1753-1754", "id_number": "CaltechAUTHORS:MARpof65", "issn": "1070-6631", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:MARpof65", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "doi": "10.1063/1.1761500", "primary_object": { "basename": "MARpof65.pdf", "url": "https://authors.library.caltech.edu/records/7gkvs-8x881/files/MARpof65.pdf" }, "resource_type": "article", "pub_year": "1965", "author_list": "Marble, Frank E." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/g47jd-r8g20", "eprint_id": 10284, "eprint_status": "archive", "datestamp": "2023-08-21 23:20:08", "lastmod": "2023-10-16 22:46:46", "type": "article", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } } ] }, "title": "Mechanism of particle collision in the one-dimensional dynamics of gas-particle mixtures", "ispublished": "pub", "full_text_status": "public", "note": "\u00a9 1964 American Institute of Physics. \n\nReceived 20 February 1964. \n\nThis work was supported by the National Science Foundation Grant GP-713.\n\nPublished - MARpof64.pdf
", "abstract": "A theory is developed for the one-dimensional flow of a gas, containing solid particles of two different sizes, in which the effect of particle collisions is accounted for as well as the interaction between the particles and the gas. It is assumed that the particles behave as smooth elastic spheres, that they follow the Stokes drag law and exchange heat with the gas at a Nusselt number of unity. It is shown that there exists a range of parameters which provides that (i) the viscous flow fields about each particle do not interfere during collision, and (ii) the random velocities imparted by one collision are damped before either particle suffers another collision. Using the assumption of small particle slip, the one-dimensional flow problem is solved explicitly up to first order terms in the small slip. It is found, of course, that the tendency of collisions is to cause the two particle-slip speeds to have more nearly the same value than they would in the absence of interparticle collision. It appears that, although the physical assumptions restrict the magnitude of the interparticle forces, the model does provide the proper limit for very strong particle interaction and can conceivably be applied in this range also without gross error.", "date": "1964-08", "date_type": "published", "publication": "Physics of Fluids", "volume": "7", "number": "8", "publisher": "American Institute of Physics", "pagerange": "1270-1282", "id_number": "CaltechAUTHORS:MARpof64", "issn": "1070-6631", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:MARpof64", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "other_numbering_system": { "items": [ { "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "doi": "10.1063/1.1711372", "primary_object": { "basename": "MARpof64.pdf", "url": "https://authors.library.caltech.edu/records/g47jd-r8g20/files/MARpof64.pdf" }, "resource_type": "article", "pub_year": "1964", "author_list": "Marble, Frank E." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/q1qy6-9y416", "eprint_id": 21580, "eprint_status": "archive", "datestamp": "2023-08-19 04:32:08", "lastmod": "2023-10-21 00:09:15", "type": "article", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } } ] }, "title": "Nozzle contours for minimum particle-lag loss", "ispublished": "pub", "full_text_status": "public", "note": "\u00a9 1964, American Institute of Aeronautics and Astronautics.\nReceived June 20, 1963; revision received September 10, 1963.\n\nPublished - 152_Marble_FE_1963.pdf
", "abstract": "The flow of a gas-particle mixture through a rocket nozzle is analyzed under the approximation that the particle slip velocity is small compared with the average mixture velocity, using one-dimensional gasdynamics, the Stokes drag law, and corresponding approximations for the heat transfer between solid and gas phase. The variational problem defining the pressure distribution giving the minimum impulse loss due to particle lag is formulated and\nsolved for nozzles of prescribed mass flow, length, and of given exit pressure or area. The throat section of the optimum nozzle is considerably elongated and more gradual than that of the conventional nozzle. The velocity and temperature lags were much lower (about 1/3) in the throat region than those for the conventional nozzle. The impulse loss of the optimum nozzle was, however, reduced only about 30% below that of the conventional nozzle. It is concluded that contouring of the nozzle to improve gas-particle flow performance will result in only very modest gains. As a direct consequence, the impulse losses calculated herein for optimum nozzles can be used as a rough but convenient approximation for the impulse losses in conventional nozzles having the same area ratio or pressure ratio.", "date": "1963-12", "date_type": "published", "publication": "AIAA Journal", "volume": "1", "number": "12", "publisher": "AIAA", "pagerange": "2793-2801", "id_number": "CaltechAUTHORS:20110104-120110913", "issn": "0001-1452", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20110104-120110913", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "other_numbering_system": { "items": [ { "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "primary_object": { "basename": "152_Marble_FE_1963.pdf", "url": "https://authors.library.caltech.edu/records/q1qy6-9y416/files/152_Marble_FE_1963.pdf" }, "resource_type": "article", "pub_year": "1963", "author_list": "Marble, Frank E." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/fnwt0-m4c83", "eprint_id": 22071, "eprint_status": "archive", "datestamp": "2023-08-19 04:15:28", "lastmod": "2023-10-23 15:39:32", "type": "book_section", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } } ] }, "title": "Dynamics of a gas containing small solid particles", "ispublished": "unpub", "full_text_status": "public", "note": "\u00a9 1963 Pergamon Press.\n\nReprint - 147_Marble_FE_1963.pdf
