This report has three main purposes:
\r\n\r\n1. To establish an engineering computation procedure for predicting CM(c.g.) as a function of CL for a multi-engine monoplane of conventional configuration with tractor propellers mounted on and forward of the wing.
\r\n\r\n2. To recommend aircraft configurations which will minimize the destabilizing effect of power.
\r\n\r\n3. To provide a physical explanation for the effect of power on stability.
" }, { "name": "Whitmore, Quentin Robert", "degree": "Masters", "year": "1947", "title": "Experimental Investigation of Temperature and Velocity Distribution About a Rocket Jet", "advisor": "Unknown, Unknown", "url": "https://resolver.caltech.edu/CaltechETD:etd-12092008-140117", "creators": [ { "name": { "family": "Whitmore", "given": "Quentin Robert" }, "id": "Whitmore-Quentin-Robert", "display_name": "Whitmore, Quentin Robert" } ], "advisors": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics", "eleceng" ], "doi": "10.7907/SN1E-KS25", "abstract": "The purpose of the investigation was to determine the temperature distribution and velocity profile surrounding the wake of a 1500 pound thrust liquid rocket motor. The temperature measurements were restricted to those 500\u00b0F and below. The velocities measured were in the region in which the temperature measurements were made.\r\n\r\nThe region in which the temperatures exceeded 500\u00b0F was found to be included within a solid angle of ten degrees. The high temperature region was found to be larger than the high velocity region.\r\n\r\nThe investigation was carried out during the academic year 1946-1947 at GALCIT Jet Propulsion Laboratory under the supervision of Dr. Robert H. Boden.\r\n" }, { "name": "Hege, Jeremiah Collins", "degree": "Masters", "year": "1945", "title": "An Experimental Investigation of the Effect of Lip on the Column Strength of Rolled Sheet Zee and Angle Sections", "advisor": "Sechler, Ernest Edwin", "url": "https://resolver.caltech.edu/CaltechTHESIS:05242011-153838445", "creators": [ { "name": { "family": "Hege", "given": "Jeremiah Collins" }, "id": "Hege-Jeremiah-Collins", "display_name": "Hege, Jeremiah Collins" }, { "name": { "family": "Goebel", "given": "Thomas Parker" }, "id": "Goebel-Thomas-Parker", "display_name": "Goebel, Thomas Parker" } ], "advisors": [ { "name": { "family": "Sechler", "given": "Ernest Edwin" }, "id": "Sechler-E-E", "role": "advisor", "display_name": "Sechler, Ernest Edwin" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/HM7P-CK04", "abstract": "The hat section used by certain of the aircraft companies has been quite widely accepted as the most efficient compression carrying member when stiffened by a sheet. However, due to the difficulty of inspection and corrosion control, which is particularly important in naval aircraft, the Consolidated Vultee Aircraft Corporation has for some time been using open angle and zee sections formed from dural sheet. For this reason the members of the engineering staff of Consolidated Vultee became interested in the effect of lips on zee and angle sections such as are frequently used to stiffen panels occurring in the compression side of semi-monocoque structures subjected to bending loads.
\r\n\r\nThis paper is an attempt to determine experimentally the optimum amount of lip for the sections under consideration. Sufficient tests are made to locate the column curves for these sections, and from the curves the strengthening effect of the lip noted.
" }, { "name": "Wayne, Jay C.", "degree": "Masters", "year": "1944", "title": "Flight Testing : Report", "advisor": "Millikan, Clark Blanchard", "url": "https://resolver.caltech.edu/CaltechTHESIS:06102025-185052730", "creators": [ { "name": { "family": "Wayne", "given": "Jay C." }, "id": "Wayne-Jay-C.", "display_name": "Wayne, Jay C." }, { "name": { "family": "Walkowicz", "given": "Teddy F." }, "id": "Walkowicz-Teddy-F.", "display_name": "Walkowicz, Teddy F." } ], "advisors": [ { "name": { "family": "Millikan", "given": "Clark Blanchard" }, "id": "Millikan-C-B", "role": "advisor", "display_name": "Millikan, Clark Blanchard" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/xez2-cg73", "abstract": "No abstract." }, { "name": "Belsley, Steven Eric", "degree": "Masters", "year": "1940", "title": "The Determination of Two Parameters Dealing with Power-On Stability for a Model with Right Hand Propellers", "advisor": "Millikan, Clark Blanchard", "url": "https://resolver.caltech.edu/CaltechETD:etd-11142008-131655", "creators": [ { "name": { "family": "Belsley", "given": "Steven Eric" }, "id": "Belsley-Steven-Eric", "display_name": "Belsley, Steven Eric" } ], "advisors": [ { "name": { "family": "Millikan", "given": "Clark Blanchard" }, "id": "Millikan-C-B", "role": "advisor", "display_name": "Millikan, Clark Blanchard" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/RPDT-VM86", "abstract": "This work presents expressions for determining the down-wash over the tail and the tail efficiency power-on and off. A method for the determination of empirical constants used by Millikan is presented. The method gives excellent agreement for the multiplicative factor Ap and good agreement for Bp. The theory checks experiment very well as Ap and Bp are nearly independent of Tc. " }, { "name": "Fischer, Harold S.", "degree": "Masters", "year": "1940", "title": "An Application of Matrix Methods to Wing Theory", "advisor": "von K\u00e1rm\u00e1n, Theodore; Sears, William Rees", "url": "https://resolver.caltech.edu/CaltechETD:etd-11142008-094640", "creators": [ { "name": { "family": "Fischer", "given": "Harold S." }, "id": "Fischer-Harold-S", "display_name": "Fischer, Harold S." } ], "advisors": [ { "name": { "family": "von K\u00e1rm\u00e1n", "given": "Theodore" }, "id": "von-K\u00e1rm\u00e1n-Th", "role": "advisor", "display_name": "von K\u00e1rm\u00e1n, Theodore" }, { "name": { "family": "Sears", "given": "William Rees" }, "id": "Sears-W-R", "role": "advisor", "display_name": "Sears, William Rees" } ], "committee": [ { "name": { "family": "von K\u00e1rm\u00e1n", "given": "Theodore" }, "id": "von-K\u00e1rm\u00e1n-Th", "role": "chair", "display_name": "von K\u00e1rm\u00e1n, Theodore" }, { "name": { "family": "Stewart", "given": "Homer Joseph" }, "id": "Stewart-H-J", "role": "member", "display_name": "Stewart, Homer Joseph" }, { "name": { "family": "Rannie", "given": "W. Duncan" }, "id": "Rannie-W-D", "role": "member", "display_name": "Rannie, W. Duncan" }, { "name": { "family": "Sears", "given": "William Rees" }, "id": "Sears-W-R", "role": "member", "display_name": "Sears, William Rees" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/E1VN-SQ19", "abstract": "The calculation of spanwise lift distribution of a wing by a new method proposed by Theodore von Karman and W. R. Sears* depends on knowledge of certain \"characteristic values\" (eigenvalues) and \"characteristic functions\" (eigenfunctions) of the wing planform. These functions are solutions of a homogeneous boundary-value problem of the third kind.
\r\n\r\nIn the present paper the eigenvalues and the eigenfunctions, in series form, are calculated for a class of planforms by the method of successive multiplication of matrices.
\r\n\r\nThe class of planforms considered is that of trapezoidal wings with rounded tips. The eigenvalues and eigenfunctions are calculated for taper ratios 1:1, 2:1, 3:1, and 4:1; they are independent of aspect ratio. It is found, that for intermediate taper ratios they can be determined with reasonable accuracy by graphical interpolation.
\r\n\r\n* To be published shortly.
" }, { "name": "Fredrick, Joseph Louis", "degree": "Masters", "year": "1940", "title": "The Failure of Thin-Walled Semi-Elliptical Cylinders Under Torsion", "advisor": "von K\u00e1rm\u00e1n, Theodore; Sechler, Ernest Edwin", "url": "https://resolver.caltech.edu/CaltechETD:etd-11132008-142412", "creators": [ { "name": { "family": "Fredrick", "given": "Joseph Louis" }, "id": "Fredrick-Joseph-Louis", "display_name": "Fredrick, Joseph Louis" } ], "advisors": [ { "name": { "family": "von K\u00e1rm\u00e1n", "given": "Theodore" }, "id": "von-K\u00e1rm\u00e1n-Th", "role": "advisor", "display_name": "von K\u00e1rm\u00e1n, Theodore" }, { "name": { "family": "Sechler", "given": "Ernest Edwin" }, "id": "Sechler-E-E", "role": "advisor", "display_name": "Sechler, Ernest Edwin" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/31X1-Q070", "abstract": "This paper constitutes a report on one phase of an investigation sponsored by the National Advisory Committee for Aeronautics at the California Institute of Technology, namely, the determination of the allowable loads in wing nose-sections under the action of combined loading conditions. As intimated by the title, the material presented here has been limited to the case of pure torsion only, this choice being dictated by the present state of the experimental program and the interpretation of its results.\r\n\r\nThe experimental program itself consisted of the testing of specimens made up of two semi-elliptical (or semi-circular) segments of sheet supported and clamped at the ends of the minor axis of the ellipse, thus simulating two wing nose-sections mounted to a common spar and tested as a single unit. As a result of the testing of these specimens with varying ellipticity, sheet thickness, and length, sufficient experimental data was obtained to establish rational design curves for both the buckling and ultimate failure of semi-elliptical cylinders under torsion.\r\n\r\nSince the type of specimens used only approximated the shape of an actual wing nose-section, it was necessary to devise a means of relating the two structures, in order that the criteria presented in this paper could be used for actual design practice.\r\n\r\nSince a limited amount of torsion tests on actual wing assemblies was available to this author, it was used to check the validity of both the geometric relation devised between the two types of structures as mentioned above and the actual design criteria developed from the experimental results. The agreement obtained was quite good, thus substantiating the usefulness and reliability of the results presented in this paper.\r\n\r\nIn the light of the above results, it is believed that the experimental portion of the investigation has been satisfactorily completed, with the possible exception of determining the affect of stiffeners upon the strength of the cylinders under discussion. However, since this represents an entirely different field of study, it is beyond the scope of this present investigation and must be relegated to the future.\r\n\r\nAttempts were made to develop a theoretical verification of the results obtained, but due to the complexities of the problem, they met with little success for the present. Therefore, this task also remains as one to be completed as a part of any future work which may be undertaken.\r\n" }, { "name": "Gentner, William Ellis", "degree": "Masters", "year": "1940", "title": "A Study of the Effect of Repeated Tension Impact Loads Upon Certain Metals Used in Aircraft Construction", "advisor": "Sechler, Ernest Edwin", "url": "https://resolver.caltech.edu/CaltechTHESIS:04252011-080056433", "creators": [ { "name": { "family": "Gentner", "given": "William Ellis" }, "id": "Gentner-William-Ellis", "display_name": "Gentner, William Ellis" }, { "name": { "family": "Biglow", "given": "James Otis" }, "id": "Biglow-James-Otis", "display_name": "Biglow, James Otis" } ], "advisors": [ { "name": { "family": "Sechler", "given": "Ernest Edwin" }, "id": "Sechler-E-E", "role": "advisor", "display_name": "Sechler, Ernest Edwin" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/93VQ-ED36", "abstract": "The Impact Endurance Limit is evaluated for several materials used in aircraft construction. The Impact Endurance Limit is defined as the energy per blow in tension impact below which the specimen will withstand an indefinitely large number of blows without fracture.