[ { "id": "https://authors.library.caltech.edu/records/g29a7-s7f84", "eprint_id": 62643, "eprint_status": "archive", "datestamp": "2023-08-19 04:48:09", "lastmod": "2024-01-13 16:29:15", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Herzog-R-T", "name": { "family": "Herzog", "given": "Robert T." } } ] }, "title": "Nitrogen Injection into the Base Region of a Hypersonic Wake", "ispublished": "unpub", "full_text_status": "public", "note": "Contract No. DA-31-124-ARO(D)-33 U.S. Army Research Office and the Advanced Research Projects Agency. This research is part of Project DEFENDER sponsored by the Advanced Research Projects Agency.\n\n
Submitted - Nitrogen_injection_into_the_base_region_of_a_hypersonic_wake.pdf
", "abstract": "An experimental investigation was made of the changes\noccurring in the near wake of a cylinder at M = 6.0 when nitrogen was injected into the base region. The free stream Reynolds number based on cylinder diameter was 30,000 and the rate of injection was varied from zero to 3 percent of the frontal area free stream mass flow. Pitot pressure profiles across the wake, Schlieren photographs\nand measurement of the boundary layer separation point on the cylinder were used to define the changes in wake geometry. Static pressure and temperature surveys were made along the wake centerline starting at the base of the cylinder and continuing downstream to X/D = 6.O. The injection reduced the recompression in the neck region and left only a slight is entropic compression in place of the\nstrong wake shock. The recirculation of mass in the base region was eliminated with approximately 1.5 percent injection. \n\nAn automated hot wire recording system which produced data\nsuitable for computer reduction was developed and used to measure temperature. In order to reduce the measured wire temperature to total temperature an attempt was made to use a previously developed computer program. Deficiencies in this program are discussed with suggestions for improvements.", "date": "2015-12-08", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151207-101021403", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151207-101021403", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "Army Research Office (ARO)", "grant_number": "DA-31-124-ARO(D)-33" }, { "agency": "Advanced Research Projects Agency (ARPA)" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "Nitrogen_injection_into_the_base_region_of_a_hypersonic_wake.pdf", "url": "https://authors.library.caltech.edu/records/g29a7-s7f84/files/Nitrogen_injection_into_the_base_region_of_a_hypersonic_wake.pdf" }, "pub_year": "2015", "author_list": "Herzog, Robert T." }, { "id": "https://authors.library.caltech.edu/records/q1kbm-e2555", "eprint_id": 62668, "eprint_status": "archive", "datestamp": "2023-08-19 02:47:06", "lastmod": "2024-01-13 16:29:22", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Rabinowicz-J", "name": { "family": "Rabinowicz", "given": "J." } }, { "id": "Jessey-M-E", "name": { "family": "Jessey", "given": "M. E." } }, { "id": "Bartsch-C-A", "name": { "family": "Bartsch", "given": "C. A." } } ] }, "title": "Resistance Thermometer for Heat Transfer Measurements in a Shock Tube", "ispublished": "unpub", "full_text_status": "public", "note": "ARMY ORDNANCE CONTRACT NO. DA-04-495-Ord-19\nArmy Project No. 5B0306004\nOrdnance Project No. TB3-0118\nOOR Project No. 1600-PE.\n\nSubmitted - Resistance_Thermometer_for_Heat_Transfer_Measurement_in_a_Shock_tube.pdf
", "abstract": "This report describes a method for the application of the well-known principle of the resistance thermometer to the problem of measuring surface temperatures and heat transfer rates under highly transient conditions, such as are experienced in a shock tube. By using a thin platinum film sputtered on glass, a resistance thermometer\ngage is obtained which has a response lag of less than 1 \u00b5 sec, a linear output of 2-3 mv/\u00b0c, repeatability and durability. The gage preparation, including the sputtering technique, calibration method, and response characteristics are discussed, and some measurements of surface temperatures and heat transfer rates on models in the shock\ntube are presented in order to illustrate the performance that can be expected from this instrument.", "date": "2015-12-08", "date_type": "published", "publisher": "California Instittue of Technology", "id_number": "CaltechAUTHORS:20151207-161105278", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151207-161105278", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-19" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "Resistance_Thermometer_for_Heat_Transfer_Measurement_in_a_Shock_tube.pdf", "url": "https://authors.library.caltech.edu/records/q1kbm-e2555/files/Resistance_Thermometer_for_Heat_Transfer_Measurement_in_a_Shock_tube.pdf" }, "pub_year": "2015", "author_list": "Rabinowicz, J.; Jessey, M. E.; et el." }, { "id": "https://authors.library.caltech.edu/records/bga1b-gh139", "eprint_id": 62671, "eprint_status": "archive", "datestamp": "2023-08-19 02:50:04", "lastmod": "2024-01-13 16:29:24", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Oliver-R-E", "name": { "family": "Oliver", "given": "R. E." } }, { "id": "Cummings-B-E", "name": { "family": "Cummings", "given": "B. E." } } ] }, "title": "The Effect of a Simple Throat Distortion on the Downstream Flow in a Hypersonic Wind Tunnel Nozzle", "ispublished": "unpub", "full_text_status": "public", "note": "ARMY ORDNANCE CONTRACT NO. DA-04-495-Ord-19\nArmy Project No. 5B0306004\nOrdnance Project No. TB3- 0l 18\nOOR Project No. 1600-PE\n\nSubmitted - The_Effect_of_a_Simple_Throat_Distortion_on_the_Downstream_Flow_in_a_Hypersonic_Wind_Tunnel_Nozzle.pdf
", "abstract": "An experimental investigation was conducted in the GALCIT 2 1/2\" Supersonic Wind Tunnel to determine the effect of a known distortion of the throat section of a hyper sonic nozzle on the flow in the region downstream from the throat. The flow in the nozzle with a rectangular\nthroat section was compared with the flow in the same nozzle with the throat region distorted to produce a throat height which varied linearly across the throat section. The flow was investigated by means of Pitot pressure surveys in the horizontal plane of symmetry of the undistorted nozzle.\n\nThe magnitude of the effect produced by the throat distortion was observed to be approximately that predicted by one-dimensional isentropic flow relations. However, the sign of the effect was reversed in about the distance required for a curved Mach line to cross the channel.", "date": "2015-12-08", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151207-170857129", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151207-170857129", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-19" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "The_Effect_of_a_Simple_Throat_Distortion_on_the_Downstream_Flow_in_a_Hypersonic_Wind_Tunnel_Nozzle.pdf", "url": "https://authors.library.caltech.edu/records/bga1b-gh139/files/The_Effect_of_a_Simple_Throat_Distortion_on_the_Downstream_Flow_in_a_Hypersonic_Wind_Tunnel_Nozzle.pdf" }, "pub_year": "2015", "author_list": "Oliver, R. E. and Cummings, B. E." }, { "id": "https://authors.library.caltech.edu/records/thz0z-vee29", "eprint_id": 62592, "eprint_status": "archive", "datestamp": "2023-08-19 02:43:43", "lastmod": "2024-01-13 16:29:13", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Lees-L", "name": { "family": "Lees", "given": "Lester" } } ] }, "title": "Inviscid Hypersonic Flow Over Blunt-Nosed Slender Bodies", "ispublished": "unpub", "full_text_status": "public", "note": "Army Ordnance Contract No. DA-04-495-Ord-19 Army Project No. 5B0306004 Ordnance Project No. TB3-0118 OOR Project No. 1600-PE.\n\nSubmitted - Inviscid_hypersonic_flow_over_blunt-nosed_slender_bodies.pdf
", "abstract": "At hypersonic speeds the drag/area of a blunt nose is much larger than the drag/area of a slender afterbody, and the energy contained in the flow field in a plane at right angles to the flight direction is nearly constant over a downstream distance many times greater than the characteristic nose dimension. The transverse flow field exhibits certain similarity properties directly analogous to the flow similarity behind an intense blast wave found by G. I. Taylor and S. C. Lin. Conditions for constant energy show that the shape of the bow shock wave R(x) not\ntoo close to the nose is given by R/d = K_1 (\u03b3)(d/c)^(1/2) for a body of revolution, and by R/d = K_0(\u03b3) (x/d)^(2/3) for a planar body, where d is nose diameter, or leading-edge thickness. A comparison with the experiments of Hammitt, Vas, and Bogdonoff on a flat plate with a blunt leading-edge at M_\u221e = 13 in helium shows that the shock wave shape is predicted very accurately by this analysis. The predicted surface pressure distribution is somewhat\nless satisfactory.\n\nEnergy considerations combined with a detailed study of the\nequations of motion show that flow similarity is also possible for a class of bodies of the form r_b ~ x^m, provided that m' \u2264 m \u2264 1, where m' = 3/4 for a planar body and m' = (3/2(\u03b3+1))/(3\u03b3 + 2) for a body of revolution. When m < m' the shock shape is not similar to the body shape, and except for the constant energy flows the entire\nflow field some distance from the nose must depend to some extent on the details of the nose geometry.\n\nBe again again utilizing energy and drag considerations one finds that at hypersonic speeds the inviscid surface pressures generated by a blunt nose are larger than the pressures produced by boundary layer growth on a flat surface over a distance from the nose of order \u2113, where\n\u2113/d \u2243 1/15 ((Re_d)/M_\u221e^2))^3 (Here Re_d is free-stream Reynolds number based on leading-edge thickness.)\nThus at M_\u221e = 15 the viscous interaction effects should be important for Re_d < 10^3, but somewhere in the range 1500 < Re_d < 2000 the inviscid effects must spread rapidly over the plate surface, and certainly for Re_d > 3000 the inviscid pressure field is dominant and determines\nthe boundary layer development, skin friction and heat transfer over the forward portion of the body. These rough estimates are in qualitative agreement with the experimental results of References 7 and 9.", "date": "2015-12-04", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151203-165813194", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151203-165813194", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-19" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "Inviscid_hypersonic_flow_over_blunt-nosed_slender_bodies.pdf", "url": "https://authors.library.caltech.edu/records/thz0z-vee29/files/Inviscid_hypersonic_flow_over_blunt-nosed_slender_bodies.pdf" }, "pub_year": "2015", "author_list": "Lees, Lester" }, { "id": "https://authors.library.caltech.edu/records/b1jb6-ykn57", "eprint_id": 62459, "eprint_status": "archive", "datestamp": "2023-08-19 02:47:11", "lastmod": "2024-01-13 16:28:44", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Machell-R-M", "name": { "family": "Machell", "given": "Reginald M." } }, { "id": "O'Bryant-W-T", "name": { "family": "O'Bryant", "given": "William T." } } ] }, "title": "An Experimental Investigation of the Flow over Blunt-Nosed Cones at a Mach Number of 5.8", "ispublished": "unpub", "full_text_status": "public", "note": "Army Ordnance Contract No. DA-04-495-Ord-19. Army Project No. 5B0306004 Ordnance Project No. TB3-0118 OOR Project No. 1600-PE.\n\nSubmitted - An_Experimental_Investigation_of_the_Flow_over_Blunt-Nosed_Cones_at_a_Mach_Number_of_5.8.pdf
