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Aerodynamic Characteristics of Horizontal Tail Surfaces

Description: From Summary: "Collected data are presented on the aerodynamic characteristics of 17 horizontal tail surfaces including several with balanced elevators and two with end plates. Curves are given for coefficients of normal force, drag, and elevator hinge moment. A limited analysis of the results has been made. The normal-force coefficients are in better agreement with the lifting-surface theory of Prandtl and Blenk for airfoils of low aspect ratio than with the usual lifting-line theory. Only par… more
Date: 1940
Creator: Silverstein, Abe & Katzoff, S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation of NACA 23012, 23021, and 23030 airfoils with various sizes of split flap

Description: Report presents the results of an investigation made in the NACA 7 by 10-foot wind tunnel of large-chord NACA and 23021, and 23030 airfoils with split flaps 10, 20, 30, and 40 percent of the wing chord to determine the section aerodynamic characteristics of the airfoils as affected by airfoil thickness, flap chord, and flap deflection. The complete section aerodynamic characteristics of all the combinations tested are given in the form of graphs of lift, drag, and pitching-moment coefficients, … more
Date: March 10, 1939
Creator: Wenzinger, Carl J. & Harris, Thomas A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Airfoil section data obtained in the NACA variable-density tunnel as affected by support interference and other corrections

Description: From Introduction: "The purpose of this report is to present the corrections for application to published results from the variable-density tunnel to give more reliable values of section profile-drag coefficient for airfoils of various thickness."
Date: 1939
Creator: Jacobs, Eastman N. & Abbott, Ira H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A study of air flow in an engine cylinder

Description: A 4-stroke-cycle test engine was equipped with a glass cylinder and the air movements within it were studied while the engine was being motored. Different types of air flow were produced by using shrouded intake valves in various arrangements and by altering the shape of the intake-air passage in the cylinder head. The air movements were made visible by mixing feathers with the entering air, and high-speed motion pictures were taken of them so that the air currents might be studied in detail an… more
Date: September 15, 1938
Creator: Lee, Dana W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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General Airplane Performance

Description: "Equations have been developed for the analysis of the performance of the ideal airplane, leading to an approximate physical interpretation of the performance problem. The basic sea-level airplane parameters have been generalized to altitude parameters and a new parameter has been introduced and physically interpreted. The performance analysis for actual airplanes has been obtained in terms of the equivalent ideal airplane in order that the charts developed for use in practical calculations wil… more
Date: June 1, 1937
Creator: Rockfeller, W. C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The knocking characteristics of fuels in relation to maximum permissible performance of aircraft engines

Description: An analysis is presented of the relationship of various engine factors to knock in preignition in an aircraft engine. From this analysis and from the available experimental data, a method of evaluating the knocking characteristics of the fuel in an aircraft-engine cylinder is suggested.
Date: September 14, 1938
Creator: Rothrock, A. M. & Biermann, Arnold E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Surface heat-transfer coefficients of finned cylinders

Description: An investigation to determine and correlate the experimental surface heat-transfer coefficients of finned cylinders with different air-stream cooling arrangements was conducted at the Langley Memorial Aeronautical Laboratory from 1932 to 1938. The investigation covered the determination of the effect of fin width, fin space, fin thickness, and cylinder diameter on the heat transfer. Wind-tunnel tests were made in the free air stream with and without baffles and also with various devices for cre… more
Date: April 27, 1939
Creator: Ellerbrock, Herman H., Jr. & Biermann, Arnold E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-tunnel investigation of NACA 23012 airfoil with various arrangements of slotted flaps

Description: "An investigation was made in the NACA 7 by 10-foot wind tunnel of a large-chord NACA 23012 airfoil with several arrangements of 25.66 percent chord slotted flaps to determine the section aerodynamic characteristics as affected by slot shape, flap shape, flap location, and flap deflection. The flap position for maximum lift, the polars for arrangements considered favorable for take-off and climb, and the complete section aerodynamic characteristics for selected optimum arrangements were determi… more
Date: February 24, 1939
Creator: Wenzinger, Carl J. & Harris, Thomas A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of Two Full-Scale Propellers With Different Pitch Distributions, at Blade Angles Up to 60 Degrees

Description: "Two 3-blade 10-foot propellers were operated in front of a liquid-cooled engine nacelle. The propellers differed only in pitch distribution; one had normal distribution (nearly constant pitch for a blade angle of 15 degrees at 0.75 radius), and the other had the pitch of the tip sections decreased with respect to that for the shank sections (blade angle of 35 degrees for nearly constant pitch distribution). Propeller blade angles at 0.75r from 15 degrees to sixty degrees, corresponding to desi… more
Date: April 14, 1938
Creator: Biermann, David & Hartman, Edwin P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental Investigation of the Momentum Method for Determining Profile Drag

Description: Report presents the results of an experimental investigation conducted in the full-scale tunnel to determine the accuracy of the Jones and the Betz equations for computing profile drag from total and static pressure surveys in the wake of wings. Surveys were made behind 6 by 8-foot airfoils of the NACA 0009, and 0018 sections at zero lift and behind the NACA 0012 at positive lifts. The surveys were made at various spanwise positions and at distances behind the airfoil ranging from 0.05c to 3.00… more
Date: 1939
Creator: Goett, Harry J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Service Stress on Impact Resistance, X-Ray Diffraction Patterns, and Microstructure of 25S Aluminum Alloy