\r\n\r\nThe effect of grain orientation on the Impact Endurance Limit is shown.\r\n\r\nEvidence is presented that the Impact Endurance Limit may be a function of the ultimate tensile strength but not of the elongation or the yield point.\r\n\r\nThe effect of service stresses on the Impact Endurance Limit is discussed.\r\n" }, { "name": "Hatton, George Anthony", "degree": "Masters", "year": "1940", "title": "The Longitudinal Stability of a Flying-Boat in the Planing Condition as Computed from Tank Test Data of a Hull Model", "advisor": "von K\u00e1rm\u00e1n, Theodore; Millikan, Clark Blanchard", "url": "https://resolver.caltech.edu/CaltechETD:etd-11142008-082321", "creators": [ { "name": { "family": "Hatton", "given": "George Anthony" }, "id": "Hatton-George-Anthony", "display_name": "Hatton, George Anthony" } ], "advisors": [ { "name": { "family": "von K\u00e1rm\u00e1n", "given": "Theodore" }, "id": "von-K\u00e1rm\u00e1n-Th", "role": "advisor", "display_name": "von K\u00e1rm\u00e1n, Theodore" }, { "name": { "family": "Millikan", "given": "Clark Blanchard" }, "id": "Millikan-C-B", "role": "advisor", "display_name": "Millikan, Clark Blanchard" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/JR58-MH75", "abstract": "The question of \u201cporpoising\u201d of flying-boats has been the subject of investigation both abroad and in the United States. In Germany and England recourse has been had to the use of dynamically similar models, duplicating in the model as closely as possible all the features of the full scale flying-boat. In the towing tanks of the United States, usually a bare hull is tested, where measurements are made of resistance, load, trimming moment, and trim angle at various speeds. The results are usually furnished in the form of curves of trimming moment and draft against speed at various loadings and trim angles. Conclusions regarding \u201cporpoising\u201d of the full scale flying-boat cannot be drawn from the behavior of the hull alone, but it is considered possible to evaluate certain hydrodynamic stability derivatives, which, in conjunction with aerodynamic derivatives obtained from wind-tunnel tests, may be used in the stability equation to determine the behavior of the flying-boat in the planning condition.\r\n\r\nIn the following discussion the aerodynamic and hydrodynamic derivatives are deduced. The aerodynamic derivatives are similar to those normally used for airplanes, but they are evaluated in terms of beam, trim angle, and other hydrodynamic terms; then the hydrodynamic derivatives are deduced, also in terms of hull dimensions and attitudes. This permits direct addition of the hydrodynamic and aerodynamic derivatives for use in the longitudinal stability equation. The criteria of stability then are applied. In addition, a factorization of the stability quartic, formulated by Dr. Millikan, is applied to determine periods of the oscillations, as well as damping factors.\r\n\r\nAn example following the procedure above outlined and devised by Dr. Millikan is presented, using tank test data of a model 36 hull for hydrodynamic quantities. The aerodynamic quantities are based on an average of many modern flying-boats. The model 36 hull is selected as being fairly representative of present day flying boats.\r\n" }, { "name": "Koch, Walter Louis", "degree": "Masters", "year": "1940", "title": "An Experimental Investigation of Wind Tunnel Wall Interference on Rolling and Yawing Moments Due to Deflected Ailerons", "advisor": "von K\u00e1rm\u00e1n, Theodore; Millikan, Clark Blanchard", "url": "https://resolver.caltech.edu/CaltechETD:etd-10282005-141733", "creators": [ { "name": { "family": "Koch", "given": "Walter Louis" }, "id": "Koch-Walter-Louis", "display_name": "Koch, Walter Louis" } ], "advisors": [ { "name": { "family": "von K\u00e1rm\u00e1n", "given": "Theodore" }, "id": "von-K\u00e1rm\u00e1n-Th", "role": "advisor", "display_name": "von K\u00e1rm\u00e1n, Theodore" }, { "name": { "family": "Millikan", "given": "Clark Blanchard" }, "id": "Millikan-C-B", "role": "advisor", "display_name": "Millikan, Clark Blanchard" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/MN6W-EB71", "abstract": "Wind tunnel tests were made on a model wing with deflected ailerons in both open- and closed-jet configurations of a small wind tunnel. Rolling and yawing moments and lift were measured at various angles of attack. The wind tunnel wall interference on rolling and yawing moments is determined by comparison of the open- and closed-jet results. An approximate comparison with available theories is included. It appears that the interference effects measured are somewhat smaller than predicted by the theories.\r\n" }, { "name": "Kybal, Dalimil", "degree": "Masters", "year": "1940", "title": "The Aileron Influence on Wing Flutter", "advisor": "von K\u00e1rm\u00e1n, Theodore", "url": "https://resolver.caltech.edu/CaltechTHESIS:08212024-205858806", "creators": [ { "name": { "family": "Kybal", "given": "Dalimil" }, "id": "Kybal-Dalimil", "display_name": "Kybal, Dalimil" } ], "advisors": [ { "name": { "family": "von K\u00e1rm\u00e1n", "given": "Theodore" }, "id": "von-K\u00e1rm\u00e1n-Th", "role": "advisor", "display_name": "von K\u00e1rm\u00e1n, Theodore" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/46zn-zn97", "abstract": "No abstract." }, { "name": "Moyers, Frank Neff", "degree": "Masters", "year": "1940", "title": "A Comparison of Theoretical and Experimental Pressure Distributions at High Speed About the N.A.C.A. 4412 Airfoil", "advisor": "von K\u00e1rm\u00e1n, Theodore", "url": "https://resolver.caltech.edu/CaltechETD:etd-09152005-142724", "creators": [ { "name": { "family": "Moyers", "given": "Frank Neff" }, "id": "Moyers-Frank-Neff", "display_name": "Moyers, Frank Neff" } ], "advisors": [ { "name": { "family": "von K\u00e1rm\u00e1n", "given": "Theodore" }, "id": "von-K\u00e1rm\u00e1n-Th", "role": "advisor", "display_name": "von K\u00e1rm\u00e1n, Theodore" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/YTRV-NM88", "abstract": "The general problem of aerodynamics is the determination of the forces and moments imposed on a stationary body immersed in a moving fluid. The problem is soluble if a mathematical calculation of the velocity distribution throughout the fluid can be made. The application of certain restrictions facilitates the calculation. Without great loss of usefulness we may restrict the motion to a steady, uniform, and rectilinear flow from infinity. With considerable loss of usefulness but with tremendous simplification in calculation we may add the further restrictions that the fluid be non-viscous and incompressible. Upon these assumptions the problem may be solved by utilizing two physical relationships, namely, the equations of motion and continuity." }, { "name": "Nagamatsu, Henry Takeshi", "degree": "Masters", "year": "1940", "title": "Experimental Investigation of Ultimate Loads Carried by Flat, Unstiffened Panels Under Combined Shear and Compression", "advisor": "Sechler, Ernest Edwin", "url": "https://resolver.caltech.edu/CaltechETD:etd-11142008-140614", "creators": [ { "name": { "family": "Nagamatsu", "given": "Henry Takeshi" }, "id": "Nagamatsu-Henry-Takeshi", "display_name": "Nagamatsu, Henry Takeshi" } ], "advisors": [ { "name": { "family": "Sechler", "given": "Ernest Edwin" }, "id": "Sechler-E-E", "role": "advisor", "display_name": "Sechler, Ernest Edwin" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/FNQF-4Q12", "abstract": "NOTE: Text or symbols not renderable in plain ASCII are indicated by [...]. Abstract is included in .pdf document.\r\n\r\nThe behavior of flat, unstiffened panels was investigated for two length over width ratios and five thicknesses. In each case the panels were loaded until they failed. An empirical relation was developed for the variation of the ultimate combined shear and compression stress of the form [...].\r\n\t\r\nThe values of m and n were found to be: m = 1.65 and n = .9 for panels with length over width ratio equal to 2, and m = 1.4 and n = 1.3 for panels with length over width ratio equal to 1 1/3. The above equations agree very closely with the experimental results.\r\n\r\nThere was a variation in the apparent shear modulus under different combined loading conditions, but no definite result was obtained.\r\n" }, { "name": "Powell, Walter Brown", "degree": "Masters", "year": "1940", "title": "An Investigation of Some Problems in the Design of Tailless Airplanes", "advisor": "Millikan, Clark Blanchard; Sears, William Rees", "url": "https://resolver.caltech.edu/CaltechETD:etd-11252008-112304", "creators": [ { "name": { "family": "Powell", "given": "Walter Brown" }, "id": "Powell-Walter-Brown", "display_name": "Powell, Walter Brown" } ], "advisors": [ { "name": { "family": "Millikan", "given": "Clark Blanchard" }, "id": "Millikan-C-B", "role": "advisor", "display_name": "Millikan, Clark Blanchard" }, { "name": { "family": "Sears", "given": "William Rees" }, "id": "Sears-W-R", "role": "advisor", "display_name": "Sears, William Rees" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/PZW5-2085", "abstract": "Some problems in the design of tailless airplanes are discussed. The conditions essential to the flight of such airplanes are determined, and a survey of methods of calculating the aerodynamic characteristics of plain wings and wings with flaps and ailerons deflected is presented. The effect of adding a fuselage and ring nacelles to a wing to form a practical airplane is discussed.
\r\n\r\nConsideration is given to the problem of damping of longitudinal oscillations, and a method of calculating the damping in pitch of a sweptback wing alone is presented.
\r\n\r\nAn example is carried through to illustrate the application of all the material covered in the paper. In all respects considered, the tailless airplane is shown to be comparable to normal type airplanes.
" }, { "name": "Sparks, Brian Orville", "degree": "Masters", "year": "1940", "title": "The Effects of Vertical Gusts on an Elastic Wing", "advisor": "Sears, William Rees", "url": "https://resolver.caltech.edu/CaltechETD:etd-11142008-144847", "creators": [ { "name": { "family": "Sparks", "given": "Brian Orville" }, "id": "Sparks-Brian-Orville", "display_name": "Sparks, Brian Orville" } ], "advisors": [ { "name": { "family": "Sears", "given": "William Rees" }, "id": "Sears-W-R", "role": "advisor", "display_name": "Sears, William Rees" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/20SK-0031", "abstract": "The case of a wing flexible in bending and rigid in torsion entering a vertical gust is treated by consideration of the corresponding two-dimensional case. The bending stiffness of the wing is expressed as a spring constant, the aerodynamic forces acting are taken from the two-dimensional theory of airfoils in non-uniform motion, and the differential equation of motion of the wing is solved by operational methods.
\r\n\r\nCases of sharp-edged and exponentially graded gusts are considered, and in each case the deflection is calculated in dimensionless form for three values of a dimensionless stiffness parameter. As a numerical example these results are put into dimensional form for a wing whose elastic properties are supposed to be typical of modern airplane wings.
\r\n\r\nThe results obtained for the cases considered show only in one instance a maximum deflection greater than the steady-state value. Even in the sharp-gust case the deflection increases comparatively slowly following the entrance of the wing into the gust. The effects of grading the gust are to decrease slightly the rate of deflection and to reduce the amplitude of the oscillations produced by the gust.