", "abstract": "Shock shapes were observed and static pressures were measured on spherically-blunted cones at a nominal Mach number of 5.8 over a range of Reynolds numbers per inch from 97,000 to 238,000, for angles of yaw from 0\u00b0 to 8\u00b0. Six combinations of the bluntness ratios 0.4, 0.8,\nand l.064 with the cone half angles 10\u00b0, 20\u00b0, and 40\u00b0 were used in determining the significant parameters governing pressure distribution.\n\nThe pressure distribution on the spherical nose for both yawed and unyawed bodies is predicted quite accurately by the modified Newtonian theory given by C_p = C_(P_(max)) cos ^2 \u03b7, where \u03b7 is the angle between the\nnormal to a surface element and the flow direction ahead of the bow shock. Cone half angle was found to be the significant parameter in determining the pressure distribution near the nose-cone junction and\nover the conical afterbody. On the 40\u00b0 spherical nosed cone models the flow overexpanded with respect to the Taylor-Maccoll pressure in the region of the spherical-conical juncture, after which the pressure returned rapidly to the Taylor-Maccoll value. For models with smaller\ncone angles the region of minimum pressure occurred farther back on the conical portion of the model, and the Taylor-Maccoll pressure was approached more gradually. The shape of the pressure distributions as described in nondimensional coordinates was independent of the\nradius of the spherical nose and of the Reynolds number over the range of Reynolds number per inch between .97 x 10^5 and 2.38 x 10^5.\n\nIntegrated results for the pressure foredrag of the models at zero yaw compared very closely with the predictions of the modified Newtonian approximation, except for models with large cone angles and small nose\nradii, where the drag approaches the value given by the Taylor-Maccoll theory for sharp cones.", "date": "2015-12-03", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151130-140501755", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151130-140501755", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-19" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "An_Experimental_Investigation_of_the_Flow_over_Blunt-Nosed_Cones_at_a_Mach_Number_of_5.8.pdf", "url": "https://authors.library.caltech.edu/records/b1jb6-ykn57/files/An_Experimental_Investigation_of_the_Flow_over_Blunt-Nosed_Cones_at_a_Mach_Number_of_5.8.pdf" }, "pub_year": "2015", "author_list": "Machell, Reginald M. and O'Bryant, William T." }, { "id": "https://authors.library.caltech.edu/records/7adrv-phr25", "eprint_id": 62507, "eprint_status": "archive", "datestamp": "2023-08-19 06:24:34", "lastmod": "2024-01-13 16:29:03", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Ko-D-R-S", "name": { "family": "Ko", "given": "Denny R. S." } }, { "id": "Kubota-T", "name": { "family": "Kubota", "given": "Toshi" } }, { "id": "Lees-L", "name": { "family": "Lees", "given": "Lester" } } ] }, "title": "Finite Disturbance Effect on the Stability of a Laminar Incompressible Wake Behind a Flat Plate", "ispublished": "unpub", "full_text_status": "public", "note": "Contract No. DA-31-124-ARO(D)-33 U.S. Army Research Office and the Advanced Rsesarch Projects Agency. This research is a part of Project DEFENDER sponsored by the Advanced Research Projects Agency.\n\nSubmitted - Finite_Disturbance_Effect_on_the_Stability...Memorandum_No._72.pdf
", "abstract": "An integral method is used to investigate the interaction\nbetween the stability of a single frequency finite amplitude disturbance with the non-parallel mean flow in a laminar, incompressible wake behind a flat plate. The mean flow is assumed to be characterized by a few shape parameters. The integrals involving the fluctuating\ncomponents are determined as functions of those shape parameters by solving the inviscid Rayleigh equation of the linear stability theory using the local mean flow. The variations of the amplitude of the fluctuation and the mean flow in the streamwise direction are then determined from solving the set of ordinary differential equations.\nThe effect of coupling between the mean flow and the fluctuation was found to be very important. The calculations show good agreement with the experimental data of Sato and Kuriki.", "date": "2015-12-03", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151201-133700798", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151201-133700798", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "Army Research Office (ARO)", "grant_number": "DA-31-124-ARO(D)-33" }, { "agency": "Advanced Research Projects Agency (ARPA)" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "Finite_Disturbance_Effect_on_the_Stability...Memorandum_No._72.pdf", "url": "https://authors.library.caltech.edu/records/7adrv-phr25/files/Finite_Disturbance_Effect_on_the_Stability...Memorandum_No._72.pdf" }, "pub_year": "2015", "author_list": "Ko, Denny R. S.; Kubota, Toshi; et el." }, { "id": "https://authors.library.caltech.edu/records/h7qej-2sw53", "eprint_id": 62442, "eprint_status": "archive", "datestamp": "2023-08-19 02:51:22", "lastmod": "2024-01-13 16:28:42", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Munson-A-G", "name": { "family": "Munson", "given": "Albert G." } } ] }, "title": "A Preliminary Experimental Investigation of the Flow over Simple Bodies of Revolution at M=18.4 in Helium", "ispublished": "unpub", "full_text_status": "public", "note": "Army Ordnance Contract No. DA-04-495-Ord-19. Army Contract No. 5B0306004 Ordnance Project No. TB3-0118 OOR Project No. 1600-PE.\n\nSubmitted - A_Preliminary_Experimental_Investigation_of_the_Flow_Over_Simple_Bodies_of_Revolution.pdf
", "abstract": "An experimental investigation was conducted in the GALCIT\nhypersonic blow-down tunnel to determine surface pressure distributions and shock wave shapes for a series of \"sharp\"-nosed and slightly-blunted bodies of revolution at a nominal Mach number of 18.4 and a free stream Reynolds number of 6.20 x 10^5 per inch. The four bodies\ninvestigated were as follows: (1) 15\u00b0 half-angle \"sharp\" cone; (2) 15\u00b0 half-angle spherically-blunt cone (bluntness ratio= .24); (3) 20\u00b0 half-angle \"sharp\" cone; (4) 2/3-power body.\n\nThe pressure distributions on the \"sharp\" cones agreed well\nwith the Taylor-Maccoll theory. As expected, the pressure near the nose of the blunt cone was much higher than predicted by this theory, but the pressure decreases monotonically to a value lower than the\ntheoretical value on the conical skirt, indicating that the flow has over-expanded. The measured shock wave shape for the 2/3-power body was found to be proportional to x^(0.69), and the shock wave ordinates agree closely with those predicted by Cole and by Kubota and Lees. Measured surface pressure distributions on the 2/3-power\nbody are predicted satisfactorily by the Kubota-Lees analysis. A simple correction for boundary layer growth accounts for most of the increase in pressure on the rear portion of the body over the values predicted by inviscid theory.", "date": "2015-11-30", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151130-094321363", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151130-094321363", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-19" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "A_Preliminary_Experimental_Investigation_of_the_Flow_Over_Simple_Bodies_of_Revolution.pdf", "url": "https://authors.library.caltech.edu/records/h7qej-2sw53/files/A_Preliminary_Experimental_Investigation_of_the_Flow_Over_Simple_Bodies_of_Revolution.pdf" }, "pub_year": "2015", "author_list": "Munson, Albert G." }, { "id": "https://authors.library.caltech.edu/records/wcys7-k7p06", "eprint_id": 61915, "eprint_status": "archive", "datestamp": "2023-08-19 04:08:08", "lastmod": "2024-01-13 16:27:54", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Marlotte-G-L", "name": { "family": "Marlotte", "given": "Gary L." } } ] }, "title": "An Experimental Investigation of the Effect of a Transverse Hypersonic Flow Velocity upon a Low-Density D. C. Electrical Discharge in Air", "ispublished": "unpub", "full_text_status": "public", "note": "Army Ordnance Contract No. DA-04-495-ORD-3231.\n\nThe author acknowledges with gratitude the receipt of a fellowship from the Douglas Aircraft Corporation for the year 1959-1960.\n\nSubmitted - No._66.pdf
", "abstract": "The low-density D. C. electrical discharge in a uniform gas\nstationary with respect to the electrodes has been studied extensively. However. when the gas moves at a hypersonic speed transverse to the electrodes, several completely new effects are introduced. Experiments were carried out with air in the GALCIT 5-inch by 5-inch hypersonic wind tunnel with a nominal Mach number of 5.8. D. C. breakdown voltages and steady-state sub-normal glow voltages were\nmeasured across a channel formed by two sharp-edged insulating flat plates in which flat-plate \"Rogowski\" electrodes were embedded. Segmented electrodes were then used in the normal glow regime to measure current distributions at each electrode for various electrode\nsegment combinations, total currents, and densities.\n\nSome important results of the present study are the following. For the characteristic dimensions and speeds involved. the explicit dependence\nof electrical breakdown upon the velocity of the stream is\nsmall compared to the effect of boundary layer density defects. A theoretical treatment of breakdown is given and qualitative agreement with experiments is obtained. In the normal glow regime using segmented electrodes, an unmistakable explicit flow velocity effect was\nobserved, with the discharge current paths being displaced downstream compared to static bell-jar tests at equivalent densities.", "date": "2015-11-06", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151105-160427473", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151105-160427473", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U. S. Army Office of Ordnance", "grant_number": "DA-04-495-ORD-3231" }, { "agency": "Douglas Aircraft Corporation" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "No._66.pdf", "url": "https://authors.library.caltech.edu/records/wcys7-k7p06/files/No._66.pdf" }, "pub_year": "2015", "author_list": "Marlotte, Gary L." }, { "id": "https://authors.library.caltech.edu/records/stpwx-3kc10", "eprint_id": 61908, "eprint_status": "archive", "datestamp": "2023-08-19 03:51:27", "lastmod": "2024-01-13 16:27:42", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Cann-G-L", "name": { "family": "Cann", "given": "Gordon L." } } ] }, "title": "Energy Transfer Processes in a Partially Ionized Gas", "ispublished": "unpub", "full_text_status": "public", "note": "Army Ordnance Contracts No. DA-04-495-Ord-1960 and 3231.\n\nSubmitted - No._61.pdf
", "abstract": "The following paper is divided into three more or less separate sections. The first section (Chapters II- VI) deals with an analysis of the transport properties of a partially ionized gas subject to the constraint\nthat the average random energy of all constituent particles\nis exactly equal (equipartition of energy). This constraint is necessary so that the formal Chapman-Enskog solution of Boltzman's equation can be used to evaluate the various transport coefficients. Subject to this constraint, a set of tractable equations describing the mass and energy\ndiffusion in a partially ionized gas is obtained that includes all terms correct to the order of the square root of the ratio of the electron to\natom mass compared to one. The transport coefficients are evaluated for helium and argon over the complete range of partial ionization assuming that the species particle densities are quite close to their equilibrium values.\n\nThe analysis indicates that the electron and ion diffusion\nvelocities are more closely coupled than the equations of Chapman and Cowling show. The added coupling implicitly applies the constraint of zero mass velocity to the gas locally. Because of this constraint a current in the direction of (E x B) x B occurs in addition to the direct\nand Hall currents.\n\nIt is shown that the only part of the thermal conductivity that can be influenced by a magnetic field is that part of the energy carried by the diffusion of the charged particles. For this reason, magnetic fields, in general, cannot be nearly as effective in reducing heat transfer\nrates as was previously thought, e. g., a magnetic field will have no influence on the thermal conductivity in a fully ionized gas, except through its influence on the current density and the thermal diffusion.\n\nChapters VII- IX comprise the second section of this paper and deal with the development of a similarity solution for axially symmetric electric discharges. A number of parameters are obtained and discussed. The solution is evaluated for a discharge in argon gas at one atmosphere pressure in which the temperature on the axis of\nthe discharge varies from 6,000\u00b0K to 19,000\u00b0K. The current-voltage characteristic obtained from this solution is compared with an experimentally determined curve of H. Maecker.\n\nThe third section of this paper (Chapters X - XIII) is concerned with the mechanisms of energy transfer in arc jet devices. Use is made of the previous sections of the paper to determine the relative magnitude of the amount of energy that is transferred to the gas in the various parts of the electric discharge. The various possible electrode\nconfigurations are discussed in detail and compared. The design and performance of an annular electrode arc heater with a rotating arc is next described and discussed. Because of a number of undesirable performance characteristics of this type of electrode configuration, a\nmodified heater was constructed with the cathode emission occurring along the axis of the applied magnetic field. Details of the unexpectedly good performance of this configuration are given. It is shown that the arc potential drop depends primarily on the strength of the applied\nmagnetic field and the gas enthalpy downstream of the arc. The dependence of the arc potential drop on the arc current and the ambient pressure is shown to be weak over the ranges tested, e. g., 50 to 300 amperes for the current and l to 4 atmospheres for the pressure. Some heat transfer measurements taken with this equipment are\npresented.\n\nAppendix I is concerned with the evaluation of the transport\ncoefficients in a partially ionized gas. Formulae are developed for determining the viscosity, thermal conductivity, and electric conductivity\nof the plasma. These coefficients are computed for argon\nand helium at one atmosphere pressure and over the temperature range of partial ionization.", "date": "2015-11-06", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151105-152212860", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151105-152212860", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-1960" }, { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-3231" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "No._61.pdf", "url": "https://authors.library.caltech.edu/records/stpwx-3kc10/files/No._61.pdf" }, "pub_year": "2015", "author_list": "Cann, Gordon L." }, { "id": "https://authors.library.caltech.edu/records/jtnh0-hb918", "eprint_id": 61907, "eprint_status": "archive", "datestamp": "2023-08-19 03:51:02", "lastmod": "2024-01-13 16:27:40", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Kingsland-L-Jr", "name": { "family": "Kingsland", "given": "Louis, Jr." } } ] }, "title": "Experimental Study of Helium and Argon Diffusion in the Wake of a circular Cylinder at M=5.8", "ispublished": "unpub", "full_text_status": "public", "note": "Army Ordnance Contracts No. DA-04-495-Ord-1960 and 3231.\n\nSubmitted - No._60.pdf