", "abstract": "N/A", "date": "1963", "date_type": "published", "publisher": "Pergamon Press", "id_number": "CaltechAUTHORS:20110208-103139308", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20110208-103139308", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "collection": "CaltechAUTHORS", "other_numbering_system": { "items": [ { "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center", "value": "Guggenheim Jet Propulsion Center" } ] }, "primary_object": { "basename": "147_Marble_FE_1963.pdf", "url": "https://authors.library.caltech.edu/records/fnwt0-m4c83/files/147_Marble_FE_1963.pdf" }, "resource_type": "book_section", "pub_year": "1963", "author_list": "Marble, Frank E." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/n62n4-4q295", "eprint_id": 21743, "eprint_status": "archive", "datestamp": "2023-08-19 03:24:42", "lastmod": "2023-10-21 00:17:25", "type": "article", "metadata_visibility": "show", "creators": { "items": [ { "id": "Kerrebrock-J-L", "name": { "family": "Kerrebrock", "given": "Jack L." } }, { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } } ] }, "title": "Constant-temperature magneto-gasdynamic channel flow", "ispublished": "pub", "full_text_status": "public", "note": "\u00a9 1960 Institute of the Aeronautical Sciences. Received August 5, 1959.\n\nReprint - 105_Kerrebrock_JL_1959.pdf
", "abstract": "In the course of investigating boundary-layer flow in continuous\nplasma accelerators with crossed electric and magnetic\nfields, it was found advantageous to have at hand simple\nclosed-form solutions for the magneto-gas dynamic flow in the\nduct which could serve as free-stream conditions for the boundary\nlayers. Nontrivial solutions of this sort are not available at\npresent. and in fact, as in the work of Resler and Sears, the\nvariation of conditions along the flow axis must be obtained\nthrough numerical integration.\nConsequently, some simple solutions of magneto-gasdynamic\nchannel flow were sought, possessing sufficient algebraic simplicity\nto serve as free-stream boundary conditions for analytic investigations\nof the boundary layer in a physically reasonable accelerator.\nIn particular, since the cooling of the accelerator tube is likely to\nbe an important physical problem because of the high gas temperatures\nrequired to provide sufficient gaseous conductivity,\nchannel flow with constant temperature appears interesting.\nSome simple algebraic solutions for the case of a constant temperature\nplasma are developed in the following paragraphs.", "date": "1960-01", "date_type": "published", "publication": "Journal of the Aerospace Sciences", "volume": "27", "number": "1", "publisher": "Institute of the Aeronautical Sciences", "pagerange": "78-78", "id_number": "CaltechAUTHORS:20110113-074847570", "issn": "1936-9999", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20110113-074847570", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "other_numbering_system": { "items": [ { "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "primary_object": { "basename": "105_Kerrebrock_JL_1959.pdf", "url": "https://authors.library.caltech.edu/records/n62n4-4q295/files/105_Kerrebrock_JL_1959.pdf" }, "resource_type": "article", "pub_year": "1960", "author_list": "Kerrebrock, Jack L. and Marble, Frank E." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/jf5mr-vn476", "eprint_id": 21697, "eprint_status": "archive", "datestamp": "2023-08-19 03:23:31", "lastmod": "2024-01-13 00:08:43", "type": "book_section", "metadata_visibility": "show", "creators": { "items": [ { "id": "Brownlee-W-G", "name": { "family": "Brownlee", "given": "W. Grant" } }, { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } } ] }, "title": "An experimental investigation of unstable combustion in solid propellant rocket motors", "ispublished": "unpub", "full_text_status": "public", "note": "\u00a9 1960, AIAA.\n\nAccepted Version - 122_Brownlee_WG_1960.pdf
", "abstract": "Unstable combustion in solid propellant rocket motors is\ncharacterized by high frequency chamber pressure oscillations, often accompanied by changes in the mean burning rate. Experiments with casebonded, cylindrically perforated motors using a polysulfide, ammoniumperchlorate\npropellant were reproducible as a result of careful manufacturing control and extended propellant curing time. In these motors the oscillations were in the fundamental standing tangential mode and were accompanied by increases in the average burning rate. At sufficiently high pressure levels all firings were stable. Reduction of the operating\nlevel led to mild instability. A sufficient further reduction produced a sudden change to maximum instability. Continued reduction in pressure level from this point resulted in a gradual decrease in the degree of\ninstability but it could not be experimentally verified that a low pressure stable region existed. The levels at which these events took place were frequency dependent and generally increased as the tangential frequency was reduced. At a given operating leve1, the instability\nbecame less severe when the grain length was reduced below a critical value. Increasing the length above the critical value did not affect the level at which the motors became