" }, { "name": "Ashkenas, Irving Louis", "degree": "Masters", "year": "1939", "title": "Wind Tunnel Model Tests to Investigate the Effects of Boundary Layer Control", "advisor": "Millikan, Clark Blanchard; Sears, William Rees", "url": "https://resolver.caltech.edu/CaltechETD:etd-05222007-104409", "creators": [ { "name": { "family": "Ashkenas", "given": "Irving Louis" }, "id": "Ashkenas-Irving-Louis", "display_name": "Ashkenas, Irving Louis" }, { "name": { "family": "Smith", "given": "Robert Beaton" }, "id": "Smith-Robert-Beaton", "display_name": "Smith, Robert Beaton" } ], "advisors": [ { "name": { "family": "Millikan", "given": "Clark Blanchard" }, "id": "Millikan-C-B", "role": "advisor", "display_name": "Millikan, Clark Blanchard" }, { "name": { "family": "Sears", "given": "William Rees" }, "id": "Sears-W-R", "role": "advisor", "display_name": "Sears, William Rees" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/FE14-GP68", "abstract": "This thesis presents a study of the results obtained with the Boundary Layer Removal Model of the Guggenheim Aeronautics Laboratory, California Institute of Technology (GALCIT). It is a continuation of work begun here some time past and, as such, contains very little in the way of historical review, the origin of the project, preliminary studies of the problem and experimental technique being contained in previous reports.
\r\n\r\nThe attempt, in this series of tests, to find a definite scale effect on the power required to produce a given change in airfoil characteristics has been somewhat unsuccessful because the test Reynolds Numbers unfortunately fell in the region of critical Reynolds Number. There has, however, been some success in finding the definite mechanism by which boundary layer removal is effective, a logical explanation being given for the nature and magnitude of various changes in airfoil characteristics incurred by the use of a given amount of suction.
" }, { "name": "Beardsley, George Francis", "degree": "Masters", "year": "1939", "title": "A Study of the Effect of Repeated Tension Impact Loads Upon Certain Metals Used in Aircraft Construction", "advisor": "Sechler, Ernest Edwin", "url": "https://resolver.caltech.edu/CaltechETD:etd-01102006-132339", "creators": [ { "name": { "family": "Beardsley", "given": "George Francis" }, "id": "Beardsley-George-Francis", "display_name": "Beardsley, George Francis" }, { "name": { "family": "Coates", "given": "Leonidas Dixon" }, "id": "Coates-Leonidas-Dixon", "display_name": "Coates, Leonidas Dixon" } ], "advisors": [ { "name": { "family": "Sechler", "given": "Ernest Edwin" }, "id": "Sechler-E-E", "role": "advisor", "display_name": "Sechler, Ernest Edwin" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/R4GM-7G81", "abstract": "A test method is developed for evaluating the Impact Endurance Limit of a material. The Impact Endurance Limit is defined as the energy per blow in tensile impact loading below which the specimen will withstand an indefinitely large number of blows without rupture, and this value is given for ALCOA 24ST and 14ST, with and across the grain, and Dowmetals X and Z-1 with the grain. Evidence is presented that this value probably does not depend directly either on the energy absorbed in breaking in one blow or on the brittleness of the material.\r\n\r\nThe ability to absorb energy in failure under static loading is shown to decrease nearly linearly with dynamic strain, while the ability to carry design static load is not adversely affected by any amount of dynamic strain short of failure.\r\n\r\nSome shortcomings of the present test methods are pointed out and a new machine is briefly described which will be used in further investigation of repeated tension impact.\r\n\r\nCo-author: L.D. Coates" }, { "name": "Fan, Hsu-Tsi", "degree": "Masters", "year": "1939", "title": "A Study of \"Shear Lag\" Phenomenon in a Stiffened Flat Panel by Photoelastic Methods", "advisor": "von K\u00e1rm\u00e1n, Theodore; Sechler, Ernest Edwin", "url": "https://resolver.caltech.edu/CaltechETD:etd-12282005-161537", "creators": [ { "name": { "family": "Fan", "given": "Hsu-Tsi" }, "id": "Fan-Hsu-Tsi", "display_name": "Fan, Hsu-Tsi" } ], "advisors": [ { "name": { "family": "von K\u00e1rm\u00e1n", "given": "Theodore" }, "id": "von-K\u00e1rm\u00e1n-Th", "role": "advisor", "display_name": "von K\u00e1rm\u00e1n, Theodore" }, { "name": { "family": "Sechler", "given": "Ernest Edwin" }, "id": "Sechler-E-E", "role": "advisor", "display_name": "Sechler, Ernest Edwin" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/WANC-TP12", "abstract": "In the construction of modern metal airplanes there are many locations where a more or less concentrated load is transferred to a large area of material. Therefore the design-engineer is frequently confronted with the problem of \u201cshear lag.\u201d This problem can be treated in a few simple cases by the mathematical theory of elasticity, especially by Airy\u2019s stress functions, but in many other cases, in order to avoid mathematical complexities, certain assumptions must be made which will simplify the analytical solution of the problem. These assumptions usually do not agree with the actual conditions therefore the results are not adequate. By the photoelastic method, however, the results obtained by the mathematical theory can be checked. It is the purpose of this experiment to check the results which have been obtained by the theoretical investigation for a few simple cases." }, { "name": "Jackson, Andrew McBurney", "degree": "Masters", "year": "1939", "title": "An Investigation of Forced Flexural Torsional Oscillations of a Wing and the Phenomenon of Flutter", "advisor": "Unknown, Unknown", "url": "https://resolver.caltech.edu/CaltechETD:etd-03252005-082813", "creators": [ { "name": { "family": "Jackson", "given": "Andrew McBurney" }, "id": "Jackson-Andrew-McBurney", "display_name": "Jackson, Andrew McBurney" }, { "name": { "family": "Parish", "given": "Elliott Walter" }, "id": "Parish-Elliott-Walter", "display_name": "Parish, Elliott Walter" } ], "advisors": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/V7TP-Q228", "abstract": "In this thesis the torsional-flexural response of a two-dimensional airfoil to forced oscillations of various frequencies and at various airspeeds is investigated. The airfoil chosen has characteristics which are typical of modern American transport wings, and the speeds cover the range from zero airspeed up through the speeds for torsional-flexural flutter and torsional divergence.
\r\n\r\nIn the latter part of this thesis, curves are plotted showing the effects which changes in the assumed wing parameters have on the torsional-flexural flutter speed and the torsional divergence speed.
" }, { "name": "Kanemitsu, Sunao", "degree": "Masters", "year": "1939", "title": "Axial Compression Test of Thin Circular Cylinders. A. Length Effect. B. Visual Study of Buckling", "advisor": "Sechler, Ernest Edwin", "url": "https://resolver.caltech.edu/CaltechETD:etd-12052005-105325", "creators": [ { "name": { "family": "Kanemitsu", "given": "Sunao" }, "id": "Kanemitsu-Sunao", "display_name": "Kanemitsu, Sunao" }, { "name": { "family": "Nojima", "given": "Noble M." }, "id": "Nojima-Noble-M", "display_name": "Nojima, Noble M." } ], "advisors": [ { "name": { "family": "Sechler", "given": "Ernest Edwin" }, "id": "Sechler-E-E", "role": "advisor", "display_name": "Sechler, Ernest Edwin" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/HBZ9-MZ48", "abstract": "A: This portion of the report contains results obtained from compression tests on 95 thin-walled steel circular cylinder. The tested cylinders were mainly of very small L/R ratio and large R/t ratio.
\r\n\r\nThe results are compared with the existing theoretical failing stresses and are also presented in a non dimensional form, \u03b4/E. The failure stress is best given by the equation \u03b4/E = 9(t/R)1.6 + .16(T/L)1.3. This equation shall be limited for use for L/R greater than 0.1 and for L/R greater than 1.5 assume L/R = 1.5.
\r\n\r\nB: A visual study of buckle formation is presented to aid future research which may be done on compression of thin cylinders.
" }, { "name": "Piper, Clark Neil", "degree": "Masters", "year": "1939", "title": "Experimental Investigation of the Profile Drag and Boundary Layer of a Wing Section During Free Flight and in the Wind Tunnel", "advisor": "Millikan, Clark Blanchard", "url": "https://resolver.caltech.edu/CaltechETD:etd-01092006-142449", "creators": [ { "name": { "family": "Piper", "given": "Clark Neil" }, "id": "Piper-Clark-Neil", "display_name": "Piper, Clark Neil" } ], "advisors": [ { "name": { "family": "Millikan", "given": "Clark Blanchard" }, "id": "Millikan-C-B", "role": "advisor", "display_name": "Millikan, Clark Blanchard" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/DSRZ-HZ95", "abstract": "A general report covering the method used in obtaining flight test and wind tunnel data for the investigation of profile drag and the thickness of the boundary layer with its transition point is presented, together with some of the results and conclusions reached.\r\n\r\nMethods of data reduction with the difficulties encountered are given. After final results of the profile drag for flight test are obtained, they are compared with T. N. 695.\r\n\r\nA detailed description of the apparatus with the technique used for both the flight tests and the wind tunnel is also presented.\r\n" }, { "name": "Tsubota, George Yoshio", "degree": "Masters", "year": "1939", "title": "Experimental Investigation of Ultimate Loads Carried by Flat, Unstiffened Panels Under Combined Shear and Compression", "advisor": "Sechler, Ernest Edwin", "url": "https://resolver.caltech.edu/CaltechETD:etd-12222005-104133", "creators": [ { "name": { "family": "Tsubota", "given": "George Yoshio" }, "id": "Tsubota-George-Yoshio", "display_name": "Tsubota, George Yoshio" } ], "advisors": [ { "name": { "family": "Sechler", "given": "Ernest Edwin" }, "id": "Sechler-E-E", "role": "advisor", "display_name": "Sechler, Ernest Edwin" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/ZDZH-Y940", "abstract": "NOTE: Text or symbols not renderable in plain ASCII are indicated by [...]. Abstract is included in .pdf document.\r\n\r\nThe problem of the behavior of flat, unstiffened panels under combined shear and compression load was investigated for one length over width ratio and three thicknesses. Due to the lack of data obtained in a limited amount of time, no definite conclusion was reached. Until further investigation is carried out, the ultimate failure stress relationship of [...] is recommended. The effect of shear load on the modulus of elasticity and compression load on the shear modulus was found to be nonexistent.\r\n" }, { "name": "Wang, Tsun-Kuei", "degree": "Masters", "year": "1939", "title": "A Theoretical Investigation of the Distribution of Maximum Shearing Stresses in a Stiffened Flat Panel", "advisor": "von K\u00e1rm\u00e1n, Theodore", "url": "https://resolver.caltech.edu/CaltechETD:etd-04142008-083306", "creators": [ { "name": { "family": "Wang", "given": "Tsun-Kuei" }, "id": "Wang-Tsun-Kuei", "display_name": "Wang, Tsun-Kuei" } ], "advisors": [ { "name": { "family": "von K\u00e1rm\u00e1n", "given": "Theodore" }, "id": "von-K\u00e1rm\u00e1n-Th", "role": "advisor", "display_name": "von K\u00e1rm\u00e1n, Theodore" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/A1JY-DH94", "abstract": "No abstract submitted.\r\n" }, { "name": "Bell, Willard Newton", "degree": "Masters", "year": "1938", "title": "A Photoelastic Investigation of the Distribution of Shearing Stresses in a Stiffened Flat Panel", "advisor": "Sechler, Ernest Edwin; von K\u00e1rm\u00e1n, Theodore", "url": "https://resolver.caltech.edu/CaltechETD:etd-01102006-131047", "creators": [ { "name": { "family": "Bell", "given": "Willard Newton" }, "id": "Bell-Willard-Newton", "display_name": "Bell, Willard Newton" }, { "name": { "family": "Bussey", "given": "John Kenneth" }, "id": "Bussey-John-Kenneth", "display_name": "Bussey, John Kenneth" } ], "advisors": [ { "name": { "family": "Sechler", "given": "Ernest Edwin" }, "id": "Sechler-E-E", "role": "advisor", "display_name": "Sechler, Ernest Edwin" }, { "name": { "family": "von K\u00e1rm\u00e1n", "given": "Theodore" }, "id": "von-K\u00e1rm\u00e1n-Th", "role": "advisor", "display_name": "von K\u00e1rm\u00e1n, Theodore" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/9JFS-SF60", "abstract": "No abstract.\r\n" }, { "name": "Berler, Irving", "degree": "Masters", "year": "1938", "title": "The Elastic Properties of 17ST Aluminum Alloy Tubing Including the Effects of Prestressing", "advisor": "Sechler, Ernest Edwin", "url": "https://resolver.caltech.edu/CaltechTHESIS:02272025-192811948", "creators": [ { "name": { "family": "Berler", "given": "Irving" }, "id": "Berler-Irving", "display_name": "Berler, Irving" } ], "advisors": [ { "name": { "family": "Sechler", "given": "Ernest Edwin" }, "id": "Sechler-E-E", "role": "advisor", "display_name": "Sechler, Ernest Edwin" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/cz5j-jz92", "abstract": "No abstract." }, { "name": "Bowen, William Harold", "degree": "Masters", "year": "1938", "title": "Tests of Axial Flow Fans Designed by Lattice Theory", "advisor": "von K\u00e1rm\u00e1n, Theodore", "url": "https://resolver.caltech.edu/CaltechETD:etd-02122007-144119", "creators": [ { "name": { "family": "Bowen", "given": "William Harold" }, "id": "Bowen-William-Harold", "display_name": "Bowen, William Harold" } ], "advisors": [ { "name": { "family": "von K\u00e1rm\u00e1n", "given": "Theodore" }, "id": "von-K\u00e1rm\u00e1n-Th", "role": "advisor", "display_name": "von K\u00e1rm\u00e1n, Theodore" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/M6E1-0T44", "abstract": "This paper presents the tests and calibrations which were made on three axial flow fan units of the G.A.L.C.I.T. Boundary Layer Removal Model in order that operating parameters might be developed from the data. The tests serve also as a check on the success achieved in the design of fans using the Lattice Theory. (cf. Theoretical Aerodynamics Lecture Notes of Dr. Clark B. Millikan).\r\n" }, { "name": "Butterworth, Wesley Theodore", "degree": "Masters", "year": "1938", "title": "Experimental Investigation of Ultimate Loads Carried by Flat, Unstiffened Panels Under Combined Shear and Compression", "advisor": "Sechler, Ernest Edwin", "url": "https://resolver.caltech.edu/CaltechETD:etd-12282005-095455", "creators": [ { "name": { "family": "Butterworth", "given": "Wesley Theodore" }, "id": "Butterworth-Wesley-Theodore", "display_name": "Butterworth, Wesley Theodore" } ], "advisors": [ { "name": { "family": "Sechler", "given": "Ernest Edwin" }, "id": "Sechler-E-E", "role": "advisor", "display_name": "Sechler, Ernest Edwin" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/C57T-2C92", "abstract": "Four series of tests were made on flat, unstiffened panels under combined shear and compression loading for two thicknesses and two length over width ratios. In each case, the panels were carried to their ultimate loads. An empirical relation was developed for the variation of shear and compressive stresses of the form: (Pc/Pco) + (Ps/Pso)4 = 1,
\r\nwhere:
\r\nPco = failure stress, pure compression,
\r\nPso = failure stress, pure shear.