", "abstract": "Experimental measurements of the diffusion of helium and argon in the wake of a porous cylinder were made in the GALCIT hypersonic wind tunnel at Mach number 5. 8. The cylinder was mounted perpendicular to the flow and small quantities of tracer gas were pumped through the\nmodel walls into the flow. The thermal conductivity method of gas analysis was used to determine the concentration of sample gases extracted from points in the wake.\n\nThe transverse and axial distribution of concentration appeared to follow theoretical estimates of \"similarity behavior\". Injection of tracer gas was found to have a measurable effect on stagnation pressure and this effect was taken into account during computations. Numerical\nvalues of diffusion coefficients along the wake centerline were computed from the experimental data and then compared with theoretical values for laminar flow. Close agreement between experimental and theoretical values at Re_d= 18,000 verified that the inner wake was laminar as far downstream as measurements could be made (15 diameters).\nAt Re_d= 72,000, the data showed that mixing processes\nwere 3 times more rapid for helium, and 10 times more rapid for argon, than those expected in laminar flow. This result confirmed the presence of turbulence at this flow condition.", "date": "2015-11-06", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151105-151451677", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151105-151451677", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-1960" }, { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-3231" } ] }, "collection": "CaltechAUTHORS", "local_group": { "items": [ { "id": "Hypersonic-Research-Project", "value": "Hypersonic Research Project" } ] }, "primary_object": { "basename": "No._60.pdf", "url": "https://authors.library.caltech.edu/records/jtnh0-hb918/files/No._60.pdf" }, "pub_year": "2015", "author_list": "Kingsland, Louis, Jr." }, { "id": "https://authors.library.caltech.edu/records/0xb7q-72y97", "eprint_id": 61917, "eprint_status": "archive", "datestamp": "2023-08-19 04:25:12", "lastmod": "2024-01-13 16:27:58", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Wu-Ying-Chu-Lin", "name": { "family": "Wu", "given": "Ying-chu Lin" } } ] }, "title": "Flow Generated by a Suddenly Heated Flat Plate", "ispublished": "unpub", "full_text_status": "public", "note": "U. S. Army Research Office and the Advanced Research Projects Agency Contract No. DA-31-124-ARO(D)-33. This research is a part of Project DEFENDER sponsored by the Advanced Research Projects Agency.\n\nThe author is grateful to the Zonta International for granting the Amelia Earhart Sc-holarships which provided part of her financial support.\n\nSubmitted - No._68.pdf
", "abstract": "By employing the two-sided Maxwellian in Maxwell's moment\nmethod a kinetic theory description is obtained of the flow generated by a step-function increase in the temperature of an infinite flat plate. Four moments are employed in order to satisfy the three conservation\nequations, plus one additional equation involving the heat flux in the direction normal to the plate. For a small temperature rise the equations are linearized, and closed-form solutions are obtained for\nsmall and large time in terms of the average collision time.\n\nInitially the disturbances propagate along two distinct characteristics, but the discontinuities across these waves damp out as time increases. At large time the main disturbance propagates with the isentropic sound speed. Solutions for mean normal velocity and temperature show the transition from the nearly collision-free regime\nto the Navier-Stokes-Fourier regime, which is characterized by a boundary layer near the plate surface merging into a diffuse \"wave\".\nThe classical continuum equations, plus a temperature jump boundary condition, seem to be perfectly adequate to describe the flow beyond a few collision times, provided one accounts properly for the interaction between the inner thermal layer and the outer diffuse wave.", "date": "2015-11-06", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151105-161933516", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151105-161933516", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "Army Research Office (ARO)", "grant_number": "DA-31-124-ARO(D)-33" }, { "agency": "Advanced Research Projects Agency (ARPA)" }, { "agency": "Zonta International Amelia Earhart Fellowship" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "No._68.pdf", "url": "https://authors.library.caltech.edu/records/0xb7q-72y97/files/No._68.pdf" }, "pub_year": "2015", "author_list": "Wu, Ying-chu Lin" }, { "id": "https://authors.library.caltech.edu/records/n934q-7rd36", "eprint_id": 61918, "eprint_status": "archive", "datestamp": "2023-08-19 04:26:34", "lastmod": "2024-01-13 16:28:00", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Tracy-R-R", "name": { "family": "Tracy", "given": "Richard R." } } ] }, "title": "Hypersonic Flow over a Yawed Circular Cone", "ispublished": "unpub", "full_text_status": "public", "note": "Contract No. DA-31-124-ARO(D)-33 U.S. Army Research Office and the Advanced Research Projects Agency. This research is a part of Project DEFENDER sponsored by the Advanced Research Projects Agency. \n\nBeyond the appreciation due to those of the GALCIT faculty and staff whose continuing effort underlies every research project, and the U. S. taxpayers, through whose generosity and wisdom a portion of this research was underwritten by the Hypersonic Research Project sponsored by the U. S. Army Research Office and the Advanced Research Projects Agency, the author is particularly grateful to:\n\nLockheed Aircraft Corporation who, through the Lockheed Leadership Foundation, contributed financially to the author's graduate studies...\n\nSubmitted - No._69.pdf
", "abstract": "A 10\u00b0 semi-apex, circular cone is tested in air at Mach 8 and at 0 yaw angles to 24\u00b0; surface pressure, heat transfer, and pitot-pressure throughout the flow field are presented. The nominal surface temperature\nis 40\" of the free stream stagnation temperature, and the\nReynolds nunber, based on cone generator length, is varied from 0.5 x 10^5 to 4.2 x 10^5 . Heat transfer is measured at higher surface temperature ratios (up to 56%) and Reynolds nunbers (up to 7.3 x 10^5) by reducing the free stream stagnation temperature. All raw data consist\nof continuous circumferential distributions of each quantity and are included in a supplement.\n\nThe surface pressure data are compared with the theories of\nStone-Kopal and Cheng; Reshotko's theory of heat transfer to the windward generator is compared with experiment. The probe data delineate the boundary between viscous and inviscid flow and determine the shape\nof the outer shock wave as well as the secondary shocks which appear in the flow field at large yaw. The probe data are sufficient to determine the flow field in the plane of symmetry and permit an approximate\nrepresentation of the Mach number profiles of the separated viscous flow in the leeward meridian plane beyond a moderate yaw angle.", "date": "2015-11-06", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151105-162933285", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151105-162933285", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "Army Research Office (ARO)", "grant_number": "DA-31-124-ARO(D)-33" }, { "agency": "Advanced Research Projects Agency (ARPA)" }, { "agency": "Lockheed Aircraft Corporation" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "No._69.pdf", "url": "https://authors.library.caltech.edu/records/n934q-7rd36/files/No._69.pdf" }, "pub_year": "2015", "author_list": "Tracy, Richard R." }, { "id": "https://authors.library.caltech.edu/records/c1wq3-xm483", "eprint_id": 61916, "eprint_status": "archive", "datestamp": "2023-08-19 04:09:27", "lastmod": "2024-01-13 16:27:56", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "McCarthy-J-F-Jr", "name": { "family": "McCarthy", "given": "John F., Jr." } } ] }, "title": "Hypersonic Wakes", "ispublished": "unpub", "full_text_status": "public", "note": "Army Ordnance Contract No. DA-04-495-ORD-3231.\n\nSubmitted - No._67.pdf
", "abstract": "An experimental investigation was made of the flow field behind a two-dimensional circular cylinder at a nominal Mach number of 5.7. The free-stream Reynolds number based on the cylinder diameter was varied over a range from 4300 to 66, 500 by changing both the diameter of\nthe cylinder and the stagnation pressure of the wind tunnel.\nPitot-pressure, static-pressure, and total-temperature measurements were made at various distances behind the cylindrical rod in order to determine the state properties in the wake. Base-pressure measurements\nwere also taken at various Reynolds numbers.\n\nFrom these measurements, the transition from laminar to turbulent flow in the wake was determined and successfully correlated with other data. A transition Reynolds number based on local conditions and the\nlength of laminar run was determined. Extensive comparison of the experimental data with Kubota's theory for laminar flow was then made. A satisfactory comparison was made between theory and experiment.\nBecause of the nature of the tests conducted, only a qualitative comparison was made with the theory of Lees and Hromas for turbulent flow.", "date": "2015-11-06", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151105-161358311", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151105-161358311", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U. S. Army Ordnance", "grant_number": "DA-04-495-ORD-3231" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "No._67.pdf", "url": "https://authors.library.caltech.edu/records/c1wq3-xm483/files/No._67.pdf" }, "pub_year": "2015", "author_list": "McCarthy, John F., Jr." }, { "id": "https://authors.library.caltech.edu/records/xgm4e-w1v24", "eprint_id": 61914, "eprint_status": "archive", "datestamp": "2023-08-19 04:03:35", "lastmod": "2024-01-13 16:27:52", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Lees-L", "name": { "family": "Lees", "given": "Lester" } }, { "id": "Liu-Chung-Yen", "name": { "family": "Liu", "given": "Chung-Yen" } } ] }, "title": "Kinetic Theory Description of Conductive Heat Transfer from a Fine Wire", "ispublished": "unpub", "full_text_status": "public", "note": "Army Ordnance Contract No. DA-04-495-ORD-3231.\n\nSubmitted - No._65.pdf
", "abstract": "The Maxwell moment method utilizing the two-sided Maxwellian\ndistribution function is applied to the problem of conductive heat transfer between two concentric cylinders at rest. Analytical solutions are obtained for small temperature differences between the cylinders.\nThe predicted heat transfer agrees very well with experiments performed by Bomelburg, Sch\u00e4fer-Rating and Eucken. Comparison with results given by Grad's thirteen moment equations, and with those given by Fourier's \"law\" plus the Maxwell-Smoluchowski temperature-jump\nboundary condition shows that the two-sided character in the\ndistribution function is a crucial factor in problems involving surface curvature.", "date": "2015-11-06", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151105-155638313", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151105-155638313", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U. S. Army Office of Ordnance", "grant_number": "DA-04-495-ORD-3231" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "No._65.pdf", "url": "https://authors.library.caltech.edu/records/xgm4e-w1v24/files/No._65.pdf" }, "pub_year": "2015", "author_list": "Lees, Lester and Liu, Chung-Yen" }, { "id": "https://authors.library.caltech.edu/records/jqk5z-wgz59", "eprint_id": 61861, "eprint_status": "archive", "datestamp": "2023-08-19 03:32:29", "lastmod": "2024-01-13 16:27:32", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Russell-D-A", "name": { "family": "Russell", "given": "David A." } } ] }, "title": "A Study of Area Change Near the Diaphragm of a Shock Tube", "ispublished": "unpub", "full_text_status": "public", "note": "Army Ordnance Contract No. DA-04-495-Ord-1960.\n\nSubmitted - No._57.pdf