stable. The pressure levels for stability and for maximum instability moved to lower values with decreases in the propellant grain temperature in a manner not entirely accounted for by the effect of grain temperature on burning rate. Stable, mildly unstable and severely unstable operation was observed throughout the range -80\u00b0F to\n180\u00b0F. The maximum instability decreased with grain temperature.", "date": "1960", "date_type": "published", "publisher": "Academic Press", "place_of_pub": "New York", "pagerange": "455-494", "id_number": "CaltechAUTHORS:20110111-110838368", "isbn": "9781600862571", "book_title": "Solid propellant rocket research : a selection of technical papers based mainly on a symposium of the American Rocket Society", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20110111-110838368", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "other_numbering_system": { "items": [ { "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "contributors": { "items": [ { "id": "Summerfield-M", "name": { "family": "Summerfield", "given": "Martin" } } ] }, "doi": "10.2514/4.9781600862571", "primary_object": { "basename": "122_Brownlee_WG_1960.pdf", "url": "https://authors.library.caltech.edu/records/jf5mr-vn476/files/122_Brownlee_WG_1960.pdf" }, "resource_type": "book_section", "pub_year": "1960", "author_list": "Brownlee, W. Grant and Marble, Frank E." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/xemjt-3p211", "eprint_id": 22018, "eprint_status": "archive", "datestamp": "2023-08-19 02:51:33", "lastmod": "2023-10-23 15:36:51", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Rannie-W-D", "name": { "family": "Rannie", "given": "W. Duncan" } }, { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } } ] }, "title": "Unsteady flows in axial turbomachines", "ispublished": "unpub", "full_text_status": "public", "note": "\u00a9 1957. This work was performed in part with financial sponsorship of the Office of Naval Research, Contract\nNonr 220(23), NR 097-001 and in part with financial sponsorship of the Office of Scientific Research,\nU.S. Airforce, Contract AF 18(600)-1728.\n\nPublished - 94_Rannie_WD_1957.pdf
", "abstract": "Of the various unsteady flows that occur in axial turbomachines certain asymmetric disturbances, of wave length large in comparison with blade spacing, have become understood to a certain extent. These disturbances divide themselves into two categories: self-induced oscillations and forced disturbances. A special type of propagating stall appears as a self-induced disturbance; an asymmetric velocity profile introduced at the compressor inlet\nconstitutes a forced disturbance. \nBoth phenomena have been treated from a unified theoretical point of view in which the asymmetric disturbances are linearized and the blade characteristics are assumed quasi-steady. Experimental results are in essential agreement with this theory wherever the limitations of the theory are satisfied. For the self-induced disturbances and the more interesting examples of the forced disturbances, the dominant blade characteristic is the dependence of total pressure loss, rather than the turning angle, upon the local blade inlet angle.", "date": "1957", "date_type": "published", "publisher": "Caltech Library", "id_number": "CaltechAUTHORS:20110204-111252490", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20110204-111252490", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "Office of Naval Research (ONR)", "grant_number": "Nonr 220(23)" }, { "agency": "Office of Naval Research (ONR)", "grant_number": "NR 097-00" }, { "agency": "Air Force Office of Scientific Research (AFOSR)", "grant_number": "AF 18(600)-1728" } ] }, "other_numbering_system": { "items": [ { "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "primary_object": { "basename": "94_Rannie_WD_1957.pdf", "url": "https://authors.library.caltech.edu/records/xemjt-3p211/files/94_Rannie_WD_1957.pdf" }, "resource_type": "monograph", "pub_year": "1957", "author_list": "Rannie, W. Duncan and Marble, Frank E." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/q1gmz-brp53", "eprint_id": 21763, "eprint_status": "archive", "datestamp": "2023-08-19 02:46:37", "lastmod": "2023-10-21 00:18:14", "type": "article", "metadata_visibility": "show", "creators": { "items": [ { "id": "Rogers-D-E", "name": { "family": "Rogers", "given": "Don E." } }, { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } } ] }, "title": "A mechanism for high-frequency oscillation in ramjet combustors and afterburners", "ispublished": "pub", "full_text_status": "public", "note": "\u00a9 1956 American Rocket Society. Received Sept. 15, 1955.\n\nReprint - 68_Rogers_DE_1956.pdf
", "abstract": "An experimental investigation was made of the behavior\nof a small two-dimensional combustion chamber, burning\na uniform mixture of air and fuel vapor under conditions\nof high-frequency oscillation or screech. Measurements\nwere made of the limits of stable screech, the amplitude\nand frequency of pressure oscillations over a wide range of\nmixture ratio, inlet air temperature, and combustor flow\nrate. Spark schlieren photographs and high-speed motion pictures taken of the combustion process showed, in\nagreement with other investigations, that the high-frequency\noscillation is accompanied by vortices shed periodically from the flameholder lip with the same frequency as the oscillation. The following mechanism of exciting the oscillations is suggested. A mode of transverse\noscillation is excited as the result of periodic transport\nof combustible material, associated