\r\nThe above equation was found to hold for the entire range of thicknesses and length over width ratios investigated.
The extensive use of reinforced duralumin sheet in aircraft construction makes it desirable to know the behaviour of such structures under load. This paper deals principally with the experimental results obtained by testing a large number of reinforced panels of various lengths under direct compression.
\r\n\r\nThe main purpose of the investigation was to determine the ultimate stresses in the reinforcing members, which in this case were bulb-angles of a size commonly used in aircraft constrution. It was, however, felt that it would be desirable to obtain as much information from the tests as possible. Consequesntly the stresses in the bulb-angles were measured at intermediate loads for a number of panels. From this data it was possible to determine that portion of the total load carried by either the skin or the bulb-angles throughout the entire range of load.
\r\n" }, { "name": "Dykes, John Christopher", "degree": "Masters", "year": "1938", "title": "Stability Derivatives of Helicopter Rotors", "advisor": "von K\u00e1rm\u00e1n, Theodore", "url": "https://resolver.caltech.edu/CaltechETD:etd-10282005-161504", "creators": [ { "name": { "family": "Dykes", "given": "John Christopher" }, "id": "Dykes-John-Christopher", "display_name": "Dykes, John Christopher" } ], "advisors": [ { "name": { "family": "von K\u00e1rm\u00e1n", "given": "Theodore" }, "id": "von-K\u00e1rm\u00e1n-Th", "role": "advisor", "display_name": "von K\u00e1rm\u00e1n, Theodore" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/N0GE-EA65", "abstract": "At present there are only three published papers dealing with the stability of helicopters, all based on helicopters with rigid rotors. Since all rotors are, in practice, constructed with the blades free to \"flap\", these analyses are not sufficiently general.
\r\n\r\nBelow, the blade motion equation has been written in terms of small incremental accelerations and velocities; for which an approximate solution is obtained. This is then used to calculate the actual forces and moments that are produced on the rotor; by taking suitable mean values, it has been found possible to express these forces and moments without reference to the actual position of the blades at that instant, but only as functions of the position of the whole helicopter. The aerodynamic mechanism of the rotor has therefore been expressed in a a series of equations, and the stability of the helicopter now becomes solely a dynamical problem.
\r\n\r\nIt appears that a helicopter is most likely to become unstable when hovering; this analysis is confined to this case.
\r\n\r\nCalculated values for a helicopter of the same size as the \"C.30\" autogyro, are given to show the dimensions of the various forces and moments.
" }, { "name": "Mechling, Wallace Bristol", "degree": "Masters", "year": "1938", "title": "An Evaluation of the Tension Impact Test by Correlation With the Physical Properties of Aluminum Alloys", "advisor": "von K\u00e1rm\u00e1n, Theodore; Sechler, Ernest Edwin", "url": "https://resolver.caltech.edu/CaltechETD:etd-07192007-104706", "creators": [ { "name": { "family": "Mechling", "given": "Wallace Bristol" }, "id": "Mechling-Wallace-Bristol", "display_name": "Mechling, Wallace Bristol" }, { "name": { "family": "Jack", "given": "Samuel Sloan" }, "id": "Jack-Samuel-Sloan", "display_name": "Jack, Samuel Sloan" } ], "advisors": [ { "name": { "family": "von K\u00e1rm\u00e1n", "given": "Theodore" }, "id": "von-K\u00e1rm\u00e1n-Th", "role": "advisor", "display_name": "von K\u00e1rm\u00e1n, Theodore" }, { "name": { "family": "Sechler", "given": "Ernest Edwin" }, "id": "Sechler-E-E", "role": "co-advisor", "display_name": "Sechler, Ernest Edwin" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/7XWB-QP81", "abstract": "No abstract.\r\n\r\n" }, { "name": "Mellinger, George Rolland", "degree": "Masters", "year": "1938", "title": "Shear Transfer of Load From Main Beams to Intermediate Corrugations in Metal Sheet Covered Box Beams", "advisor": "Sechler, Ernest Edwin", "url": "https://resolver.caltech.edu/CaltechETD:etd-01262006-140318", "creators": [ { "name": { "family": "Mellinger", "given": "George Rolland" }, "id": "Mellinger-George-Rolland", "display_name": "Mellinger, George Rolland" }, { "name": { "family": "Kurihara", "given": "Hisayuki" }, "id": "Kurihara-Hisayuki", "display_name": "Kurihara, Hisayuki" } ], "advisors": [ { "name": { "family": "Sechler", "given": "Ernest Edwin" }, "id": "Sechler-E-E", "role": "advisor", "display_name": "Sechler, Ernest Edwin" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/5751-Y722", "abstract": "NOTE: Text or symbols not renderable in plain ASCII are indicated by [...]. Abstract is included in .pdf document.\r\n\r\nA program of experimental investigation for three combinations of sheet reinforced with corrugations has been carried out.
\r\n\r\nAn assumption has been made for the transverse neutral axis of such a system.
\r\n\r\nFor an open section box beam, the conventional assumption of the neutral axis on the center of gravity plane indicates an error.
\r\n\r\nAn attempt has been made to calculate the compressive stress in each corrugation due to shear transfer of load.
\r\n\r\nAn effective shear modulus for each corrugation and its share of the skin under bending loads has been found by experimental methods.
\r\n\r\nFor the combinations tested, it was found that the effective shear modulus, G/E, decreases with increasing \u03c4, which corresponds to increasing G/E with distance from the free end of the panel.
\r\n\r\nPanel curvature was found to have a marked effect on G/E, in that the curved panel had a larger value of G/E for the same \u03c4.
\r\n\r\nContour maps of \u03c4, the shearing stress, have been constructed for the three panels.
" }, { "name": "Putt, Donald Leander", "degree": "Masters", "year": "1938", "title": "Experimental Investigation of the Thickness of the Boundary Layer and the Location of the Transitional Region Along a Wing Section", "advisor": "Sechler, Ernest Edwin", "url": "https://resolver.caltech.edu/CaltechETD:etd-01092006-152711", "creators": [ { "name": { "family": "Putt", "given": "Donald Leander" }, "id": "Putt-Donald-Leander", "display_name": "Putt, Donald Leander" } ], "advisors": [ { "name": { "family": "Sechler", "given": "Ernest Edwin" }, "id": "Sechler-E-E", "role": "advisor", "display_name": "Sechler, Ernest Edwin" } ], "committee": [ { "name": { "family": "Sechler", "given": "Ernest Edwin" }, "id": "Sechler-E-E", "role": "chair", "display_name": "Sechler, Ernest Edwin" }, { "name": { "family": "Millikan", "given": "Clark Blanchard" }, "id": "Millikan-C-B", "role": "member", "display_name": "Millikan, Clark Blanchard" }, { "name": { "family": "von K\u00e1rm\u00e1n", "given": "Theodore" }, "id": "von-K\u00e1rm\u00e1n-Th", "role": "member", "display_name": "von K\u00e1rm\u00e1n, Theodore" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/ZZVX-7082", "abstract": "A general review of the investigation of the thickness of the boundary layer and the location of the transition point on an airplane wing in free flight that have been published to date is presented, along with some of the conclusions that have been reached from the results of the investigations.
\r\n\r\nThe development and design of apparatus for the experimental determination of the thickness of the boundary layer, and the location of the point of transition from laminar to turbulent flow in the boundary layer which can be readily attached to the surface of a metal airplane wing is described.
\r\n\r\nAlso the method and technique developed for recording the data and the interpretation of the test results are described in detail.
" }, { "name": "Scoles, Albert Buddy", "degree": "Masters", "year": "1938", "title": "Range Calculations for Airplanes With Continuously Controllable Pitch Propellers, and the Effect of Certain Geometric Parameters of the Airplane on Range", "advisor": "Millikan, Clark Blanchard", "url": "https://resolver.caltech.edu/CaltechETD:etd-02082006-090132", "creators": [ { "name": { "family": "Scoles", "given": "Albert Buddy" }, "id": "Scoles-Albert-Buddy", "display_name": "Scoles, Albert Buddy" }, { "name": { "family": "Schoech", "given": "William Alton" }, "id": "Schoech-William Alton", "display_name": "Schoech, William Alton" } ], "advisors": [ { "name": { "family": "Millikan", "given": "Clark Blanchard" }, "id": "Millikan-C-B", "role": "advisor", "display_name": "Millikan, Clark Blanchard" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/CMHQ-E314", "abstract": "This investigation was undertaken to develop a satisfactorily exact method for the calculation of range of airplane; and with such method, to determine the effect of certain geometrical parameters of the airplane on range, namely, span, aspect ratio, and wing loading.