", "abstract": "The performance of a shock tube with area change near the\ndiaphragm has been calculated for the high shock speed case by previous authors. This report extends the ideal theory calculations to include the whole shock speed range and all possible area changes near the diaphragm.\nSimple calculation procedures are presented and the practical applications of this type of area change are discussed.\n\nExperimental measurements show excellent agreement with the\ntheory except for the intermediate shock speed range where a non-steady secondary shock wave is predicted. Here not only is the agreement with the basic performance curves marginal, but detailed observations\nrevealed that no secondary normal shock is present! A new model is devised to explain these discrepancies. This new model takes frictional effects into account and shows promise of being useful for other shock tube problems.", "date": "2015-11-05", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151104-160152440", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151104-160152440", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-1960" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "No._57.pdf", "url": "https://authors.library.caltech.edu/records/jqk5z-wgz59/files/No._57.pdf" }, "pub_year": "2015", "author_list": "Russell, David A." }, { "id": "https://authors.library.caltech.edu/records/zexj9-5bf03", "eprint_id": 61860, "eprint_status": "archive", "datestamp": "2023-08-19 03:32:23", "lastmod": "2024-01-13 16:27:30", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Ai-Daniel-Kwoh-i", "name": { "family": "Ai", "given": "Daniel Kwoh-i" } } ] }, "title": "Cylindrical Couette Flow in a Rarefied Gas According to Grad's Equations", "ispublished": "unpub", "full_text_status": "public", "note": "Army Ordnance Contract No. DA-04-495-Ord-1960.\n\nSubmitted - No._56.pdf
", "abstract": "Grad's thirteen moment method is applied to the problem of the shear flow and heat conduction between two concentric, rotating cylinders of infinite length. In order to concentrate on the effects of curvature the\nproblem is linearized by requiring that the Mach number is small compared with unity, and that the temperature difference between the two cylinders is small compared with the mean temperature. The solutions\nof the linearized Grad equations show a qualitatively correct transition of the cylinder drag from free-molecule flow to the classical Navier-Stokes regime. However the magnitude of the curvature effect on the drag in\nrarefied flow is not given correctly, because Grad's distribution function ignores the wedge-like domains of influence of the two cylinders.\n\nThe solution obtained for the heat transfer rate is physically unrealistic in the free-molecule flow limit, and this result is produced by a cross-coupling between the normal stresses and the radial heat flux\nimposed by Grad's distribution function. In this simple problem the difficulty can be eliminated by taking the normal stresses to be identically zero and employing a truncated moment method. However, in general this\ndevice cannot be utilized in problems involving curved solid boundaries, or when dissipation is considered. One concludes that the choice of the\ndistribution function to be employed in Maxwell's moment equations is dictated by the requirements imposed in the limiting case of highly rarefied gas flows, as well as in the Navier-Stokes regime.", "date": "2015-11-05", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151104-154821570", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151104-154821570", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-1960" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "No._56.pdf", "url": "https://authors.library.caltech.edu/records/zexj9-5bf03/files/No._56.pdf" }, "pub_year": "2015", "author_list": "Ai, Daniel Kwoh-i" }, { "id": "https://authors.library.caltech.edu/records/jkfga-n1b84", "eprint_id": 61909, "eprint_status": "archive", "datestamp": "2023-08-19 03:51:57", "lastmod": "2024-01-13 16:27:44", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Christiansen-W-H", "name": { "family": "Christiansen", "given": "Walter H." } } ] }, "title": "Development and Calibration of a Cold Wire Probe for Use in Shock Tubes", "ispublished": "unpub", "full_text_status": "public", "note": "Army Ordnance Contracts No. DA-04-495-Ord-1960 and 3231.\n\nSubmitted - No._62.pdf
", "abstract": "Th e use of a fine unheated wire for making s hock tube flow\nmeasurements is investigated. The operation of the instrument depends on the transient nature of the shock tube flow. The wire is referred to here as a cold wire; it operates in a non-steady manner which is completely different from the usual hot wire operation.\nThis report describe s the construction and calibration of the cold wire.\n\nThe experimental law for the rate of gain of heat to the wire 1n air is determine d over a range of Mach numbers from 0.4 to 1.9 and a range of Reynolds numbers from 0.035 to 3,500 based on the wire diameter and the conditions in the hot flow following the initial shock wave. Similar measurements are reported for argon. The heat transfer measurements cover the continuum region, the slip\nand transitional regions, and extend into the free-molecule flow region. The dimensionless results are compared with hot wire measurements obtained in wind tunnels and are found to differ slightly. A difference exists because the cold wire gains heat from the fluid while the hot wire loses heat to the fluid. The measurements are\nvery repeatable and self-consistent, and they indicate that the wire can be used to give an accurate flow measurement in the shock tube. \n\nSome potential applications of the wire for the study of shock-tube flows are presented. It is concluded that the fine unheated wire is a versatile tool that can be used to great advantage in the shock tube.", "date": "2015-11-05", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151105-153304847", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151105-153304847", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-1960" }, { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-3231" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "No._62.pdf", "url": "https://authors.library.caltech.edu/records/jkfga-n1b84/files/No._62.pdf" }, "pub_year": "2015", "author_list": "Christiansen, Walter H." }, { "id": "https://authors.library.caltech.edu/records/41v0q-thz60", "eprint_id": 61912, "eprint_status": "archive", "datestamp": "2023-08-19 04:03:22", "lastmod": "2024-01-13 16:27:50", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Renard-M-L", "name": { "family": "Renard", "given": "Marc L." } } ] }, "title": "Experimental Investigation of an Arc Heater", "ispublished": "unpub", "full_text_status": "public", "note": "Army Ordnance Contract No. DA-04-495-0RD-3231.\n\nSubmitted - No._64.pdf
", "abstract": "An electric arc heater, intended to provide a steady flow of high stagnation temperature gas (up to 10,000\u00b0K) into a convergent-divergent nozzle, was designed at the GALCIT Hypersonic Laboratory. \n\nSection 2 first gives a few preliminary calculations which have been made for the arc heater-nozzle combination, using argon, at stagnation pressures of 1 and 2 atm., and assuming equilibrium flow. In particular, the Mach number in the test section of a fixed nozzle\nwill depend on the thermodynamic properties at the reservoir.\n\nIn the heater, the direct-current arc is axially constricted by a channel parallel to the gas flow. A description of the design and instrumentation is given in Sections 2 and 3.\n\nFor two series of experiments, using argon, the central electrode was either the cathode, as in the conventional arrangement, or the anode: both configurations were thoroughly investigated. Provided a sharp\nedge exists at the end of the flow constricting channel, the configuration with anode in the center was found to give, generally, a more stable functioning, with a voltage drop about twice as large, higher efficiency\nand thus higher average temperature for the same mass flow of gas, as compared to the case where the cathode is in the center. In the ranges of power (up to 13 Kw) and mass flow (up to 6.00 gr/sec) investigated, it was found that the best efficiency is obtained for a swirl close to the\ncentral electrode and large gas mass flows. When the anode is in the center, a long and narrow constricting channel leads to the optimal conditions. With the reversed polarities, the geometry of the downstream channel is not very important.\n\nFinally, a tentative explanation of the results is given,\nemphasizing in particular that the \"anode in the center\" case corresponds to a \"long\" arc, and the \"cathode in the center\" to a \"short\" one with poorer transfer of energy from the arc to the gas.", "date": "2015-11-05", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151105-154635012", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151105-154635012", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U. S. Army Ordnance", "grant_number": "DA-04-495-0RD-3231" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "No._64.pdf", "url": "https://authors.library.caltech.edu/records/41v0q-thz60/files/No._64.pdf" }, "pub_year": "2015", "author_list": "Renard, Marc L." }, { "id": "https://authors.library.caltech.edu/records/ssc27-70a26", "eprint_id": 61911, "eprint_status": "archive", "datestamp": "2023-08-19 03:54:03", "lastmod": "2024-01-13 16:27:48", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Dewey-C-F-Jr", "name": { "family": "Dewey", "given": "C. Forbes, Jr." } } ] }, "title": "Hot-wire Measurements in Low Reynolds Number Hypersonic Flows", "ispublished": "unpub", "full_text_status": "public", "note": "Army Ordnance Contracts DA-04-495-Ord-1960 and DA-04-495-ORD-3231.\n\nSubmitted - No._63.pdf
", "abstract": "Measurements were made of the heat loss and recovery temperature of a fine hot-wire at a nominal Mach number of 5.8. Data were obtained over an eight-fold range of Reynolds numbers in the transitional regime between continuum and free-molecule flow. At high Reynolds numbers, the heat transfer data agree well with the results of Laufer and McClellan, which were obtained at lower Mach\nnumbers. At lower Reynolds numbers, the results indicate a monotonic transition between continuum and free molecule heat transfer laws. The slope of the heat transfer correlation also appears to vary monotonically,\nwith Nu=\u221aRe at high Reynolds numbers and Nu ~ Re for\nRe < < 1.\n\nData on the wire recovery temperature (corresponding to zero\nnet heat transfer) were obtained for free-stream Knudsen numbers between 0.4 and 3.0. Comparison with previous data suggests that for Mach numbers greater than about two the normalized variation of recovery temperature in the transitional regime is a unique function of the free-stream Knudsen number.\n\nThe steady-state hot-wire may be used to obtain two thermodynamic measurements: the rate of heat transfer from the wire and the wire recovery temperature. An illustrative experiment was performed in the wake of a transverse cylinder, using both hot-wire and pressure instruments in a redundant system of measurements. It was shown that\ngood accuracy may be obtained with a hot-wire even when the Reynolds number based on wire diameter is small.", "date": "2015-11-05", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151105-153754956", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151105-153754956", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-1960" }, { "agency": "U. S. Army Office of Ordnance", "grant_number": "DA-04-495-ORD-3231" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "No._63.pdf", "url": "https://authors.library.caltech.edu/records/ssc27-70a26/files/No._63.pdf" }, "pub_year": "2015", "author_list": "Dewey, C. Forbes, Jr." }, { "id": "https://authors.library.caltech.edu/records/e7be0-4zg83", "eprint_id": 61866, "eprint_status": "archive", "datestamp": "2023-08-19 03:34:31", "lastmod": "2024-01-13 16:27:36", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Lees-L", "name": { "family": "Lees", "given": "Lester" } }, { "id": "Liu-Chung-Yen", "name": { "family": "Liu", "given": "Chung-Yen" } } ] }, "title": "Kinetic Theory Description of Plane, Compressible Couette Flow", "ispublished": "unpub", "full_text_status": "public", "note": "Army Ordnance Contract no. DA-04-495-Ord-1960.\n\nSubmitted - No._58.pdf