with the vortices,\ninto the hot wake of the flameholder. The vortices, in\nturn, are generated at the flameholder lips by the fluctuating transverse velocity. When the ignition time delay lies in the proper range, the phase relationship between oscillations in transverse velocity and combustion intensity is such that the oscillation is amplified.", "date": "1956-06", "date_type": "published", "publication": "Jet Propulsion", "volume": "26", "number": "6", "publisher": "American Rocket Society", "pagerange": "456-462", "id_number": "CaltechAUTHORS:20110114-111632665", "issn": "0095-8751", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20110114-111632665", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "collection": "CaltechAUTHORS", "other_numbering_system": { "items": [ { "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center", "value": "Guggenheim Jet Propulsion Center" } ] }, "primary_object": { "basename": "68_Rogers_DE_1956.pdf", "url": "https://authors.library.caltech.edu/records/q1gmz-brp53/files/68_Rogers_DE_1956.pdf" }, "resource_type": "article", "pub_year": "1956", "author_list": "Rogers, Don E. and Marble, Frank E." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/900ap-2vf91", "eprint_id": 21768, "eprint_status": "archive", "datestamp": "2023-08-19 02:44:27", "lastmod": "2023-10-21 00:18:28", "type": "article", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } } ] }, "title": "Flame theory and combustion technology", "ispublished": "pub", "full_text_status": "public", "note": "\u00a9 1956 Institute of the Aeronautical Sciences.\n\nReprint - 76_Marble_FE_1956.pdf
", "abstract": "The study of combustion processes is in a sufficiently early\nstage so that there is no strong connection between combustion theory and the technology of combustion chamber development. To clarify such a connection is the principal task of workers engaged in establishing combustion as an engineering science. The equations of aerothermochemistry are reviewed for the case in which temperature and composition gradients are small. Solutions have been obtained in very few cases and under very restrictive circumstances; most detailed considerations are restricted\nto the plane laminar flame front. The current situation\nin the theory of plane laminar flames is discussed. The few extensions that have been made to two-dimensional problems are then described. Several directions of work which would assist in establishing theoretical results approaching technological requirements appear possible.", "date": "1956-05", "date_type": "published", "publication": "Journal of the Aeronautical Sciences", "volume": "23", "number": "5", "publisher": "Institute of the Aeronautical Sciences", "pagerange": "462-468", "id_number": "CaltechAUTHORS:20110118-074645504", "issn": "1936-9956", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20110118-074645504", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "other_numbering_system": { "items": [ { "id": "76", "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "primary_object": { "basename": "76_Marble_FE_1956.pdf", "url": "https://authors.library.caltech.edu/records/900ap-2vf91/files/76_Marble_FE_1956.pdf" }, "resource_type": "article", "pub_year": "1956", "author_list": "Marble, Frank E." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/yptrk-jqv81", "eprint_id": 21811, "eprint_status": "archive", "datestamp": "2023-08-19 02:34:31", "lastmod": "2023-10-23 15:10:16", "type": "article", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } } ] }, "title": "Propagation of stall in a compressor blade row", "ispublished": "pub", "full_text_status": "public", "note": "\u00a9 1955 Institute of the Aeronautical Sciences. Received April 7, 1954. This work was performed, in part, under the financial support of the Office of Scientific Research, United States Air Force\n\nReprint - 67_Marble_FE_1955.pdf
", "abstract": "Recent experimental observations on compressors, in particular those of Rannie and Iura, have clarified some features of the phenomenon of stall propagation. Using these observations as a guide, the process of stall in an airfoil cascade has been characterized by a static pressure loss across the cascade which increases discontinuously at the stall angle, the turning angle being affected in only a minor way. Deductions from this simple model yield the essential features of stall propagation such as dependence of the extent of stalled region upon operating conditions,\nthe pressure loss associated with stall, and the angular\nvelocity of stall propagation. Using two-dimensional approximation for a stationary or rotating blade row, free from interference of adjacent blade rows, extent of the stalled region, the total pressure loss and stall propagation speed are discussed in detail for a general cascade characteristic. Employing these results, the effect of stall propagation upon the performance of a single-stage\naxial compressor is illustrated and the mechanism of entering the regime of stall propagation is discussed. The essential points of the results seem to agree with experimental evidence.", "date": "1955-08", "date_type": "published", "publication": "Journal of the Aeronautical Sciences", "volume": "22", "number": "8", "publisher": "Institute of the Aeronautical Sciences", "pagerange": "541-554", "id_number": "CaltechAUTHORS:20110119-110427631", "issn": "1936-9956", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20110119-110427631", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "Air Force Office of Scientific Research (AFOSR)" } ] }, "other_numbering_system": { "items": [ { "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "primary_object": { "basename": "67_Marble_FE_1955.pdf", "url": "https://authors.library.caltech.edu/records/yptrk-jqv81/files/67_Marble_FE_1955.pdf" }, "resource_type": "article", "pub_year": "1955", "author_list": "Marble, Frank E." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/0kjhw-vy813", "eprint_id": 21796, "eprint_status": "archive", "datestamp": "2023-08-19 02:29:45", "lastmod": "2023-10-21 00:20:07", "type": "article", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } } ] }, "title": "Servo-stabilization of low-frequency oscillations in liquid propellant rocket motors.", "ispublished": "pub", "full_text_status": "restricted", "note": "\u00a9 1955 Springer. Received: February 2, 1954.", "abstract": "Two points of view may be taken with regard to the undesirable pressure\noscillations in rocket motors which arise from instability of combustion, acoustic resonance, coupled oscillations of chamber pressure and propellant flow\nrate, as well as from more obscure sources. One is to eliminate the underlying\ncause of instability through change in mechanical design or modification of\npropellant properties; this is possible when the mechanism of instability is\nunderstood and its removal is not detrimental to rocket performance. The\nalternative is, as was demonstrated by H. S. Tsien [1], to modify the system\ndynamics by utilizing a feedback servo control which, for example, senses pressure\nfluctuations in the combustion chamber and modifies the propellant feeding\nrate at the proper frequency and phase to damp the fluctuation. Servo-stabilization\nprovides the distinct advantage that stability need not be a major\nconcern during rocket design, relying upon the feedback system to insure stable\noperation. Furthermore these concepts suggest the possibility of eliminating\nempirically an undesirable oscillation even when its basic cause is not known.", "date": "1955-01", "date_type": "published", "publication": "Zeitschrift f\u00fcr Angewandte Mathematick und Physik", "volume": "6", "number": "1", "publisher": "Springer", "pagerange": "1-35", "id_number": "CaltechAUTHORS:20110118-140949997", "issn": "0044-2275", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20110118-140949997", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "collection": "CaltechAUTHORS", "other_numbering_system": { "items": [ { "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center", "value": "Guggenheim Jet Propulsion Center" } ] }, "doi": "10.1007/BF01600733", "resource_type": "article", "pub_year": "1955", "author_list": "Marble, Frank E." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/qycd1-h1z74", "eprint_id": 17230, "eprint_status": "archive", "datestamp": "2023-08-19 02:21:30", "lastmod": "2023-10-19 23:40:21", "type": "article", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } }, { "id": "Adamson-T-C-Jr", "name": { "family": "Adamson", "given": "Thomas C., Jr." } } ] }, "title": "Ignition and combustion in a laminar mixing zone", "ispublished": "pub", "full_text_status": "public", "note": "(Reprinted from JET PROPULSION, March-April, 1954). \n\nCopyright, 1954, by the American Rocket Society, Inc., and reprinted by permission of the copyright owner. \n\nPresented at the 8th ARS National Convention, New York, N. Y., December 3, 1953. \n\nThis investigation was carried out, in part, under the financial sponsorship of the Ordnance Corps, U. S. Army.\n\nReprint - 50_Marble_FE_1954.pdf
", "abstract": "The analytic investigation of laminar combustion processes which are essentially two- or three-dimensional present some mathematical difficulties. There are, however, several examples of two-dimensional flame propagation which involve transverse velocities that are small in comparison with that in the principal direction of flow. Such examples occur in thc problem of flame quenching by a cool surface, flame stabilization on a heated flat plate, combustion in laminar mixing zones, etc. In these cases the problem may be simplified by employing what is known in fluid mechanics as the boundary-layer approximation, since it was applied first by Prandtl in his treatment of the viscous flow over a flat plate. Physically it consists in recognizing that if the transverse velocity is small, the variations of flow properties along the direction of main flow are small in comparison with those in a direction normal to the main flow. The analytic description of the problem simplifies accordingly. The present analysis considers the ignition and combustion in the laminar mixing zone between two parallel moving gas streams. One stream consists of a cool combustible mixture, the second is hot combustion products. The two streams come into contact at a given point and a laminar mixing process follows in which the velocity distribution is modified by viscosity, and the temperature and composition distributions by conduction, diffusion, and chemical reaction. The decomposition of the combustible stream is assumed to follow first-order reaction kinetics with temperature dependence according to the Arrhenius law. For a given initial velocity, composition, and temperature distribution, the questions to be answered are: (1) Does the combustible material ignite; and (2) how far downstream of the initial contact point does the flame appear and what is the detailed process of development. Since the hot stream is of infinite extent, it is found that ignition always takes place at some point of the stream. However, when the temperature of the hot