\r\n\r\nWith satisfactory aerodynamic data from wind tunnel reports, and with satisfactory engine performance data from test stand reports, the method developed permits determination of range, optimum speeds to use, and optimum propeller rpm to use for each speed. It further permits determination of endurance.
\r\n\r\nIn general, increasing aspect ratio for constant span will increase maximum range if reasonable upper limits are placed on wing loading. The gain is but slight for aspect ratios in excess of 11. Similarly, decreasing span for constant aspect ratio will increase maximum range. Both of these variations results in increased wing loading, which can therefore be considered as the fundamental factor giving the increase. There will in general be an optimum combination of aspect ratio and span for a given wing loading which will give maximum range. Satisfactory takeoff and sea-level rate of climb will limit the wing loading; however, for wing loadings in excess of 50, the maximum gain obtainable is of the order of 5%.
\r\n" }, { "name": "Smith, Apollo Milton Olin", "degree": "Masters", "year": "1938", "title": "A Preliminary Study of the Problem of Boundary Layer Control", "advisor": "Millikan, Clark Blanchard", "url": "https://resolver.caltech.edu/CaltechETD:etd-12052007-091749", "creators": [ { "name": { "family": "Smith", "given": "Apollo Milton Olin" }, "id": "Smith-Apollo-Milton-Olin", "display_name": "Smith, Apollo Milton Olin" } ], "advisors": [ { "name": { "family": "Millikan", "given": "Clark Blanchard" }, "id": "Millikan-C-B", "role": "advisor", "display_name": "Millikan, Clark Blanchard" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/STNT-3N37", "abstract": "This thesis presents a study of the problem of securing high lifts by means of boundary layer removal, together with first results of tests on the Boundary Layer Model of the Guggenheim Aeronautics Laboratory, California Institute of Technology (hereinafter called GALCIT). It is divided into two parts: first, a review and discussion of previous work, and second, presentation and development of methods used for carrying out tests upon the GALCIT model, together with experimental results obtained from the tests upon the model.
\r\n\r\nPrevious researches show that boundary layer removal is indeed successful in securing high lift coefficients. Study reveals also that results from one experiment may differ greatly from those of another. Consequently, previous work is of little help in predicting results to be obtained for a design different from the model tested.
\r\n\r\nResults on the GALCIT model have not been favorable, but it is believed that flow tests have found the difficulty. Consequently, the experimental work has value only for the light it sheds upon the future course of this research at the Institute.
\r\n\r\n\r\n" }, { "name": "Allardt, Frederick Hamilton", "degree": "Masters", "year": "1937", "title": "The Brinelling of Small Ball Bearings", "advisor": "Klein, Arthur Louis; Sechler, Ernest Edwin", "url": "https://resolver.caltech.edu/CaltechETD:etd-10132005-103946", "creators": [ { "name": { "family": "Allardt", "given": "Frederick Hamilton" }, "id": "Allardt-Frederick-Hamilton", "display_name": "Allardt, Frederick Hamilton" } ], "advisors": [ { "name": { "family": "Klein", "given": "Arthur Louis" }, "id": "Klein-A-L", "role": "advisor", "display_name": "Klein, Arthur Louis" }, { "name": { "family": "Sechler", "given": "Ernest Edwin" }, "id": "Sechler-E-E", "role": "advisor", "display_name": "Sechler, Ernest Edwin" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/K872-W635", "abstract": "The brinelling of ball bearings is a subject which has had comparatively little study. Since ball bearings have found most of their applications in such things as rotating shafts, there has been little reason to study their action under static loading conditions. This research was suggested by the Fafnir Ball Bearing Company because of the increasing use of ball bearings for static loads in aircraft. In the aircraft business, the designers, because of strict weight requirements, have used ball bearings up to their rated loads. Not infrequently these bearings brinelled. (A brinelled bearing is one in which a dent has been formed in one of the races by a ball). It is therefore evident that more should be known about the brinelling of bearings." }, { "name": "Losey, Robert M.", "degree": "Masters", "year": "1937", "title": "A Theoretical Investigation of the Possibilities of Internal Cooling of Aircraft Engines by Water Injection to the Cylinder", "advisor": "Millikan, Clark Blanchard", "url": "https://resolver.caltech.edu/CaltechETD:etd-04112008-132848", "creators": [ { "name": { "family": "Losey", "given": "Robert M." }, "id": "Losey-Robert-M", "display_name": "Losey, Robert M." } ], "advisors": [ { "name": { "family": "Millikan", "given": "Clark Blanchard" }, "id": "Millikan-C-B", "role": "advisor", "display_name": "Millikan, Clark Blanchard" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/3PXW-GF19", "abstract": "No abstract." }, { "name": "Miller, Shirley Snow", "degree": "Masters", "year": "1937", "title": "Wind Tunnel Tests on a Low-Wing Monoplane With Propeller Running", "advisor": "Millikan, Clark Blanchard", "url": "https://resolver.caltech.edu/CaltechTHESIS:11122024-214212298", "creators": [ { "name": { "family": "Miller", "given": "Shirley Snow" }, "id": "Miller-Shirley-Snow", "display_name": "Miller, Shirley Snow" }, { "name": { "family": "Albach", "given": "Walter Henry" }, "id": "Albach-Walter-Henry", "display_name": "Albach, Walter Henry" } ], "advisors": [ { "name": { "family": "Millikan", "given": "Clark Blanchard" }, "id": "Millikan-C-B", "role": "advisor", "display_name": "Millikan, Clark Blanchard" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/y5vw-2z26", "abstract": "Various tests have been conducted on airplane wind tunnel models with an operating propeller in an endeavor to furnish the industry data as an aid in design and performance predictions. At the GALCIT, these investigations have comprised the material set forth in references 1, 2 and 4.
\r\n\r\nThe tests conducted by the authors of this paper represent a continuation of the above-mentioned investigations. The purpose of the present tests was to determine l) the effect of power on static longitudinal stability (elevator free); 2)\u00b7the effect of power on hinge moments (at various tab angles); and 3) the effect of power on static directional stability with the model operating at high and low angle of attack.
" }, { "name": "Moore, Charles Kenneth", "degree": "Masters", "year": "1937", "title": "Age Hardening of Heat Treated Aluminum Alloy. An Investigation of the Fluctuation of Hardness with Time of Ageing of Heat Treated Aluminum Alloy Sheet", "advisor": "Sechler, Ernest Edwin; von K\u00e1rm\u00e1n, Theodore", "url": "https://resolver.caltech.edu/CaltechETD:etd-03212005-103521", "creators": [ { "name": { "family": "Moore", "given": "Charles Kenneth" }, "id": "Moore-Charles-Kenneth", "display_name": "Moore, Charles Kenneth" }, { "name": { "family": "Nollan", "given": "John Lloyd" }, "id": "Nollan-John-Lloyd", "display_name": "Nollan, John Lloyd" } ], "advisors": [ { "name": { "family": "Sechler", "given": "Ernest Edwin" }, "id": "Sechler-E-E", "role": "advisor", "display_name": "Sechler, Ernest Edwin" }, { "name": { "family": "von K\u00e1rm\u00e1n", "given": "Theodore" }, "id": "von-K\u00e1rm\u00e1n-Th", "role": "advisor", "display_name": "von K\u00e1rm\u00e1n, Theodore" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics", "mecheng" ], "doi": "10.7907/3G1Z-F889", "abstract": "The authors have found what they believe to be a tendency for a certain Aluminum Alloy, namely 24-SO, to fluctuate in strength, and hardness, during the process of age hardening, after heat treatment.
\r\n\r\nThis variation in hardness of the material, while the ageing process is going on, is accompanied by a change in ultimate strength, and in the stress-strain relationship of the material; and in general the condition of the alloy is indicated by the hardness number.
\r\n\r\nThe limited scope of this research does not indicate that this phenomenon of fluctuation of hardening is constant in occurrence; as the number of tests made were insufficient to determine the regularity, or irregularity, of this characteristic of the material.
\r\n\r\nAll of the metal tested became stable within the commonly accepted range of ultimate strength for this alloy.
\r\n\r\nFrom these few experiments it appears that although the hardness varies with time, the alloy, if allowed to age sufficiently, will develop its rated strength.
\r\n\r\nVarious reports have been made to the effect that sheet aluminum alloy, after being heat treated, quenched, and allowed to begin normal age hardening, did not respond to ageing as might be expected, nor did it follow the theoretical hardening curve with reasonable agreement. It was found that sheet material, although apparently properly heat treated, had not hardened, or acquired its full strength, when inspected by hardness testing methods.
\r\n\r\nFrom observations it was found that the same piece, which was observed to be soft, when allowed to age for a longer period and tested again for hardness, had in some cases come up to the required standard, and in others had exceeded the inspection limits.
\r\n\r\nTo the best of the authors knowledge no systematic investigation of this phenomenon has been undertaken, and as a preliminary quest in this field of research a periodic measurement of hardness, and tensile strength, was carried out to determine the actual manner in which the selected material would harden with time, and to correlate its indicated hardness with the strength of the piece at the time of measurement.
" }, { "name": "Smith, Joe Nelson", "degree": "Masters", "year": "1937", "title": "Investigation of Extended Bulb Angle Sections Under Compression: Part One. As Euler Columns ; Part Two. As Stiffeners Attached to Sheet", "advisor": "Sechler, Ernest Edwin", "url": "https://resolver.caltech.edu/CaltechETD:etd-04252008-093950", "creators": [ { "name": { "family": "Smith", "given": "Joe Nelson" }, "id": "Smith-Joe-Nelson", "display_name": "Smith, Joe Nelson" }, { "name": { "family": "Murphy", "given": "Joseph Nathaniel" }, "id": "Murphy-Joseph Nathaniel", "display_name": "Murphy, Joseph Nathaniel" } ], "advisors": [ { "name": { "family": "Sechler", "given": "Ernest Edwin" }, "id": "Sechler-E-E", "role": "advisor", "display_name": "Sechler, Ernest Edwin" } ], "committee": [ { "name": { "family": "None", "given": "None" }, "display_name": "None, None" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/R62Z-6P10", "abstract": "No abstract.\r\n" }, { "name": "Young, Bradley Hobart", "degree": "Masters", "year": "1937", "title": "A Two-Parameter Wind Tunnel Rigging System", "advisor": "Klein, Arthur Louis", "url": "https://resolver.caltech.edu/CaltechETD:etd-03242005-100937", "creators": [ { "name": { "family": "Young", "given": "Bradley Hobart" }, "id": "Young-Bradley-Hobart", "display_name": "Young, Bradley Hobart" } ], "advisors": [ { "name": { "family": "Klein", "given": "Arthur Louis" }, "id": "Klein-A-L", "role": "advisor", "display_name": "Klein, Arthur Louis" } ], "committee": [ { "name": { "family": "Klein", "given": "Arthur Louis" }, "id": "Klein-A-L", "role": "chair", "display_name": "Klein, Arthur Louis" }, { "name": { "family": "Millikan", "given": "Clark Blanchard" }, "id": "Millikan-C-B", "role": "member", "display_name": "Millikan, Clark Blanchard" }, { "name": { "family": "Sechler", "given": "Ernest Edwin" }, "id": "Sechler-E-E", "role": "member", "display_name": "Sechler, Ernest Edwin" }, { "name": { "family": "Bowen", "given": "William H." }, "id": "Bowen-W-H", "role": "member", "display_name": "Bowen, William H." } ], "option_major": [ "aeronautics" ], "doi": "10.7907/CVB4-7510", "abstract": "In January of 1935, definite steps were taken in a two part program to modernize the ten-foot wind tunnel of the Guggenheim Aeronautical Laboratory at the California Institute of Technology. Part one of the program was the design and construction of a new wind tunnel rigging system based on concepts originally laid down by Dr. A. L. Klein, Associate Professor at the same institution. Part two of the program, to be carried on intensively immediately after completion of part one, will be the development of an entirely new force measuring system to replace the present modified steelyard type balances.