", "abstract": "By utilizing the two-stream Maxwellian in Maxwell's integral\nequations of transfer we are able to find a closed-form solution of the problem of compressible plane Couette flow over the whole range of gas density from free molecule flow to atmospheric. The ratio of shear\nstress to the product of ordinary viscosity and velocity gradient, which is unity for a Newtonian fluid, here depends also on the gas density, the\nplate temperatures and the plate spacing. For example, this ratio decreases rapidly with increasing plate Mach number when the plate temperatures are fixed. On the other hand, at a fixed Mach number based on the temperature of one plate, this ratio approaches unity as\nthe temperature of the other plate increases. Similar remarks can be made for the ratio of heat flux to the product of ordinary heat conduction\ncoefficient and temperature gradient.\n\nThe effect of gas density on the skin friction and heat transfer coefficients is described in terms of a single rarefaction parameter, which amounts to evaluating gas properties at a certain \"kinetic temperature\"\ndefined in terms of plate Mach number and plate temperature ratio. One interesting result is the effect of plate temperature on velocity \"slip\".\nIn the Navier-Stokes regime most of the gas follows the hot plate, because the gas viscosity is larger there. As the gas density decreases the situation is reversed, because the velocity slip is larger at the hot plate\nthan at the cold plate. In the limiting case of a highly rarefied gas most of the gas follows the cold plate.", "date": "2015-11-05", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151104-163525738", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151104-163525738", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-1960" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "No._58.pdf", "url": "https://authors.library.caltech.edu/records/e7be0-4zg83/files/No._58.pdf" }, "pub_year": "2015", "author_list": "Lees, Lester and Liu, Chung-Yen" }, { "id": "https://authors.library.caltech.edu/records/jf0da-2qv04", "eprint_id": 61867, "eprint_status": "archive", "datestamp": "2023-08-19 03:34:37", "lastmod": "2024-01-13 16:27:38", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Ai-Daniel-Kwoh-i", "name": { "family": "Ai", "given": "Daniel Kwoh-i" } } ] }, "title": "Small Perturbations in the Unsteady Flow of a Rarefied Gas Based on Grad's Thirteen Moment Approximation", "ispublished": "unpub", "full_text_status": "public", "note": "Army Ordnance Contract No. DA-04-495-Ord-1960.\n\nSubmitted - No._59.pdf
", "abstract": "In this paper, the unsteady one-dimensional flow of a compressible, viscous and heat conducting fluid is treated, based on linearized Grad's thirteen moment equations. The fluid, initially at rest, is set into motion by some small external disturbances. Our interest is to\nexamine the nature of all the responses. The fluid field extends to infinity in both directions; thus no length is involved, and also there is no\nsolid wall boundary existing in the problem. The nature of the external disturbances is restricted to having a unit impulse in the momentum\nequation and a unit heat addition in the energy equation. The disturbances are located on an infinite plane normal to the flow direction; and the\nresponses induced correspond to fundamental solutions of the problem. The method of Laplace transforms is applied, and the inverse transforms of all quantities are obtained in integral form. Because of the complicated\nexpressions of the integrands involved, we consider only certain limiting cases which correspond to small and large times from the start of the motion, compared to the average time between molecular collisions. In order to study these limiting cases, it is essential to understand\nthe behavior of the integrand in the complex plane; hence all singularities and branch points are obtained.\n\nWhen t is small, the integrand is expanded in powers of t to\nobtain a wave front approximation. All discontinuities are propagated along the characteristics of the linearized system, and a damping term also appears.\n\nAt large values of time, the integrand gets its main contribution around the branch points, and these solutions are identical to those obtained from the Navier-Stokes equation.\n\nThe fundamental solution of the one-dimensional unsteady flow, idealized as it seems to be, offers itself as a tool to understand other related problems. The piston problem, as well as the normal quantities in Rayleigh's problem (e. g., normal velocity, normal stress, and thermodynamical\nquantities), are governed by the same set of equations.\nHence, certain parts of the fundamental solutions can be applied directly\nto these problems. The limiting forms of the normal quantities in Rayleigh's\nproblem are expected to be worked out in another paper in the near future.", "date": "2015-11-05", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151104-170004041", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151104-170004041", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-1960" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "No._59.pdf", "url": "https://authors.library.caltech.edu/records/jf0da-2qv04/files/No._59.pdf" }, "pub_year": "2015", "author_list": "Ai, Daniel Kwoh-i" }, { "id": "https://authors.library.caltech.edu/records/4ak44-qnz65", "eprint_id": 61852, "eprint_status": "archive", "datestamp": "2023-08-19 03:31:08", "lastmod": "2024-01-13 16:27:26", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Christiansen-W-H", "name": { "family": "Christiansen", "given": "Walter H." } } ] }, "title": "Use of Fine Unheated Wires for Heat Transfer Measurements in the Shock Tube", "ispublished": "unpub", "full_text_status": "public", "note": "Army Ordnance Contract No. DA-04-495-Ord-1960.\n\nSubmitted - No._55.pdf
", "abstract": "This report describes the application of fine cold wires for heat transfer measurements in the shock tube. The use of the calorimetric property of the wire results in a heat transfer instrument with an output of .25 mv/oC and a response lag of less than 1 \u00b5sec. The gage construction,\ncalibration, and response characteristics are discussed. Some preliminary results are also presented.", "date": "2015-11-05", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151104-151224999", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151104-151224999", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-1960" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" }, { "id": "GALCIT" } ] }, "primary_object": { "basename": "No._55.pdf", "url": "https://authors.library.caltech.edu/records/4ak44-qnz65/files/No._55.pdf" }, "pub_year": "2015", "author_list": "Christiansen, Walter H." }, { "id": "https://authors.library.caltech.edu/records/21hxp-tpq66", "eprint_id": 61837, "eprint_status": "archive", "datestamp": "2023-08-19 03:29:40", "lastmod": "2024-01-13 16:27:25", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Mohlenhoff-W", "name": { "family": "Mohlenhoff", "given": "William" } } ] }, "title": "Experimental Study of Helium Diffusion in the Wake of a Circular Cylinder at M=5.8", "ispublished": "unpub", "full_text_status": "public", "note": "Army Ordnance Contract No. Da-04-495-Ord-1960.\n\nSubmitted - No._54.pdf
", "abstract": "An experimental study of the diffusion of helium in the wake of a circular cylinder was conducted in the GALCIT hypersonic wind tunnel at a Mach number of 5.8. The cylinder was constructed of material having random porosity and was mounted with its axis perpendicular to\nthe stream. The light gas was injected in small amounts and the thermal conductivity method was utilized to detect the concentration of helium in\nthe air at points downstream. Problems in the utilization of the thermal conductivity method for low sample densities were overcome by suitable calibration.\n\nFlow in the wake of the cylinder was found to display characteristically similar behavior at a few diameters downstream, with respect\nto decay and spread of the concentration. Reynolds number similarity was established in the laminar case, but turbulent Reynolds number similarity may require reference to momentum thickness, which was not\npossible with the present data.\n\nProfile data was somewhat marred by a tunnel pressure perturbation, but many of the important conclusions were not affected. The profiles appear to follow the theoretical Gaussian distribution in the similar region.\n\nThe thermal conductivity method is quite promising as a means of tracing the diffusion of one binary gas constituent in another, as applied to hyper sonic wind tunnel experiment. It will also serve in the\nanalysis of transition and turbulence, and of the lateral spreading of the turbulent fluid into the rest of the wake region behind the bow shock.", "date": "2015-11-04", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151104-125024500", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151104-125024500", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-1960" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "No._54.pdf", "url": "https://authors.library.caltech.edu/records/21hxp-tpq66/files/No._54.pdf" }, "pub_year": "2015", "author_list": "Mohlenhoff, William" }, { "id": "https://authors.library.caltech.edu/records/16bsm-49w92", "eprint_id": 61775, "eprint_status": "archive", "datestamp": "2023-08-19 03:23:26", "lastmod": "2024-01-13 16:27:13", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Lees-L", "name": { "family": "Lees", "given": "Lester" } } ] }, "title": "A Kinetic Theory Description of Rarefied Gas Flows", "ispublished": "unpub", "full_text_status": "public", "note": "Army Ordnance Contract No. Da-04-495-Ord-19. Army Project No. 5B0306004 Ordnance Project No. TB3-0118 OOR Project No. 1600-PE.\n\nSubmitted - No._51.pdf
", "abstract": "An approach to the kinetic theory of gas flows is developed which starts with Maxwell's original integral equations of transfer, rather than with the Maxwell-Boltzmann equation for the velocity distribution function itself. In this procedure the Maxwell-Boltzmann equation is satisfied in\na certain average sense, rather than at every point. The advantage of this method is that relatively simple distribution functions are utilized which contain a small number of unknown functions to be determined by\napplying the conservation laws, plus several additional higher moments. For simplicity a \"two-stream Maxwellian\" is employed, which is a natural extension and generalization of Mott-Smith's function for a normal shock,\nbut differs from it in certain essential respects. As an illustration, the method is applied to linearized plane Couette flow and Rayleigh's problem. Reasonable results are obtained for macroscopic quantities such as mean\nvelocity and shear stress over the whole range of densities from free-molecule flow to the Navier-Stokes regime. This technique is now being applied to some typical non-linear rarefied gas flows.", "date": "2015-11-03", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151102-150954032", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151102-150954032", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-19" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "No._51.pdf", "url": "https://authors.library.caltech.edu/records/16bsm-49w92/files/No._51.pdf" }, "pub_year": "2015", "author_list": "Lees, Lester" }, { "id": "https://authors.library.caltech.edu/records/pqffr-z2e33", "eprint_id": 61777, "eprint_status": "archive", "datestamp": "2023-08-19 03:29:28", "lastmod": "2024-01-13 16:27:17", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Glick-H-S", "name": { "family": "Glick", "given": "Herbert S." } } ] }, "title": "Modified Crocco-Lees Mixing Theory for Supersonic Separated and Reattaching Flows", "ispublished": "unpub", "full_text_status": "public", "note": "Army Ordnance Contract No. DA-04-495-Ord-1960.\n\nThe author acknowledges with gratitude the receipt of a sabbatical leave grant from the Cornell Aeronautical Laboratory, Inc. of Buffalo, New York for the year 1957-1958, and a fellowship from the Curtiss-Wright Corporation for the year 1958-1959.\n\nSubmitted - No._53.pdf