stream drops below a certain value, the distance required for ignition increases so enormously that it essentially does not occur in a physical apparatus of finite dimension. The complete development of the laminar flame front is computed using an approximation similar to the integral technique introduced by von K\u00e1rm\u00e1n into boundary layer theory.", "date": "1954-03", "date_type": "published", "publication": "Jet Propulsion", "volume": "24", "number": "2", "publisher": "American Rocket Society", "pagerange": "85-94", "id_number": "CaltechAUTHORS:20100120-092445763", "issn": "0095-8751", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20100120-092445763", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "Ordnance Corps, U.S. Army" } ] }, "collection": "CaltechAUTHORS", "other_numbering_system": { "items": [ { "id": "50", "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center", "value": "Guggenheim Jet Propulsion Center" } ] }, "primary_object": { "basename": "50_Marble_FE_1954.pdf", "url": "https://authors.library.caltech.edu/records/qycd1-h1z74/files/50_Marble_FE_1954.pdf" }, "resource_type": "article", "pub_year": "1954", "author_list": "Marble, Frank E. and Adamson, Thomas C., Jr." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/3a3hb-v4090", "eprint_id": 16981, "eprint_status": "archive", "datestamp": "2023-08-19 02:10:24", "lastmod": "2023-10-19 22:42:29", "type": "article", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } }, { "id": "Cox-D-W-Jr", "name": { "family": "Cox", "given": "Dale W., Jr." } } ] }, "title": "Servo-Stabilization of Low-Frequency Oscillations in a Liquid Bipropellant Rocket Motor", "ispublished": "pub", "full_text_status": "public", "note": "(Reprinted from Journal of the American Rocket Society, March-April 1953) \n\nCopyright, 1953, by the American Rocket Society, Inc., and reprinted by permission of the copyright owner. \n\nReceived October 1, 1952.\n\nReprint - 37_Marble_FE_1953.pdf
", "abstract": "The recent work of H. S. Tsien concerning the servostabilization of rocket motors is extended to the liquid bipropellant rocket motor. It is shown that by use of a feedback system containing a device to sense the combustion chamber pressure, a suitably designed amplifier, and a servomechanism which governs the propellant How, the low-frequency oscillations which occur in the rocket configuration may be stabilized for any value of combustion time lag. A method is given for determining a transfer function of the feedback loop which will assure stable operation. The technique of the Satche diagram is employed in stability analysis.", "date": "1953-03", "date_type": "published", "publication": "Journal of the American Rocket Society", "volume": "23", "number": "2", "publisher": "American Rocket Society", "pagerange": "63-74, 81", "id_number": "CaltechAUTHORS:20091215-101526652", "issn": "0095-9073", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20091215-101526652", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "other_numbering_system": { "items": [ { "id": "37", "name": "Guggenheim Jet Propulsion Center" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "primary_object": { "basename": "37_Marble_FE_1953.pdf", "url": "https://authors.library.caltech.edu/records/3a3hb-v4090/files/37_Marble_FE_1953.pdf" }, "resource_type": "article", "pub_year": "1953", "author_list": "Marble, Frank E. and Cox, Dale W., Jr." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/zt6sp-jyw37", "eprint_id": 450, "eprint_status": "archive", "datestamp": "2023-08-21 22:26:13", "lastmod": "2023-10-13 21:49:14", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } }, { "id": "Michelson-I", "name": { "family": "Michelson", "given": "Irving" } } ] }, "title": "Analytical Investigation of Some Three-Dimensional Flow Problems in Turbomachines", "ispublished": "unpub", "full_text_status": "public", "note": "Guggenheim Jet Propulsion Center Publication No. 10", "abstract": "One problem encountered in the theory of turbomachines is that of calculating the fluid velocity components when the inner and outer boundaries of the machine as well as the shape of or forces imparted by the blade row are given. The present paper discusses this problem under the restrictions that the fluid is inviscid and incompressible and that the blade rows consist of an infinite number of infinitely thin blades so that axially symmetric flow is assumed. \n\nIt is shown, in general, that the velocity components in a plane through the turbomachine axis may be expressed in terms of the angular momentum and the leading-edge blade force normal to the stream surfaces. The relation is a nonlinear differential equation to which analytic solutions may be obtained conveniently only after the introduction of linearizing assumptions. A quite accurate linearization is effected through assuming an approximate shape of the stream surfaces in certain nonlinear terms. \n\nThe complete linearized solution for the axial turbomachine is given in such form that blade loading, blade shape, distribution of angular momentum, or distribution of total head may be prescribed. Calculations for single blade rows of aspect ratio 2 and 2/3 are given for a radius ratio of 0.6. They indicate that the process of formation of the axial velocity profile may extend both upstream and downstream of a high-aspect-ratio blade row, while for low aspect ratios the major portion of the three-dimensional flow occurs within the blade row itself. When the through-flow velocity varies greatly from its mean value, the simple linearized solution does