\r\n\r\nIn this paper the general problem of wind tunnel testing and equipment will be briefly outlined with the bulk of the discussion then given over to the problems concerning the evolution and design of a specific wind tunnel rigging system. As the system is not yet complete in its final form obviously there can be no description of the project as a finished piece of work. Also, it has been thought inadvisable to present only the system as it exists at present, therefore all the various features or principles that have been considered will be discussed and reason for their discard or adoption made clear. The result should then be a guide or at least an aid to the completion of part one of the modernizing program
\r\n\r\nIn a latter section of the paper some of the desired features of the contemplated force measuring system will be set down in the hope that they may be a skeletal set of requirements for the second part of the modernizing program.
\r\n" }, { "name": "Bolster, Calvin Mathews", "degree": "Masters", "year": "1936", "title": "Wind Tunnel Tests on the Effect of Power on the Stability of a Low Wing Monoplane with Three Vertical Positions of Horizontal Tail Surfaces", "advisor": "Millikan, Clark Blanchard", "url": "https://resolver.caltech.edu/CaltechETD:etd-01102006-161025", "creators": [ { "name": { "family": "Bolster", "given": "Calvin Mathews" }, "id": "Bolster-Calvin-Mathews", "display_name": "Bolster, Calvin Mathews" } ], "advisors": [ { "name": { "family": "Millikan", "given": "Clark Blanchard" }, "id": "Millikan-C-B", "role": "advisor", "display_name": "Millikan, Clark Blanchard" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/QRHQ-FP49", "abstract": "A great majority of present day airplanes are of the low wing cantilever type. An investigation into the effect of power and vertical location of the horizontal tail surfaces on the longitudinal static stability of such airplanes is therefore of interest.
\r\n\r\nThe present investigation was carried out on a one-sixth scale model of a low wing single engine tractor monoplane. The results are probably most directly applicable to airplanes of this type. However, the tendencies and general effects should also be fairly indicative of what may be expected in multiple engine low wing monoplanes of conventional design.
" }, { "name": "Childers, Milford Carlson", "degree": "Masters", "year": "1936", "title": "Stresses in Metal Beams with Flat Sheet Webs of Medium Thickness", "advisor": "von K\u00e1rm\u00e1n, Theodore", "url": "https://resolver.caltech.edu/CaltechETD:etd-04242008-111115", "creators": [ { "name": { "family": "Childers", "given": "Milford Carlson" }, "id": "Childers-Milford-Carlson", "display_name": "Childers, Milford Carlson" } ], "advisors": [ { "name": { "family": "von K\u00e1rm\u00e1n", "given": "Theodore" }, "id": "von-K\u00e1rm\u00e1n-Th", "role": "advisor", "display_name": "von K\u00e1rm\u00e1n, Theodore" } ], "committee": [ { "name": { "family": "von K\u00e1rm\u00e1n", "given": "Theodore" }, "id": "von-K\u00e1rm\u00e1n-Th", "role": "chair", "display_name": "von K\u00e1rm\u00e1n, Theodore" }, { "name": { "family": "Klein", "given": "Arthur Louis" }, "id": "Klein-A-L", "role": "member", "display_name": "Klein, Arthur Louis" }, { "name": { "family": "Millikan", "given": "Clark Blanchard" }, "id": "Millikan-C-B", "role": "member", "display_name": "Millikan, Clark Blanchard" }, { "name": { "family": "Sechler", "given": "Ernest Edwin" }, "id": "Sechler-E-E", "role": "member", "display_name": "Sechler, Ernest Edwin" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/Y3QT-J764", "abstract": "This paper develops a method by which the stresses in the component parts of a solid web beam may be computed when the dimensions of the web thickness, beam height, and distance between stiffeners are such that the web does not go into the wave state immediately upon applying a small load. The stress in the web itself is calculated by a consideration of the buckling load of the web. The load in the stiffeners and flanges is computed by assuming an effective width of sheet as acting with them. This effective width is obtained by a consideration of the buckling properties of thin sheet in shear.
\r\n\r\nThe results are in the same form as the familiar Wagner beam equations except that certain terms must be modified and corrections made. The results herein obtained are not to be considered as superseding the Wagner Equations as derived in Ref. I, but supplement them to take care of cases out of the range of the Wagner assumptions.
\r\n" }, { "name": "Colman, Philip Abbey", "degree": "Masters", "year": "1936", "title": "The Oscillating Vane-Type Fan", "advisor": "von K\u00e1rm\u00e1n, Theodore", "url": "https://resolver.caltech.edu/CaltechETD:etd-07172007-145903", "creators": [ { "name": { "family": "Colman", "given": "Philip Abbey" }, "id": "Colman-Philip-Abbey", "display_name": "Colman, Philip Abbey" } ], "advisors": [ { "name": { "family": "von K\u00e1rm\u00e1n", "given": "Theodore" }, "id": "von-K\u00e1rm\u00e1n-Th", "role": "advisor", "display_name": "von K\u00e1rm\u00e1n, Theodore" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/0TZ7-7Q11", "abstract": "The investigation herein described was undertaken to determine the performance characteristics of the oscillating vane-type fan. The fan was the invention of Mr. Van Dorn and Mr. Cornwell, primarily for use in circulating air in railroad refrigerator cars. In the present system of railroad refrigeration for the transportation of perishable foodstuffs, the refrigerator car is a heat insulated car, with bunkers at each end for the cakes of ice. When the car is loaded and the doors shut, cooling is obtained only due to the natural circulation of air in the car, caused by the difference in temperature between the ice in the bunker and the fruit. This circulation has not been found sufficient, in that there is a large temperature difference between the top and bottom fruit (see Appendix B) and the top half is too warm, often spoiling during transportation. Also, because of this, the car cannot be filled to its volumetric capacity. Therefore the requirements which led to the invention of this type of fan were as follows:
\r\n\r\n1. To provide a sufficient volume of air, against the resistance developed in passing through the fruit, to obtain the cooling characteristics required.
\r\n\r\n2. To provide a fan which would not require major changes in the structural design of the car, or lessen the amount of fruit which could be carried.
\r\n\r\n3. To provide a fan, simple in construction and installation, and in its drive mechanism from the car axle.
The oscillating vane-type fan met conditions 2 and 3 in that it could be situated in the four and one half inch space between the floor racks and the floor of the car, through which the air naturally circulated, and in that it could be driven by a simple wheel and crank drive directly off the axle. This thesis presents the results of the investigation of the first condition.
\r\n" }, { "name": "Fleming, Morton Klyne", "degree": "Masters", "year": "1936", "title": "Experimental Investigation of the Effect Of Power Upon the Static Longitudinal Stability of a Low Winged Monoplane and a Method for its Calculation", "advisor": "Millikan, Clark Blanchard", "url": "https://resolver.caltech.edu/CaltechETD:etd-04152008-085638", "creators": [ { "name": { "family": "Fleming", "given": "Morton Klyne" }, "id": "Fleming-Morton-Klyne", "display_name": "Fleming, Morton Klyne" } ], "advisors": [ { "name": { "family": "Millikan", "given": "Clark Blanchard" }, "id": "Millikan-C-B", "role": "advisor", "display_name": "Millikan, Clark Blanchard" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/JKVP-P690", "abstract": "To obtain the change in the longitudinal moment of a low winged monoplane caused by the addition of the propulsive unit operating at various conditions of power.
\r\n\r\nTo construct possible working charts for use in calculating this change from power off wind tunnel tests of scale models.
\r\n" }, { "name": "Howland, Walter Lavern", "degree": "Masters", "year": "1936", "title": "Effect of Rivet Spacing on Stiffened Thin Sheet Under Compression", "advisor": "von K\u00e1rm\u00e1n, Theodore; Sechler, Ernest Edwin", "url": "https://resolver.caltech.edu/CaltechETD:etd-07182007-093403", "creators": [ { "name": { "family": "Howland", "given": "Walter Lavern" }, "id": "Howland-Walter-Lavern", "display_name": "Howland, Walter Lavern" } ], "advisors": [ { "name": { "family": "von K\u00e1rm\u00e1n", "given": "Theodore" }, "id": "von-K\u00e1rm\u00e1n-Th", "role": "advisor", "display_name": "von K\u00e1rm\u00e1n, Theodore" }, { "name": { "family": "Sechler", "given": "Ernest Edwin" }, "id": "Sechler-E-E", "role": "advisor", "display_name": "Sechler, Ernest Edwin" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/KCDP-9732", "abstract": "This thesis discusses an experimental investigation of the stress distribution across a stiffened thin sheet panel under compression. The effect of bending stresses and curvature of the sheet on extensometer readings is also dealt with. An attempt is made to determine a rational design criteria for rivet spacing on stiffened thin sheet under compression. Design curves of rivet spacing against thickness are developed. The effect of changing the rivet spacing or size on the ultimate load of a compression panel is discussed in view of some experiments." }, { "name": "Lovett, Benjamin Barnes Compton", "degree": "Masters", "year": "1936", "title": "Transfer of Stress from Main Beams to Intermediate Stiffeners in Metal Sheet Covered Box Beams", "advisor": "Sechler, Ernest Edwin", "url": "https://resolver.caltech.edu/CaltechETD:etd-01272006-091759", "creators": [ { "name": { "family": "Lovett", "given": "Benjamin Barnes Compton" }, "id": "Lovett-Benjamin-Barnes-Compton", "display_name": "Lovett, Benjamin Barnes Compton" }, { "name": { "family": "Rodee", "given": "Walter Fred" }, "id": "Rodee-Walter-Fred", "display_name": "Rodee, Walter Fred" } ], "advisors": [ { "name": { "family": "Sechler", "given": "Ernest Edwin" }, "id": "Sechler-E-E", "role": "advisor", "display_name": "Sechler, Ernest Edwin" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/MAAF-MM48", "abstract": "The authors have obtained by experimental methods an effective sheer modulus for the sheet in a stiffened plane sheet beam combination under bending loads. For the combinations tested it was found that the modulus decreases rapidly under light loadings from the elastic value to some asymptotic value depending upon the sheet thickness. The thick sheet combination gave higher values of the effective shear modulus than the thin sheet." }, { "name": "Malina, Frank Joseph", "degree": "Masters", "year": "1936", "title": "Characteristics of Braked, Locked and Free-Wheeling Two- and Three-Bladed Propellers", "advisor": "Unknown, Unknown", "url": "https://resolver.caltech.edu/CaltechETD:etd-02092007-153045", "creators": [ { "name": { "family": "Malina", "given": "Frank Joseph" }, "id": "Malina-Frank-Joseph", "display_name": "Malina, Frank Joseph" }, { "name": { "family": "Jenney", "given": "William W." }, "id": "Jenney-William-W", "display_name": "Jenney, William W." } ], "advisors": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/HYXB-6T51", "abstract": "The use of multi-engined aircraft has introduced the problem of aircraft performance when one or more power units have either become unusable or voluntarily shut down during cruising flight. If the use of the engine is to be discontinued because of mechanical failure, the desirable procedure is obviously to stop it altogether, so as to prevent possible destruction to the engine. This can be accomplished by locking the propeller, by a free-wheeling arrangement, or by feathering a variable pitch propeller. If the use of the engine is to be discontinued merely to reduce fuel consumption, the propeller may be allowed to turn the engine, in which case the propeller is braked by a torque equal to the friction of the engine.