", "abstract": "Re-examination of the Crocco-Lees method has shown that the\nprevious quantitative disagreement between theory and experiment in the region of flow up to separation was caused primarily by the improper C(K) relation assumed. A new C(K) correlation, based on low-speed\ntheoretical and experimental data and on supersonic experimental results, has been developed and found to be satisfactory for accurate calculation\nof two-dimensional laminar super sonic flows up to separation.\n\nA study of separated and reattaching regions of flow has led to a physical model which incorporates the concept of the \"dividing\" streamline and the results of experiment. According to this physical model, viscous momentum transport is the essential mechanism in the zone between separation and the beginning of reattachment, while the reattachment process is, on the contrary, an essentially inviscid process. This physical model has been translated into Crocco-Lees language using a semi-empirical approach, and approximate C(K) and F(K) relations have been determined for the separated and reattaching regions. The results of this analysis have been applied to the problem of shock wave-laminar boundary layer interaction, and satisfactory\nquantitative agreement with experiment has been achieved.", "date": "2015-11-03", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151102-164841286", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151102-164841286", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-1960" }, { "agency": "Curtiss-Wright Corporation" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "No._53.pdf", "url": "https://authors.library.caltech.edu/records/pqffr-z2e33/files/No._53.pdf" }, "pub_year": "2015", "author_list": "Glick, Herbert S." }, { "id": "https://authors.library.caltech.edu/records/h0v4k-hn497", "eprint_id": 61776, "eprint_status": "archive", "datestamp": "2023-08-19 03:26:06", "lastmod": "2024-01-13 16:27:15", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Reshotko-E", "name": { "family": "Reshotko", "given": "Eli" } } ] }, "title": "Stability of the Compressible Laminar Boundary Layer", "ispublished": "unpub", "full_text_status": "public", "note": "Army Ordnance Contract No. Da-04-495-Ord-19. Army Project No. 5B0306004 Ordnance Project No. TB3-0118\nOOR Project No. 1600-PE.\n\nThe author acknowledges with gratitude the receipt of a Daniel and Florence Guggenheim Fellowship in Jet Propulsion for the academic years 1957-58 and 1958-59.\n\nSubmitted - No._52.pdf
", "abstract": "In previous theoretical treatments of the stability of the compressible laminar boundary layer the effect of the temperature fluctuations on the 11viscous11 (rapidly-varying) disturbances is either ignored (Lees-Lin), or\nis accounted for incompletely (Dunn-Lin). A thorough reexamination of this problem shows that temperature fluctuations have a profound influence\non both the \"inviscid\" (slowly-varying) and viscous disturbances above a Mach number of about 2.0. The present analysis includes the effect of temperature fluctuations on the viscosity and thermal conductivity, and\nalso introduces the viscous dissipation term that was dropped in the earlier theoretical treatments.\n\nSome important results of the present study are: (1), the rate of conversion of energy from the mean flow to the disturbance flow through the action of viscosity in the vicinity of the wall increases with Mach number;\n(2), instead of being nearly constant across the boundary layer, the amplitude of inviscid pressure fluctuations for Mach numbers greater than 3 decreases markedly with distance outward from the plate surface. This\nbehavior means that the jump in magnitude of the Reynolds stress in the neighborhood of the critical layer is greatly reduced; (3), at Mach numbers less than about 2 dissipation effects are minor, but they become extremely important at higher Mach numbers since for neutral disturbances they\nmust compensate for the generally destabilizing effects of items (1) and (2). \n\nNumerical examples illustrating the effects of compressibility (including neutral stability characteristics) are obtained and are compared\nwith the experimental results of Laufer and Vrebalovich at M = 2.2, and of Demetriades at M = 5.8.", "date": "2015-11-03", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151102-162610869", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151102-162610869", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-19" }, { "agency": "Daniel and Florence Guggenheim Fellowship in Jet Propulsion" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "No._52.pdf", "url": "https://authors.library.caltech.edu/records/h0v4k-hn497/files/No._52.pdf" }, "pub_year": "2015", "author_list": "Reshotko, Eli" }, { "id": "https://authors.library.caltech.edu/records/825rx-68461", "eprint_id": 61757, "eprint_status": "archive", "datestamp": "2023-08-19 03:19:18", "lastmod": "2024-01-13 16:27:08", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Wood-R-D", "name": { "family": "Wood", "given": "Richard D." } } ] }, "title": "An Experimental Investigation of Hypersonic Stagnation Temperature Problems", "ispublished": "unpub", "full_text_status": "public", "note": "Army Ordnance Contract No. DA-04-495-Ord-19. Army Project No. 6b0306004 Ordnance Project No. TB3-0118 OOR Project No. 1600-PE.\n\nSubmitted - No._50.pdf
", "abstract": "An experimental investigation of single-shielded hypersonic stagnation temperature probes was conducted in the GALCIT Leg No. 1 hypersonic wind tunnel and in the Jet Propulsion Laboratory 12-inch supersonic wind tunnel.\n\nBy the combined use of both shield and base heating, a probe recovery factor of r = 1.0 was obtained over a range of Reynolds numbers at M_\u221e = 5.75. By using the experimental data and simple heat balance equations, the probe losses, for the conditions investigated, were found to be in the proportion:\n\nshield conduction loss - 15\n\nbase conduction loss - 3\n\nthermocouple conduction loss - 1\n\nthermocouple radiation loss - 3/100\n\nThe typical decrease in probe recovery factor observed for decreasing Reynolds number appears to be related to a decrease in the base temperature\nand not to the wire conduction loss as commonly assumed.\n\nAn optimum probe vent to entrance area ratio of A_v/A_e \u2248 1/2 was found and is shown to be a function of the number of vent holes used in the shield.\n\nNo single calibration parameter was found that could relate the experimental recovery factors under all conditions.", "date": "2015-11-02", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151030-161008298", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151030-161008298", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-19" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "No._50.pdf", "url": "https://authors.library.caltech.edu/records/825rx-68461/files/No._50.pdf" }, "pub_year": "2015", "author_list": "Wood, Richard D." }, { "id": "https://authors.library.caltech.edu/records/7vtdr-bte83", "eprint_id": 61756, "eprint_status": "archive", "datestamp": "2023-08-19 03:17:05", "lastmod": "2024-01-13 16:27:06", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Chapkis-R-L", "name": { "family": "Chapkis", "given": "Robert L." } } ] }, "title": "Hypersonic Flow Over an Elliptic Cone: Theory and Experiment", "ispublished": "unpub", "full_text_status": "public", "note": "Army Ordnance Contract No. DA-04-495-Ord-19. Army Project No. 5B0306004 Ordnance Project No. TB3-0118 OOR Project No. 1600-PE.\n\nSubmitted - No._49.pdf
", "abstract": "By applying hyper sonic approximations to Ferri's linearized\ncharacteristics method simple re suits were obtained for the shock shape and surface pressure distribution for an unyawed conical body of arbitrary cross-section. Calculations were carried out for an elliptic\ncone having a ratio of major to minor axis of 2:1, and a semi-vertex angle of about 12\u00b0 in the meridian plane containing the major axis. An experimental investigation of the flow over this body conducted at a\nMa.ch number of 5.8 in the GALCIT hyper sonic wind tunnel showed that the surface pressure distribution at zero angle of attack agreed quite closely with the theoretical prediction. On the other hand the simple\nNewtonian approximation predicts pressures that are too low.\n\nSurface pressure distributions and schlieren photographs of the shock shape were also obtained at angles of attack up to 14\u00b0 at zero yaw, and at angles of yaw up to 10\u00b0, at zero pitch. At the higher angles of attack the Newtonian approximation for the surface pressures is\nquite accurate.", "date": "2015-11-02", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151030-154348286", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151030-154348286", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-19" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "No._49.pdf", "url": "https://authors.library.caltech.edu/records/7vtdr-bte83/files/No._49.pdf" }, "pub_year": "2015", "author_list": "Chapkis, Robert L." }, { "id": "https://authors.library.caltech.edu/records/24dzb-hnr84", "eprint_id": 61698, "eprint_status": "archive", "datestamp": "2023-08-19 03:06:45", "lastmod": "2024-01-13 16:26:54", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Matthews-M-L", "name": { "family": "Matthews", "given": "Malcolm L." } } ] }, "title": "An Experimental Investigation of Viscous Effects on Static and Impact Pressure Probes in Hypersonic Flow", "ispublished": "unpub", "full_text_status": "public", "note": "Hypersonic Research Project Memorandum No. 44. June 2, 1958. Army Ordnance Contract No. DA-04-495-Ord-19. Army Project No. 5B0306004 Ordnance Project No. TB3-0118 OOR Project No. 1600-PE.\n\nSubmitted - No._44.pdf
", "abstract": "An experimental investigation of viscous effects on static and impact pressure probes was conducted in the GALCIT Leg 1 hypersonic wind tunnel.\n\nThis investigation of the impact probes showed viscous effects to be important for free stream Reynolds numbers less than 6000 based on the probe diameter, in the Mach number range 5.4 to 5.7. For 80 < Re < 6000, the results showed the measured impact pressure to be less than the inviscid value. The maximum deviation from the inviscid impact pressure was 2.3 per cent at a Reynolds number of 200. For Re < 80 the measured impact pressure was greater than the inviscid value.\n\nThe investigation of the static pressure probes for a Mach number 5.8 and a free stream Reynolds number of 16,000 based on the probe diameter showed a very thick and rapidly growing boundary layer over the probe surface. This boundary layer was sufficient to cause the static pressure measured by a 10 degree cone-nosed probe with its orifice 45 diameters aft of the probe tip to be 7.5 per cent greater than the free stream static pressure. The boundary layer thickness on the 10 degree cone-nosed probe was several times that of the probe radius. The boundary layer was surveyed on a hemisperical-nosed and a flat-nosed probe and showed the boundary layer thickness to be several times that of the 10 degree cone-nosed probe.", "date": "2015-10-29", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151028-154922690", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151028-154922690", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-19" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "No._44.pdf", "url": "https://authors.library.caltech.edu/records/24dzb-hnr84/files/No._44.pdf" }, "pub_year": "2015", "author_list": "Matthews, Malcolm L." }, { "id": "https://authors.library.caltech.edu/records/0ahf5-v4b45", "eprint_id": 61712, "eprint_status": "archive", "datestamp": "2023-08-19 03:11:23", "lastmod": "2024-01-13 16:27:00", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Warren-C-H-E", "name": { "family": "Warren", "given": "C. Hugh E." } } ] }, "title": "An Experimental Investigation of the Effect of Ejecting a Coolant Gas at the Nose of a Blunt Body", "ispublished": "unpub", "full_text_status": "public", "note": "Hypersonic Research Report Memorandum No. 47. Army Ordnance Contract No. DA-04-495-Ord-19. Army Project 5B0306004 Ordnance Project No. TB3-0118 OOR Project No. 1600-PE.\n\nSubmitted - No._47.pdf
", "abstract": "An experimental investigation has been made of the effect of ejecting nitrogen and helium coolant gases at the nose of a blunt body in the GALCIT 5 inch x 5 inch hype r sonic wind tunnel at a nominal Mach number of 5.8. The gases were ejected with \"swirl\", to encourage them to flow tangentially to the model surface at ejection, and also straight out. Measurements were made of pressure, temperature and heat flux on the surface of the model at incidences of 0, 4, 8 degrees, and for a range of coolant gas flows. \n\nIt was found that ejection with swirl did not in fact lead to an easement of the heating problem, because the high tangential velocity with which the coolant was injected into the boundary layer so increased the wall shear stress, and hence by the Reynolds analogy, the heat flux, that it predominated over the reduced driving temperature difference associated with the cooled boundary layer.\n\nWith straight-out ejection it was found that the heat alleviation capabilities of the ejected coolant were reduced considerably if the momentum flow was sufficiently high that the bow shock wave was bulged out. For the size of ejection orifice in the present study it was possible to eject only nitrogen coolant without disturbing the external flow appreciably. The results suggest, however, that straight-out ejection could provide an effective way of reducing the heat flux provided that the external flow is not disturbed, and tests with a larger ejection orifice are indicated.\n\nA technique is proposed for making steady-state heat-flux measurements by measuring the temperature difference across a uniformly thin skin of uniform, low thermal conductivity.", "date": "2015-10-29", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151029-112313837", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151029-112313837", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-19" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "No._47.pdf", "url": "https://authors.library.caltech.edu/records/0ahf5-v4b45/files/No._47.pdf" }, "pub_year": "2015", "author_list": "Warren, C. Hugh E." }, { "id": "https://authors.library.caltech.edu/records/9k92q-gsr45", "eprint_id": 61700, "eprint_status": "archive", "datestamp": "2023-08-19 03:09:20", "lastmod": "2024-01-13 16:26:58", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Monroe-L-L", "name": { "family": "Monroe", "given": "Louis L." } } ] }, "title": "Investigation of the Transmission of a Shock Wave through an Orifice", "ispublished": "unpub", "full_text_status": "public", "note": "Hypersonic Research Project Memorandum no. 46. Army Ordnance Contract No. DA-04-495-Ord-19. Army Project No. 5B0306004 Ordnance Project No. TB3-0118 OOR Project No. 1600-PE.\n\nSubmitted - No._46.pdf