not describe the flow process adequately and a more accurate solution applicable to such conditions is suggested. \n\nThe structure of the first-order linearized solution for the axial turbomachine suggested a further approximation employing a minimizing operation. The simplicity of this solution permits the discussion of three interesting problems: Mutual interference of neighboring blade rows in a multistage axial turbomachine, solution for a single blade row of given blade shape, and the solution for this blade row operating at a condition different from the design condition. \n\nIt is found that the interference of adjacent blade rows in the multistage turbomachine may be neglected when the ratio of blade length to the distance between centers of successive blade rows is 1.0 or less. For values of this ratio in excess of 3.0, the interference may be an important influence. The solution for the single blade row indicated that, for the blade shape considered, the distortion of the axial velocity profile caused by off-design operation is appreciably less for low- than for high-aspect-ratio blades. \n\nTo obtain some results for a mixed-flow turbomachine comparable with those for the axial turbomachine as well as to indicate the essential versatility of the method of linearizing the general equations, completely analogous theoretical treatment is given for a turbomachine whose inner and outer walls are concentric cones with common apex and whose flow is that of a three-dimensional source or sink. A particular example for a single rotating blade row is discussed where the angular momentum is prescribed similarly to that used in the examples for the axial turbomachine.", "date": "1952-03", "date_type": "published", "publisher": "National Advisory Committee for Aeronautics", "id_number": "CaltechAUTHORS:MARnacatn2614", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:MARnacatn2614", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "other_numbering_system": { "items": [ { "id": "10", "name": "Guggenheim Jet Propulsion Center Publication" } ] }, "local_group": { "items": [ { "id": "Guggenheim-Jet-Propulsion-Center" } ] }, "primary_object": { "basename": "MARnacatn2614.pdf", "url": "https://authors.library.caltech.edu/records/zt6sp-jyw37/files/MARnacatn2614.pdf" }, "resource_type": "monograph", "pub_year": "1952", "author_list": "Marble, Frank E. and Michelson, Irving" }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/jnvkf-b4h33", "eprint_id": 449, "eprint_status": "archive", "datestamp": "2023-08-21 22:03:36", "lastmod": "2023-10-23 16:04:53", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } }, { "id": "Ritter-W-K", "name": { "family": "Ritter", "given": "William K." } }, { "id": "Miller-M-A", "name": { "family": "Miller", "given": "Mahlon A." }, "orcid": "0000-0002-3964-9312" } ] }, "title": "Effect of the NACA Injection Impeller on the Mixture Distribution of a Double-Row Radial Aircraft Engine", "ispublished": "unpub", "full_text_status": "public", "note": "Published - MARnacatn1069.pdf
", "abstract": "The NACA injection impeller was developed to improve the mixture distribution of aircraft engines by discharging the fuel from a centrifugal supercharger impeller, thus promoting a thorough mixing of fuel and charge air. Tests with a double-row radial aircraft engine indicated that for the normal range of engine power the NACA injection impeller provided marked improvement in mixture distribution over the standard spray-bar injection system used in the same engine. The mixture distribution at cruising conditions was excellent; at 1200, 15OO, and 1700 brake horsepower, the differences between the fuel-air ratios of the richest and the leanest cylinders were reduced to approximately one-third their former values. The maximum cylinder temperatures were reduced about 30 [degrees] F and the temperature distribution was improved by approximately the\ndegree expected from the improvement in mixture distribution. Because the mixture distribution of the engine tested improves slightly at engine powers exceeding 1500 brake horsepower and because the effectiveness of the particular impeller diminished slightly at high rates of fuel flow, the improvement in mixture distribution at \nrated power and rich mixtures was less than that for other conditions. \n\nThe difference between the fuel-air ratios of the richest and the leanest cylinders of the engine using the standard spray bar was so great that the fuel-air ratios of several cylinders were well below the chemically correct mixture, whereas other cylinders were operating at rich mixtures. Consequently, enrichment to improve engine cooling actually increascd some of the critical temperatures. The uniform mixture distribution providod by the injection impeller restored the normal response of cylinder temperatures to mixture enrichnent.", "date": "1946-05", "date_type": "published", "publisher": "National Advisory Committee for Aeronautics", "id_number": "CaltechAUTHORS:MARnacatn1069", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:MARnacatn1069", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "primary_object": { "basename": "MARnacatn1069.pdf", "url": "https://authors.library.caltech.edu/records/jnvkf-b4h33/files/MARnacatn1069.pdf" }, "resource_type": "monograph", "pub_year": "1946", "author_list": "Marble, Frank E.; Ritter, William K.; et el." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/d1cqm-kj337", "eprint_id": 586, "eprint_status": "archive", "datestamp": "2023-08-21 22:03:06", "lastmod": "2023-10-23 16:04:50", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } }, { "id": "Miller-M-E", "name": { "family": "Miller", "given": "Mahlon E." } }, { "id": "Bell-E-B", "name": { "family": "Bell", "given": "E. Barton" } } ] }, "title": "Analysis of cooling limitations and effect of engine-cooling improvements on level-flight cruising performance of four-engine heavy bomber", "ispublished": "unpub", "full_text_status": "public", "note": "Published - MARnacarpt860.pdf