\r\n\r\nAnother recent development connected with braked propellers is the fact that the variable pitch propeller now offers the possibility of using the large increment in drag at low blade angles of braked and free-wheeling propellers for reduction in landing speed or landing run of clean, highly powered, multi-engined aircraft.
\r\n\r\nIt was the purpose of the present investigation to provide information not already made available by researches listed under the references at the end of this paper. Therefore the following thesis will be concerned chiefly with the three-bladed propeller and its effect on airplane characteristics, the two-bladed propeller being used principally for comparison purposes with other available data. The tests were performed at model scale, but their acceptance as applicable to full scale is supported by the favorable comparisons made in Reference 5.
\r\n\r\n" }, { "name": "Martin, Victor John", "degree": "Masters", "year": "1936", "title": "Airplane Takeoff Performance", "advisor": "Unknown, Unknown", "url": "https://resolver.caltech.edu/CaltechETD:etd-03142005-145716", "creators": [ { "name": { "family": "Martin", "given": "Victor John" }, "id": "Martin-Victor-John", "display_name": "Martin, Victor John" } ], "advisors": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/JQD0-EW36", "abstract": "In this paper a general equation for calculating the takeoff performance of landplanes is developed in terms of the usual airplane parameters.
\r\n\r\nThe analysis enables the ground effect, wind and atmospheric conditions, altitude, and the use of flaps to be taken into account. A simple and rapid method is presented for the determination of the best flap angle to be used for takeoff.
\r\n\r\nVariation in takeoff performance due to changes in any of the airplane or engine-propeller characteristics is readily determined through the introduction of a new takeoff acceleration parameter.
\r\n\r\nA method for calculating the propeller speed, engine power, and thrust variation for both fixed-pitch and constant-speed propellers is included, and a new significance is given to the thrust versus square of velocity curve for takeoff computations.
\r\n\r\nExamples are included to illustrate the use of the analysis in solving the various takeoff problems.
\r\n" }, { "name": "Whelan, Thomas Murray", "degree": "Masters", "year": "1936", "title": "The Calculated Flight Path of the U.S.S. Macon", "advisor": "von K\u00e1rm\u00e1n, Theodore", "url": "https://resolver.caltech.edu/CaltechETD:etd-12222005-112942", "creators": [ { "name": { "family": "Whelan", "given": "Thomas Murray" }, "id": "Whelan-Thomas-Murray", "display_name": "Whelan, Thomas Murray" } ], "advisors": [ { "name": { "family": "von K\u00e1rm\u00e1n", "given": "Theodore" }, "id": "von-K\u00e1rm\u00e1n-Th", "role": "advisor", "display_name": "von K\u00e1rm\u00e1n, Theodore" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/PC07-4F03", "abstract": "These calculations are concerned with the flight path of the Macon after the loss of the upper fin and the deflation of the three after gas cells. Taking into account the actual flight conditions, the question was raised whether the ship would rise to an altitude of 4800 feet. For at this altitude, which the record shows was actually reached, the ship had exceeded pressure height by about 2000'. In going over pressure height, the ship loses approximately 3% of her lift for every 1000 feet. Hence 4800 feet corresponds to a heaviness of nearly 11 tons. It was felt that if this additional heaviness could have been avoided, the ship might have been flown safely in spite of the loss of some 20 tons of lift from the three after cells. The calculations were undertaken to determine whether the aerodynamic and aerostatic forces alone were sufficient to force the ship up to 4800 feet or whether there were external forces acting, i. e. gust forces." }, { "name": "Kitsuda, Kaname", "degree": "Masters", "year": "1935", "title": "Investigation of Stress Distribution on Thin Metal Sheet With Holes", "advisor": "Sechler, Ernest Edwin", "url": "https://resolver.caltech.edu/CaltechETD:etd-03112005-134957", "creators": [ { "name": { "family": "Kitsuda", "given": "Kaname" }, "id": "Kitsuda-Kaname", "display_name": "Kitsuda, Kaname" } ], "advisors": [ { "name": { "family": "Sechler", "given": "Ernest Edwin" }, "id": "Sechler-E-E", "role": "advisor", "display_name": "Sechler, Ernest Edwin" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/921K-MD80", "abstract": "This paper presents the investigation of the ultimate strength of a plate under shearing stresses when the plate contains lightening holes. The optimum arrangement of holes and the most desirable size of hole has also been investigated. Stress-strain curves have been made which show the points at which the plates reach the buckling point, the elastic limit, and the point of permanent deformation.\r\n" }, { "name": "McNeal, Don", "degree": "Masters", "year": "1935", "title": "Ice Formation in the Atmosphere", "advisor": "Unknown, Unknown", "url": "https://resolver.caltech.edu/CaltechETD:etd-04222008-104429", "creators": [ { "name": { "family": "McNeal", "given": "Don" }, "id": "McNeal-Don", "display_name": "McNeal, Don" } ], "advisors": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "meteor" ], "doi": "10.7907/SX19-PN27", "abstract": "No abstract.\r\n" }, { "name": "Parr, Warren Sherman", "degree": "Masters", "year": "1935", "title": "Investigation of Duralumin Channel Section Strut Under Compression", "advisor": "von K\u00e1rm\u00e1n, Theodore; Sechler, Ernest Edwin", "url": "https://resolver.caltech.edu/CaltechETD:etd-12222005-115855", "creators": [ { "name": { "family": "Parr", "given": "Warren Sherman" }, "id": "Parr-Warren-Sherman", "display_name": "Parr, Warren Sherman" }, { "name": { "family": "Beakley", "given": "Wallace Morris" }, "id": "Beakley-Wallace-Morris", "display_name": "Beakley, Wallace Morris" } ], "advisors": [ { "name": { "family": "von K\u00e1rm\u00e1n", "given": "Theodore" }, "id": "von-K\u00e1rm\u00e1n-Th", "role": "advisor", "display_name": "von K\u00e1rm\u00e1n, Theodore" }, { "name": { "family": "Sechler", "given": "Ernest Edwin" }, "id": "Sechler-E-E", "role": "advisor", "display_name": "Sechler, Ernest Edwin" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/9VQN-K047", "abstract": "This investigation has clearly established the fact that, for sections built up of straight line elements, theoretical calculations can be made with a degree of accuracy sufficient for practical application and will be on the conservative side." }, { "name": "Russell, James Sargent", "degree": "Masters", "year": "1935", "title": "Propeller Characteristics and Slipstream Effects on a High Wing Monoplane from Wind Tunnel Tests", "advisor": "Unknown, Unknown", "url": "https://resolver.caltech.edu/CaltechTHESIS:08182010-095214810", "creators": [ { "name": { "family": "Russell", "given": "James Sargent" }, "id": "Russell-James-Sargent", "display_name": "Russell, James Sargent" }, { "name": { "family": "McCoy", "given": "Howard Monroe" }, "id": "McCoy-Howard-Monroe", "display_name": "McCoy, Howard Monroe" } ], "advisors": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/91VQ-DG62", "abstract": "No abstract." }, { "name": "White, Roland James", "degree": "Masters", "year": "1935", "title": "The Stress Distribution in Reinforced Plates Under Concentrated Edge Loads", "advisor": "Unknown, Unknown", "url": "https://resolver.caltech.edu/CaltechETD:etd-12282005-152042", "creators": [ { "name": { "family": "White", "given": "Roland James" }, "id": "White-Roland-James", "display_name": "White, Roland James" }, { "name": { "family": "Antz", "given": "Hans Martin" }, "id": "Antz-Hans-Martin", "display_name": "Antz, Hans Martin" } ], "advisors": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/1Q4M-AS93", "abstract": "As part of the investigation of the stress distribution in metal covered wings leading to the most efficient distribution of materials, experiments have been made with flat plates reinforced with stiffeners under concentrated edge loads. Two theoretical solutions have been proposed: one by means of differential equations, considering the sheet between the stiffeners as the medium of transfer and the amount of load transferred to be proportional to the differences in the deflections; the other method, using the principle of the minimum of energy, approximates the accurate solution by considering the loaded system to be composed of columns (stiffeners acting with an effective width of sheet) under compression, the sheet being under shear." }, { "name": "Wood, Carlos Claude", "degree": "Masters", "year": "1935", "title": "Axial Flow Fan Design by Lattice Theory", "advisor": "von K\u00e1rm\u00e1n, Theodore", "url": "https://resolver.caltech.edu/CaltechETD:etd-10282005-132754", "creators": [ { "name": { "family": "Wood", "given": "Carlos Claude" }, "id": "Wood-Carlos-Claude", "display_name": "Wood, Carlos Claude" } ], "advisors": [ { "name": { "family": "von K\u00e1rm\u00e1n", "given": "Theodore" }, "id": "von-K\u00e1rm\u00e1n-Th", "role": "advisor", "display_name": "von K\u00e1rm\u00e1n, Theodore" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/6H0T-G579", "abstract": "This thesis takes the much discussed and comparatively little used lattice theory and applies it to the design of fans. The application is made through the use of charts coming out of the theory. It is felt that by the use of the charts that the design of confined fans, that is those where end effects on the blades need not be considered, will be made considerably simpler and easier.
\r\n\r\nThe use of the lattice theory in the design of fairly complicated vane systems is discussed, and an approximate method of analysis is given. This subject requires more study in the near future.
\r\n\r\nAs yet, at the time of writing, the method has not been checked by experiment, and as a result not much may be said concerning the accuracy of the results as actually applied to design. However, the use of the lattice theory gives designs that appear to be reasonable, and it is hoped that the method will prove to be fairly accurate in actual practice. At present a fan and vane installation as shown in Fig. XIII and Fix. XV is being constructed, and it is hoped that it will be possible to present some experimental data on the design in the near future.