", "abstract": "A shock wave propagating in air in a shock tube was reflected from an orifice plate, and the strength or Mach number of the transmitted wave was measured for a range of incident shock Mach numbers from 3 to 9 for several types of orifices. Also schlieren photographs of the starting flow pattern were made for some of the orifices investigated.\n\nThe measured values of transmitted shock strength are compared with predicted values based on a theoretical one-dimensional flow model for both an ideal gas and a real gas. The agreement between the measured values of transmitted wave Mach number and the theoretically predicted values is extremely good in the Mach number range investigated for a wedge type orifice at an ambient shock tube pressure of 5.0 mm Hg, and also for a conical type orifice at an ambient shock tube pressure of 2.5 mm Hg. For both orifices the ratio of outlet area to inlet area is 7.67.\n\nThe data also indicate that for a wedge type orifice of area ratio of 23.0 and for a plate (free expansion) type orifice of area ratio 23.0 possible boundary layer and shock wave interactions downstream of the orifice result in measured values of transmitted wave Mach number somewhat greater than that predicted by the one-dimensional flow model.\n\nInvestigation of the conical orifice with an area ratio 7.67 at a low ambient pressure in the shock tube (0.4 mm Hg) also yields measured values of transmitted wave Mach number greater than that predicted by the one-dimensional flow model, indicating the probable development of a thick boundary layer behind the transmitted wave downstream of the orifice.", "date": "2015-10-29", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151028-163306782", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151028-163306782", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-19" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "No._46.pdf", "url": "https://authors.library.caltech.edu/records/9k92q-gsr45/files/No._46.pdf" }, "pub_year": "2015", "author_list": "Monroe, Louis L." }, { "id": "https://authors.library.caltech.edu/records/1s460-11v46", "eprint_id": 61719, "eprint_status": "archive", "datestamp": "2023-08-19 03:14:22", "lastmod": "2024-01-13 16:27:02", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Evans-R-C", "name": { "family": "Evans", "given": "Robert C." } } ] }, "title": "Operation and Performance of a Shock Tube with Heated Driver", "ispublished": "unpub", "full_text_status": "public", "note": "Hypersonic Research Project Memorandum No. 48. Army Ordnance Contract No. DA-04-495-Ord-19. Army Project No. 5B0306004 Ordnance Project No. TB3-0118 OOR Project No. 1600-PE.\n\nSubmitted - No._48.pdf
", "abstract": "A shock tube was constructed with a driver section which could be heated with \"Calrod\" heaters to temperatures of approximately 300\u00b0C. This temperature rise increased the shock wave Mach number by about 40 per cent, or from values of 7.7 to 10 for pressure ratios of 2O,000\nacross the diaphragm. This increase is sufficient to produce partial dissociation of the oxygen molecules behind the shock wave. The flow behind the shock wave was as uniform as that produced by an unheated driver.\n\nA transition section was designed to enable the major portion of the low pressure chamber to be constructed of round Shelby tubing, while the test section still had a flat top and a flat bottom. The flat surfaces are advantageous for optical studies and for convenience in\ninstrumenting the tube. Despite the fact that the transition was gradual, disturbances were present in the flow in the test section, 18 inches downstream of the transition section.", "date": "2015-10-29", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151029-151142532", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151029-151142532", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-19" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "No._48.pdf", "url": "https://authors.library.caltech.edu/records/1s460-11v46/files/No._48.pdf" }, "pub_year": "2015", "author_list": "Evans, Robert C." }, { "id": "https://authors.library.caltech.edu/records/x067c-8b522", "eprint_id": 61699, "eprint_status": "archive", "datestamp": "2023-08-19 03:06:50", "lastmod": "2024-01-13 16:26:56", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Nicholson-K-F", "name": { "family": "Nicholson", "given": "Kenneth F." } } ] }, "title": "The Effects of Blunt Leading Edges on Delta Wings at Mach 5.8", "ispublished": "unpub", "full_text_status": "public", "note": "Hypersonic Research Project Memorandum No. 45. Army Ordnance Contract No. DA-04-495-Ord-19. Army Project No. 5B0306004 Ordnance Project No. TB3-0118 OOR Project No. 1600-PE.\n\nThe investigation was conducted in the GALCIT 5 x 5 inch hypersonic tunnel, under the sponsorship and with the financial support of the Office, Chief of Ordnance, and the Office of Ordnance Research, U. S. Army.\n\nSubmitted - No._45.pdf
", "abstract": "Pressure distributions were measured on a series of four delta wings with subsonic and supersonic leading edges, both sharp and blunt. The blunt leading edge radius was about 0.5 per cent of root chord. Schlieren studies were also made to determine top and side view shock locations. The tests were conducted at a nominal Mach number of 5.8, and at Reynolds numbers between 0.335 x 10^6 and 0.901 x 10^6 based on root chord. Angular settings covered a range -0.2 \u2264 w/V \u2264 0.5 in pitch at zero yaw {about -11.5\u00b0 \u2264 a \u2264 + 30\u00b0), and a range of v/V = \u00b1 0.125 (about \u00b1 7.2\u00b0) at a fixed angle of pitch of 11.5\u00b0.\n\nThe effects of bluntness were found to be small. Also, the pressures produced by shock wave interactions with the boundary layer, and the inviscid pressures generated by the blunt leading edges, were found to be small compared with the inviscid pressures producing lift on the basic wing. Spanwise pressure distributions show no similarity to those obtained by linearized theory. Centerline lower surface pressure in pitch at zero yaw is bracketed between the Newtonian value \u0394P/q = 2(w/V)^2 and the two-dimensional exact value.", "date": "2015-10-29", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151028-155529477", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151028-155529477", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-19" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "No._45.pdf", "url": "https://authors.library.caltech.edu/records/x067c-8b522/files/No._45.pdf" }, "pub_year": "2015", "author_list": "Nicholson, Kenneth F." }, { "id": "https://authors.library.caltech.edu/records/0zcj4-g5c93", "eprint_id": 61618, "eprint_status": "archive", "datestamp": "2023-08-19 03:05:55", "lastmod": "2024-01-13 16:26:44", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Demetriades-A", "name": { "family": "Demetriades", "given": "Anthony" } } ] }, "title": "An Experimental Investigation of the Stability of the Hypersonic Laminar Boundary Layer", "ispublished": "unpub", "full_text_status": "public", "note": "Hypersonic Research Project Memorandum No. 43. Army Ordnance Contract No. DA-04-495-Ord-19. Army Project No. 5B0306004. Ordnance Proejct No. TB3-0118. OOR Project No. 1600-PE.\n\nSubmitted - No._43.pdf
", "abstract": "An experimental investigation of the stability of the hyper sonic laminar boundary layer was carried out for the case of a flat insulated surface at zero angle of attack. The stream-wise amplitude variation of both \"natural\" disturbances (i.e., flow fluctuations existing naturally in the boundary layer) and of disturbances artificially excited with a \"siren\" mechanism was studied with the aid of a hot-wire anemometer. In both cases it was found that such small fluctuations amplify for certain ranges of the fluctuation frequency and the Reynolds number R_\u0398, and damp for others. The demarcation boundaries for the amplification (instability) zone were found to resemble the corresponding boundaries of boundary layer instability at lower speeds. A \"line of maximum amplification\" of disturbances was also found. The amplification rates and hence the degree of \"selectivity\" of the hypersonic layer were found, however, to be considerably lower than those at the lower speeds. The disturbances selected by the layer for maximum amplification have a wavelength estimated at about twenty times the boundary-layer thickness \u03b4, which is appreciably longer than the corresponding wave-lengths for low- speed boundary-layer flow.", "date": "2015-10-28", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151027-165851254", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151027-165851254", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-19" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "No._43.pdf", "url": "https://authors.library.caltech.edu/records/0zcj4-g5c93/files/No._43.pdf" }, "pub_year": "2015", "author_list": "Demetriades, Anthony" }, { "id": "https://authors.library.caltech.edu/records/df7cq-am353", "eprint_id": 61617, "eprint_status": "archive", "datestamp": "2023-08-19 03:01:35", "lastmod": "2024-01-13 16:26:42", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Rabinowicz-J", "name": { "family": "Rabinowicz", "given": "Josef" } } ] }, "title": "Measurement of Turbulent Heat Transfer Rates on the Aft Portion and Blunt Base of a Hemisphere-Cylinder in the Shock Tube", "ispublished": "unpub", "full_text_status": "public", "note": "Hypersonic Research Project Memorandum No. 41. Army Ordnance Contract No. DA-04-495-Ord-19. Army Project No. 5B0306004 Ordnance Project No. TB3-0118. OOR Project No. 1600-PE.\n\nSubmitted - No._41.pdf
", "abstract": "Turbulent heat transfer rates on the aft portion and on the blunt base of a hemisphere cylinder were measured in the 2-7/8\" x 2-7/8\" GALCIT shock tube over a range of shock Mach numbers between 3. 25 and 5. 1 and initial pressures between 3 and 17 em. Hg. The local Reynolds numbers on the cylindrical afterbody varied between 3.5 x 10^4 and 3.0 x 10^5 per em. A side support was used for the model in order to eliminate the disturbing effect of a rear sting support. \n\nThe measured turbulent heat transfer rates on the cylindrical portion agreed very well with previous flat plate measurements for small temperature differences, although the ratio of stagnation to surface enthalpy varied between 3 to 8 in the present tests. Only a slight effect of this large variation in h_s/h_w was detected in this range of local Mach numbers, i.e., 1.25 < M_e < 1.5. The measured heat transfer rate on the base indicated that at the center of the base the heat transfer rate is comparable to that on the surface just ahead of the base, while the heat transfer rate falls off to 1/2 to 1/3 of this value towards the rim of the base. This unexpected distribution of\nheat transfer rate over the base, and particularly the high value at the center, shows the necessity for a careful study of wake phenomena.", "date": "2015-10-28", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151027-165358956", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151027-165358956", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-19" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "No._41.pdf", "url": "https://authors.library.caltech.edu/records/df7cq-am353/files/No._41.pdf" }, "pub_year": "2015", "author_list": "Rabinowicz, Josef" }, { "id": "https://authors.library.caltech.edu/records/yge61-bnq32", "eprint_id": 58019, "eprint_status": "archive", "datestamp": "2023-08-19 02:53:51", "lastmod": "2023-10-23 18:00:09", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Yang-H-T", "name": { "family": "Yang", "given": "Hsun-Tiao" } }, { "id": "Lees-L", "name": { "family": "Lees", "given": "Lester" } } ] }, "title": "Plane Couette Flow at Low Mach Number According to the Kinetic Theory of Gases", "ispublished": "unpub", "full_text_status": "public", "note": "Hypersonic Research Project Memorandum No. 36 February 1, 1957. \n\nArmy Ordnance Contract No. DA-04-495-Ord-19 Army Project No. 5B0306004 Ordnance Project No. TB3-0118 OOR Project No. 1600-PE.\n\nA portion of this study was completed after Dr. Yang had taken up his new post as Research Associate at the Institute for Fluid Dynamics and Applied Mathematics, University of Maryland. The support of Dr. Yang's work at Maryland by the Office of Scientific Research, Air Research and Development Command, U. S. A. F., under Contract AF 18(600)933, is gratefully acknowledged.\n\nSubmitted - Memorandum_No._36.pdf