", "abstract": "The NACA has developed means, including an injection impeller and ducted head baffles, to improve the cooling characteristics of the 33500-cubic-inch-displacement radial engines installed in a four-engine heavy bomber. The improvements afforded proper cooling of the rear-row exhaust-valve seats for a wide range of cowl-flap angles, mixture strength, and airplane speeds. The results of flight tests with this airplane are used as a basis for a study to determine the manner and the extent to which the airplane performance was limited by engine cooling. By means of this analysis for both the standard airplane and the airplane with engine-cooling modifications, comparison of the specific range at particular conditions and comparison of the cruising-performance limitations were made. \n\nThe analysis of level-flight cruising performance of the airplane with both the standard- and the modified-engine installations indicated that the maximum cruising economy is attained at the minimum brake specific fuel consumption when engine cooling under these conditions is possible. Operation at lean mixtures, high altitudes, and large gross weights was limited for the standard airplane by engine cooling at the point where larger cowl-gap openings increase the power required for level flight at such a rate that the additional cooling air available is insufficient to cool the engine when developing the additional power. When cooling becomes impossible at the minimum brake specific fuel consumption, the maximum cruising economy is obtained with a cowl-flap angle of approximately 6[degrees] and with the leanest mixture (above the stoichiometric value) giving satisfactory\nengine cooling. \n\nComparison of the calculated perfomance of the standard and the modified airplane indicated that cooling improvements increased the maximum specfic range as much as 38 percent\nfor operation where wide cowl-flap angles and enriched mixtures are required to cool the standard airplane. Corresponding increases in cruising range were calculated for flights in which conditions allowing large increases in cruising economy were encountered. The cooling improvements allow either an increase of more than 10,000 feet in operating altitude at a given airplane weight or a gross-weight increase of from 10,000 pounds at sea lerel to 35,000 pounds at all operating altitudes above 10,000 feet.", "date": "1946", "date_type": "published", "publisher": "National Advisory Committee for Aeronautics", "id_number": "CaltechAUTHORS:MARnacarpt860", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:MARnacarpt860", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "other_numbering_system": { "items": [ { "id": "860", "name": "NACA Technical Report" } ] }, "primary_object": { "basename": "MARnacarpt860.pdf", "url": "https://authors.library.caltech.edu/records/d1cqm-kj337/files/MARnacarpt860.pdf" }, "resource_type": "monograph", "pub_year": "1946", "author_list": "Marble, Frank E.; Miller, Mahlon E.; et el." }, { "id": "https://authors.library.caltech.eduhttps://authors.library.caltech.edu/records/ctqnj-xnw02", "eprint_id": 47994, "eprint_status": "archive", "datestamp": "2023-08-19 01:05:12", "lastmod": "2023-10-26 21:27:37", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marble-F-E", "name": { "family": "Marble", "given": "Frank E." } }, { "id": "Ritter-W-K", "name": { "family": "Ritter", "given": "William K." } }, { "id": "Miller-M-A", "name": { "family": "Miller", "given": "Mahlon A." }, "orcid": "0000-0002-3964-9312" } ] }, "title": "Effect of NACA Injection Impeller on Mixture Distribution of Double-Row Radial Aircraft Engine", "ispublished": "unpub", "full_text_status": "public", "note": "No copyright.\n\nPublished - 19930091898.pdf
", "abstract": "The NACA injection impeller was developed to improve the mixture distribution of aircraft engines by discharging the fuel from a centrifugal supercharger impeller and thus to promote a thorough mixing of fuel and charge air. Experiments with a double-row radial aircraft engine indicated that for the normal range of engine power the NACA injection impeller provided marked improvement in mixture distribution over the standard spray-bar injection system used in the same engine. The mixture distribution at cruising conditions was excellent; at 1200, 1500, and 1700 brake horsepower, the differences between the fuel-air ratios of the richest and the leanest cylinders were reduced to approximately one-third their former values.", "date": "1945", "date_type": "published", "publisher": "National Advisory Committee on Aeronautics", "id_number": "CaltechAUTHORS:20140805-132115205", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20140805-132115205", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "collection": "CaltechAUTHORS", "other_numbering_system": { "items": [ { "id": "821", "name": "NACA Technical Report" } ] }, "primary_object": { "basename": "19930091898.pdf", "url": "https://authors.library.caltech.edu/records/ctqnj-xnw02/files/19930091898.pdf" }, "resource_type": "monograph", "pub_year": "1945", "author_list": "Marble, Frank E.; Ritter, William K.; et el." } ]