" }, { "name": "Bridget, Francis Joseph", "degree": "Masters", "year": "1934", "title": "Buckling of Thin Walled Cylinders under Compression of Tension and Torsion", "advisor": "Donnell, Lloyd Hamilton", "url": "https://resolver.caltech.edu/CaltechTHESIS:09182024-203332146", "creators": [ { "name": { "family": "Bridget", "given": "Francis Joseph" }, "id": "Bridget-Francis-Joseph", "display_name": "Bridget, Francis Joseph" } ], "advisors": [ { "name": { "family": "Donnell", "given": "Lloyd Hamilton" }, "id": "Donnell-Lloyd-Hamilton", "role": "advisor", "display_name": "Donnell, Lloyd Hamilton" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/3nqj-9h59", "abstract": "No abstract." }, { "name": "Descamps, Alphonse Maurice", "degree": "Masters", "year": "1934", "title": "Photographic Study of Vortex Motions", "advisor": "Unknown, Unknown", "url": "https://resolver.caltech.edu/CaltechETD:etd-04142008-151832", "creators": [ { "name": { "family": "Descamps", "given": "Alphonse Maurice" }, "id": "Descamps-Alphonse-Maurice", "display_name": "Descamps, Alphonse Maurice" } ], "advisors": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/6QH1-R015", "abstract": "No abstract.\r\n" }, { "name": "Goldstein, Julian Richard", "degree": "Masters", "year": "1934", "title": "Investigation of Turbulence in Circular Tubes by Means of a Hot-Wire Anemometer", "advisor": "von K\u00e1rm\u00e1n, Theodore", "url": "https://resolver.caltech.edu/CaltechETD:etd-04152008-111221", "creators": [ { "name": { "family": "Goldstein", "given": "Julian Richard" }, "id": "Goldstein-Julian-Richard", "display_name": "Goldstein, Julian Richard" } ], "advisors": [ { "name": { "family": "von K\u00e1rm\u00e1n", "given": "Theodore" }, "id": "von-K\u00e1rm\u00e1n-Th", "role": "advisor", "display_name": "von K\u00e1rm\u00e1n, Theodore" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/A5KY-WY52", "abstract": "It is the purpose of this paper to present the results of some investigation of turbulent flow in straight circular tubes, conducted at the suggestion of Dr. Th. Von Karman, and to give a detailed description of the method of using the hot-wire anemometer to measure fluctuations of the air velocity in a direction parallel to the mean flow." }, { "name": "Magden, John Leslie", "degree": "Masters", "year": "1934", "title": "A Preliminary Investigation of Rivets and Riveted Joints in Metal Airplane Construction", "advisor": "Klein, Arthur Louis; Sechler, Ernest Edwin", "url": "https://resolver.caltech.edu/CaltechETD:etd-07172007-081411", "creators": [ { "name": { "family": "Magden", "given": "John Leslie" }, "id": "Magden-John-Leslie", "display_name": "Magden, John Leslie" } ], "advisors": [ { "name": { "family": "Klein", "given": "Arthur Louis" }, "id": "Klein-A-L", "role": "advisor", "display_name": "Klein, Arthur Louis" }, { "name": { "family": "Sechler", "given": "Ernest Edwin" }, "id": "Sechler-E-E", "role": "advisor", "display_name": "Sechler, Ernest Edwin" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/MWT3-P557", "abstract": "No abstract." }, { "name": "Rassieur, William Theodore", "degree": "Masters", "year": "1934", "title": "Hinge Moments", "advisor": "von K\u00e1rm\u00e1n, Theodore; Klein, Arthur Louis", "url": "https://resolver.caltech.edu/CaltechETD:etd-04152008-090606", "creators": [ { "name": { "family": "Rassieur", "given": "William Theodore" }, "id": "Rassieur-William-Theodore", "display_name": "Rassieur, William Theodore" } ], "advisors": [ { "name": { "family": "von K\u00e1rm\u00e1n", "given": "Theodore" }, "id": "von-K\u00e1rm\u00e1n-Th", "role": "advisor", "display_name": "von K\u00e1rm\u00e1n, Theodore" }, { "name": { "family": "Klein", "given": "Arthur Louis" }, "id": "Klein-A-L", "role": "advisor", "display_name": "Klein, Arthur Louis" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/5P3S-7022", "abstract": "The matter herein presented represents the results of an investigation on hinge moments of ailerons on a 1/12.5 scale model of a main wing airfoil of the XP3D-l Navy Patrol Boat.
\r\n\r\nThe data obtained were then employed in the calculation of stick forces due to aileron moments on the full scale airplane, the calculations covering a flying range of eighty to one hundred eighty miles per hour.
\r\n" }, { "name": "Rockefeller, William Curtis", "degree": "Masters", "year": "1934", "title": "A Study of the Selection of Flight Paths in Air Transport Operations", "advisor": "Unknown, Unknown", "url": "https://resolver.caltech.edu/CaltechTHESIS:10242017-090415553", "creators": [ { "name": { "family": "Rockefeller", "given": "William Curtis" }, "id": "Rockefeller-William-Curtis", "display_name": "Rockefeller, William Curtis" } ], "advisors": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/2ZSP-A355", "abstract": "1. GENERAL:
\r\n\r\nWith the introduction of the modern high perfor\u00admance airplane \r\ninto the air transportation systems of the country it has become \r\nincreasingly necessary to make some study of the variables which \r\ninfluence the proper selection of flight paths for the efficient \r\noperation of the aircraft.
\r\n\r\nIn the past it has been the practice in the air transport \r\nindustry to make a very rough estimate of the ef\u00adfect of the winds \r\nand thus determine the best altitude at which to fly on the course.\t\r\nThere has been a complete neg\u00adlect of the possibilities which \r\nare presented by a considera\u00adtion of the airplane performance.
\r\n\r\nIt is the purpose of this thesis to analize the effects of all\r\nof these variables with a view to obtaining some practical\r\nknowledge which may be valuable to the air transportation industry.
\r\n\r\n2. STATEMENT OF THE PROBLEM:
\r\n\r\nThe problem in general is the following: To provide a means of \r\nquickly determining before the start of a flight the path which the \r\npilot should follow in order to fly between any two points in the \r\nminimum possible time. Thus for a given set of cruising specifications \r\nfor the air\u00adplane, this path becomes the optimum, not only for time \r\nelapsed, but also for economy of operation. The method must take into \r\naccount both aerodynamic and meteorological varia\u00adtions.
\r\n\r\nTo be of practical use in air transport operation the method\r\nprovided must have three definite qualifications.
\r\n\r\n1. It must be such as to be readily calculated for a given\r\nflight by a person completely unfamiliar with aerodynamics and\r\nairplane performance.
\r\n\r\n2. It must not require more than a few minutes to calculate for\r\na given flight.
\r\n\r\n3. It must be such that the data can be presented to the pilot\r\nin a brief and useful form.
\r\n\r\nIn addition to the above it is highly desirable to provide information \r\nwhich will be of use to the pilot in properly navigating the airplane \r\nalong the course.
\r\n\r\nAll of the above requirements have been carefully considered throughout \r\nthe analysis and the attempt has been made to incorporate them into \r\nthe resulting method to as great an extent as possible.
\r\n" }, { "name": "Root, Leonard Eugene", "degree": "Masters", "year": "1934", "title": "A Study of the Dynamic Longitudinal Stability of Airplanes with Special Application to Design", "advisor": "Millikan, Clark Blanchard; von K\u00e1rm\u00e1n, Theodore", "url": "https://resolver.caltech.edu/CaltechTHESIS:09302024-220529723", "creators": [ { "name": { "family": "Root", "given": "Leonard Eugene" }, "id": "Root-Leonard-Eugene", "display_name": "Root, Leonard Eugene" } ], "advisors": [ { "name": { "family": "Millikan", "given": "Clark Blanchard" }, "id": "Millikan-C-B", "role": "advisor", "display_name": "Millikan, Clark Blanchard" }, { "name": { "family": "von K\u00e1rm\u00e1n", "given": "Theodore" }, "id": "von-K\u00e1rm\u00e1n-Th", "role": "advisor", "display_name": "von K\u00e1rm\u00e1n, Theodore" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/an7m-3j68", "abstract": "No abstract." }, { "name": "Vosseller, Aurelius Bartlett", "degree": "Masters", "year": "1934", "title": "Investigation of Relation Between Euler and Flat Plate Buckling of \"L\" Section Struts", "advisor": "von K\u00e1rm\u00e1n, Theodore", "url": "https://resolver.caltech.edu/CaltechETD:etd-04242008-084758", "creators": [ { "name": { "family": "Vosseller", "given": "Aurelius Bartlett" }, "id": "Vosseller-Aurelius-Bartlett", "display_name": "Vosseller, Aurelius Bartlett" }, { "name": { "family": "Jerome", "given": "Clayton Charles" }, "id": "Jerome-Clayton-Charles", "display_name": "Jerome, Clayton Charles" } ], "advisors": [ { "name": { "family": "von K\u00e1rm\u00e1n", "given": "Theodore" }, "id": "von-K\u00e1rm\u00e1n-Th", "role": "advisor", "display_name": "von K\u00e1rm\u00e1n, Theodore" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/6HFP-5R14", "abstract": "No abstract.\r\n\r\n" }, { "name": "Nagashi, Masahiro Howard", "degree": "Masters", "year": "1931", "title": "A Study of Fully Developed Turbulent Flow at a Very High Reynolds Number", "advisor": "von K\u00e1rm\u00e1n, Theodore; Millikan, Clark Blanchard", "url": "https://resolver.caltech.edu/CaltechETD:etd-06142006-110528", "creators": [ { "name": { "family": "Nagashi", "given": "Masahiro Howard" }, "id": "Nagashi-Masahiro-Howard", "display_name": "Nagashi, Masahiro Howard" } ], "advisors": [ { "name": { "family": "von K\u00e1rm\u00e1n", "given": "Theodore" }, "id": "von-K\u00e1rm\u00e1n-Th", "role": "advisor", "display_name": "von K\u00e1rm\u00e1n, Theodore" }, { "name": { "family": "Millikan", "given": "Clark Blanchard" }, "id": "Millikan-C-B", "role": "advisor", "display_name": "Millikan, Clark Blanchard" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/815A-2M78", "abstract": "The object of this experiment is to make a study of a fully developed turbulent flow at a very high Reynolds Number, using a large circular tube, through with air was drawn. In determining the behavior of the air stream, Pitot tubes were used in the present experiment. This investigation is a preliminary study of the turbulence and other characteristics of the tunnel for the subsequent experiment to be conducted by Mr. A. M. Kuethe of the California Institute of Technology. In the subsequent experiment, a direct measurement of the eddying motion and a determination of the values of mischungsweg distribution of the turbulent flow will be made at the same measuring sections in the same tunnel, using an electric anemometer and oscillograph method." }, { "name": "Zahorski, Adam Teodor", "degree": "Masters", "year": "1931", "title": "On the Torsion of Wings", "advisor": "Unknown, Unknown", "url": "https://resolver.caltech.edu/CaltechETD:etd-04172008-075520", "creators": [ { "name": { "family": "Zahorski", "given": "Adam Teodor" }, "id": "Zahorski-Adam-Teodor", "display_name": "Zahorski, Adam Teodor" } ], "advisors": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/E0T0-P929", "abstract": "Methods of investigation of pure torsion differ in many ways from the general method of procedure for other types of stresses. First it is very difficult to subject a body to a pure torsion without superposing bending moments; second the exact determination of twisting moment is in most cases very doubtful; third, a body subjected to torsional shearing stresses in general does not deform according to a simple law, but this deformation is usually a function of the geometry of the body." }, { "name": "Sechler, Ernest Edwin", "degree": "Masters", "year": "1930", "title": "Problems Relating to the Use of Sheet Metal in Airplane Construction", "advisor": "Unknown, Unknown", "url": "https://resolver.caltech.edu/CaltechETD:etd-10142005-081946", "creators": [ { "name": { "family": "Sechler", "given": "Ernest Edwin" }, "id": "Sechler-Ernest-Edwin", "display_name": "Sechler, Ernest Edwin" } ], "advisors": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "committee": [ { "name": { "family": "Unknown", "given": "Unknown" }, "display_name": "Unknown, Unknown" } ], "option_major": [ "aeronautics" ], "doi": "10.7907/RP44-R311", "abstract": "Sheet metal as used in present airplane construction may have two separate and distinct functions. The first of these is merely to supplant fabric or other covering material on the airplane. The structure of the airplane is not altered and the load is completely taken by the framework. The added strength and durability of this type of covering is usually connected with an increase in weight which makes the practice uneconomical. This use of metal is not a very serious design problem since it is only used as a covering and fairing and its strength is not included in the calculated strength of the structure.
\r\n\r\nSecondly, the sheet metal can be designed so it will take part or all of the loads on the airplane. It is this use of sheet metal, and its attendant problems, that will be discusssed here. Those problems that have been solved will be mentioned first and those yet undetermined will then be outlined. To be solved the answer to a problem must be in such a form as to be available and understandable to the average airplane designer without the use of long and intricate mathematical calculations. This means that those problems are solved which could be incorporated in a handbook for designers and those which could not be so incorporated are not solved for the designer.
" } ]