", "abstract": "The thirteen-moment approximation developed by H. Grad\nfor solving the Maxwell-Boltzmann equation is applied to the problem of the relative shearing motion between two infinite, parallel flat plates (plane Couette flow). In order to bring out the molecular effects as directly as possible the problem is linearized by requiring\nthat the Mach number is small compared with unity, and that the temperature difference between the two plates is small compared with ambient temperature. According to the linearized Grad equations the shear stress in this case is given by the usual Navier-Stokes relation for all values of the parameter Re/M, in agreement with R. A.\nMillikan's postulate. Also the linearized boundary conditions for this problem are identical with the Maxwell slip relations utilized by Millikan, so the same expressions for slip velocity and drag coefficient\nare obtained. An examination of the drag data obtained by Kuhlthau, Chiang, and Bowyer and Talbot in their rotating-cylinder experiments at low densities shows that the variation of 1/C_DM with Re/M is predicted reasonably well by this theory over a range of Mach numbers\nfrom 0.15 to 1.40, in spite of the fact that the theory is supposed to hold only for low Mach numbers.", "date": "2015-06-05", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20150604-152209034", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20150604-152209034", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-19" }, { "agency": "Air Force Office of Scientific Research (AFOSR)", "grant_number": "AF 18(600)933" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "Memorandum_No._36.pdf", "url": "https://authors.library.caltech.edu/records/yge61-bnq32/files/Memorandum_No._36.pdf" }, "pub_year": "2015", "author_list": "Yang, Hsun-Tiao and Lees, Lester" }, { "id": "https://authors.library.caltech.edu/records/kjc40-8wh49", "eprint_id": 57989, "eprint_status": "archive", "datestamp": "2023-08-19 02:58:05", "lastmod": "2023-10-23 17:58:30", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Rabinowicz-J", "name": { "family": "Rabinowicz", "given": "Josef" } } ] }, "title": "Aerodynamic Studies in the Shock Tube", "ispublished": "unpub", "full_text_status": "public", "note": "Hypersonic Research Project Memorandum No. 38. Army Ordnance Contract NO. DA-04-495-Ord-19. Army Project No. 5B0306004. Ordnance Project No. TB3-0118. OOR Project No. 1600-PE.\n\nSubmitted - Memorandum_No._38.pdf
", "abstract": "In order to utilize the shock tube for quantitative investigations of some aerodynamic problems a thin platinum film resistance thermometer was developed for heat transfer rate measurements. The present report describes the construction and calibration of the heat transfer\ngage. Since the experimental technique presents a major problem this investigation has been carried out in the straight section of the shock tube where the flow conditions are well defined and readily\nmeasured. These flow conditions were calculated utilizing the most recent NBS data on air properties at high temperatures. The flow conditions were also measured utilizing the heat transfer gage and several independent experimental techniques, and good agreement was\nfound with the equilibrium flow calculations after an initial period of 30 - 50 \u03bc sec. Measurements of the heat transfer rate at the forward stagnation point and on the circumference of a circular cylinder are\nreported and compared with the theoretical calculations of L. Lees. A method for deduction of surface pressure distribution from the laminar boundary-layer heat transfer data is also presented.", "date": "2015-06-04", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20150603-141245900", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20150603-141245900", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-19" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "Memorandum_No._38.pdf", "url": "https://authors.library.caltech.edu/records/kjc40-8wh49/files/Memorandum_No._38.pdf" }, "pub_year": "2015", "author_list": "Rabinowicz, Josef" }, { "id": "https://authors.library.caltech.edu/records/fyx7f-hd978", "eprint_id": 57991, "eprint_status": "archive", "datestamp": "2023-08-19 02:58:13", "lastmod": "2023-10-23 17:58:36", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Richmond-R-L", "name": { "family": "Richmond", "given": "Ronald L." } } ] }, "title": "Experimental Investigation of Thick, Axially Symmetric Boundary Layers on Cylinders at Subsonic and Hypersonic Speeds", "ispublished": "unpub", "full_text_status": "public", "note": "Hypersonic Research Project Memorandum No. 39.\n\nArmy Ordnance contract No. DA-04-495-Ord-19. Army Project No. 5B0306004 Ordnance Project No. TB3-0118 OOR Project No. 1600-PE.\n\nSubmitted - Memorandum_No._39.pdf
", "abstract": "An experimental investigation of the transverse curvature\neffect on laminar and turbulent axially symmetric boundary layers was conducted in two subsonic wind tunnels and in the GALCIT 5 x 5 inch hyper sonic wind tunnel.\n\nSubsonic turbulent skin friction coefficients were estimated\nfrom velocity profiles with axial flow on a 0.024 inch diameter cylinder and a 1.00 inch diameter cylinder. A considerable increase\nover the flat plate skin friction coefficient at the same momentum thickness Reynolds number was found.\n\nHypersonic laminar and turbulent skin friction coefficients\nwith axial flow on an insulated 0.250 inch diameter cylinder were measured by the floating element technique and indicated, respectively, several times, and 1.5 times the laminar and turbulent flat plate skin friction coefficients at the same momentum thickness Reynolds numbers. Turbulent skin friction coefficients were\nestimated from pi tot profiles with axial flow on a 0.064 inch diameter cylinder and on a 0.024 inch diameter cylinder at M_1 = 5. 8 and indicate double the value to be found for an insulated flat plate at the same momentum thickness Reynolds number.", "date": "2015-06-04", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20150603-143924703", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20150603-143924703", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-19" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "Memorandum_No._39.pdf", "url": "https://authors.library.caltech.edu/records/fyx7f-hd978/files/Memorandum_No._39.pdf" }, "pub_year": "2015", "author_list": "Richmond, Ronald L." }, { "id": "https://authors.library.caltech.edu/records/5w7dm-4fx84", "eprint_id": 57990, "eprint_status": "archive", "datestamp": "2023-08-19 02:34:22", "lastmod": "2023-10-23 17:58:33", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Baloga-P-E", "name": { "family": "Baloga", "given": "Paul E." } }, { "id": "Nagamatsu-H-T", "name": { "family": "Nagamatsu", "given": "Henry T." } } ] }, "title": "Instrumentation of GALCIT Hypersonic Wind Tunnels", "ispublished": "unpub", "full_text_status": "public", "note": "Contract No. DA-04-495-Ord-19 Army Ordnance Department Sponsored by Army Ordnance and Air Force. Memorandum No. 29.\n\nSubmitted - Memorandum_No._29.pdf
", "abstract": "For the purpose of developing more efficient rockets and missiles for long ranges, it is necessary to acquire basic information 1n the hypersonic Mach number range of 5 to 20. To obtain such aerodynamic information two Hypersonic Wind Tunnels, Legs No. 1 and No. 2, have been\ndeveloped at GALCIT. With Leg No. 2 it is possible to obtain aerodynamic information in one-phase air flow at a Mach number of about 11. \n\nDuring the early operation of the Leg No. 1 tunnel at a Mach\nnumber range of 2 to 7 it was necessary to develop various new experimental techniques to obtain reliable aerodynamic information. The static pressures in the test section varied in the hypersonic Mach number range from about 2 to 1/4 millimeters of mercury while the static temperature was of the on the order of room temperature to 1100\u00b0F. A great\ndeal or time was spent in developing manometer boards and special valves and in perfecting new techniques for measuring these low pressures very accurately. The initial operation phase or the Leg No. 1 tunnel was\nspent in developing adequate hypersonic instrumentation for static pressure, total head, heating facilities, and a stagnation temperature controller.\n\nIn this report. the important instrumentation developed over the past few years will be discussed in detail. The information should be useful for other groups planning basic research at hypersonic Mach numbers.", "date": "2015-06-04", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20150603-143131825", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20150603-143131825", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "U.S. Army Office of Ordnance", "grant_number": "DA-04-495-Ord-19" }, { "agency": "U. S. Air Force" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "Memorandum_No._29.pdf", "url": "https://authors.library.caltech.edu/records/5w7dm-4fx84/files/Memorandum_No._29.pdf" }, "pub_year": "2015", "author_list": "Baloga, Paul E. and Nagamatsu, Henry T." }, { "id": "https://authors.library.caltech.edu/records/03mef-k2a89", "eprint_id": 62663, "eprint_status": "archive", "datestamp": "2023-08-19 04:44:32", "lastmod": "2024-01-13 16:29:19", "type": "monograph", "metadata_visibility": "show", "creators": { "items": [ { "id": "Bienkowski-G", "name": { "family": "Bienkowski", "given": "George" } } ] }, "title": "Propagation of an Initial Density Discontinuity", "ispublished": "unpub", "full_text_status": "public", "note": "Contract No. DA-31-124-ARO(D)-33 U. S. Army Research Office and the advanced Projects Agency. This research is part of Project DEFENDER sponsored by the Advanced Research Projects Agency.\n\nThe author would also like to acknowledge the help of the National Science Foundation under a Post-Doctoral Fellowship for 1961-1962.\n\nSubmitted - Propagation_of_an_Initial_Density_Discontinuity-Memorandum_No_70.pdf
", "abstract": "The propagation of an initial one-dimensional density\ndiscontinuity is studied. The solution for times much shorter than the mean free time between collisions (i.e. collisionless), and the solution for times much longer than the mean free time (i.e. Euler)\nare functions of the same similarity variable x/t. They differ only in the details f the profiles.\n\nA method for evaluating the first effect of collisions is\ndeveloped as an expansion in time with coefficients as functions of the similarity variable. The solutions are obtained in detail for both the Krook collision model and the exact collision integral for inverse fifth-power repulsion.\n\nThe Krook model is found to agree qualitatively with the \"exact\" solution except in the region of eventual shock formation for high initial density ratios. In that region the Krook model tends to overestimate the effect of collisions. The first effect of collisions in general alters\nthe free molecular solution in the proper direction towards the Navier-Stokes result. The \"first collision\" solution appears to be valid up to times of the order of a mean free time between collisions on the high pressure side.\n\nAnalysis of the long time solution through the Navier-Stokes\nequations under the assumption of no interaction between the shock and contact surface indicates that the Euler solution is not relevant until times of the order of 1,000 mean free times. The no-interaction Navier-Stokes solution is valid for times in excess of 50 mean free times.\nThe transition from the \"short-time\", first collision solution to this \"long-time\" no-interaction Navier-Stokes solution takes place in a time interval between 1 and 50 collisions per particle. One concludes that\nthe major part of this transition to the \"long-time\" solution must take place within that part of the Navier-Stokes regime where the shock, contact surface and expansion wave are not distinct but interact with\neach other.", "date": "1964-05-15", "date_type": "published", "publisher": "California Institute of Technology", "id_number": "CaltechAUTHORS:20151207-152322249", "official_url": "https://resolver.caltech.edu/CaltechAUTHORS:20151207-152322249", "rights": "No commercial reproduction, distribution, display or performance rights in this work are provided.", "funders": { "items": [ { "agency": "Army Research Office (ARO)", "grant_number": "DA-31-124-ARO(D)-33" }, { "agency": "Advanced Research Projects Agency (ARPA)" }, { "agency": "NSF Postdoctoral Fellowship" } ] }, "local_group": { "items": [ { "id": "Hypersonic-Research-Project" } ] }, "primary_object": { "basename": "Propagation_of_an_Initial_Density_Discontinuity-Memorandum_No_70.pdf", "url": "https://authors.library.caltech.edu/records/03mef-k2a89/files/Propagation_of_an_Initial_Density_Discontinuity-Memorandum_No_70.pdf" }, "pub_year": "1964", "author_list": "Bienkowski, George" } ]