Description: Report presents the results of a great number of tests made to determine the effect of service stresses on the impact resistance, the x-ray diffraction patterns, and the microstructure of 25s aluminum alloy. Many of the specimens were taken from actual propeller blades and others were cut from 13/16-inch rod furnished by the Aluminum Company of America.
Date: 1939
Creator: Kies, J. A. & Quick, G. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Theoretical Study of the Moment on a Body in a Compressible Fluid

Description: "The extension to a compressible fluid of Lagally's theorem on the moment on a body in an incompressible fluid and Poggi's method of treating the flow of compressible fluids are employed for the determination of the effect of compressibility on the moment of an arbitrary body. Only the case of the two-dimensional subsonic flow of an ideal compressible fluid is considered. As examples of the application of the general theory, two well-known systems of profiles are treated; namely the elliptic pr… more
Date: March 24, 1939
Creator: Kaplan, Carl
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Free-spinning wind-tunnel tests of a low-wing monoplane with systematic changes in wings and tails IV: effect of center-of-gravity location

Description: Eight wings and three tails, covering a wide range of aerodynamic characteristics, were independently ballasted so as to be interchangeable with no change in mass distribution. For each of the 24 resulting wing-tail combinations, observations were made of the steady spin for four control settings and of recoveries for five control manipulations. The results are presented in the form of charts comparing the spin characteristics. The tests are part of a general investigation being made in the NAC… more
Date: March 28, 1939
Creator: Seidman, Oscar & Neihouse, A. I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Experimental Verification of the Theory of Oscillating Airfoils

Description: "Measurements have been made of the lift on an airfoil in pitching oscillation with a continuous-recording, instantaneous-force balance. The experimental values for the phase difference between the angle of attack and the lift are shown to be in close agreement with theory" (p. 619).
Date: April 24, 1939
Creator: Silverstein, Abe & Joyner, Upshur T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Compressibility Burble and the Effect of Compressibility on Pressures and Forces Acting on an Airfoil

Description: "Simultaneous air-flow photographs and pressure-distribution measurements were made of the NACA 4412 airfoil at high speeds to determine the physical nature of the compressibility burble. The tests were conducted in the NACA 24-inch high-speed wind tunnel. The flow photographs were obtained by the Schlieren method and the pressures were simultaneously measured for 54 stations in the 5-inch-chord airfoil by means of a multiple-tube manometer. Following the general program, a few measurements of … more
Date: July 6, 1938
Creator: Stack, John; Lindsey, W. F. & Littell, Robert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Design Charts for Predicting Downwash Angles and Wake Characteristics Behind Plain and Flapped Wings

Description: "Equations and design charts are given for predicting the downwash angles and the wake characteristics for power-off conditions behind plain and flapped wings of the types used in modern design practice. The downwash charts cover the cases of elliptical wings and wings of taper ratios 1, 2, 3, and 5, with aspect ratios of 6, 9, and 12, having flaps covering 0, 40, 70, and 100 percent of the span. Curves of the span load distributions for all these cases are included" (p. 1).
Date: July 14, 1938
Creator: Silverstein, Abe & Katzoff, S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Interference of Tail Surfaces and Wing and Fuselage from Tests of 17 Combinations in the N.A.C.A. Variable-Density Tunnel

Description: "An investigation of the interference associated with tail surfaces added to wing-fuselage combinations was included in the interference program in progress in the NACA variable-density tunnel. The results indicate that, in aerodynamically clean combinations, the increment of the high-speed drag can be estimated from section characteristics within useful limits of accuracy. The interference appears mainly as effects on the downwash angle and as losses in the tail effectiveness and varies with t… more
Date: November 5, 1938
Creator: Sherman, Albert
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of an N.A.C.A. 23012 Airfoil with a Slotted Flap and Three Types of Auxiliary Flap

Description: An investigation was made in the N.A.C.A. 7- by 10-foot wind tunnel to determine the aerodynamic section characteristics of an N.A.C.A. 23012 airfoil with a single main slotted flap equipped successively with auxiliary flaps of the plain, split, and slotted types. A test installation was used in which an airfoil of 7-foot span was mounted vertically between the upper and the lower sides of the closed test section so that two-dimensional flow was approximated" (p. 699).
Date: October 31, 1938
Creator: Wenzinger, Carl J. & Gauvain, William E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tensile Elastic Properties of 18:8 Chromium-Nickel Steel as Affected by Plastic Deformation

Description: "The relationship between stress and strain, and between stress and permanent set, for 18:8 alloy as affected by prior plastic deformation is discussed. Hysteresis and creep and their effects on the stress-strain and stress-set curves are also considered, as well as the influence of duration of the rest interval after cold work and the influence of plastic deformation on proof stresses, on the modulus of elasticity at zero stress, and on the curvature of the stress-strain line. A constant (c su… more
Date: November 22, 1938
Creator: McAdam, D. J., Jr. & Mebs, R. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigations at supersonic speeds of 22 triangular wings representing two airfoil sections for each of 11 apex angles

Description: The results of tests of 22 triangular wings, representing two leading-edge shapes for each of 11 apex angles, at Mach numbers 1.62, 1.92, and 1.40 are presented and compared with theory. All wings have a common thickness ratio of 8 percent and a common maximum-thickness point at 18 percent chord. Lift, drag, and pitching moment are given for all wings at each Mach number. The relation of transition in the boundary layer, shocks on the wing surfaces, and characteristics of the pressure distribut… more
Date: March 30, 1949
Creator: Love, Eugene S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theoretical and analog studies of the effects of nonlinear stability derivatives on the longitudinal motions of an aircraft in response to step control deflections and to the influence of proportional automatic control

Description: Through theoretical and analog results the effects of two nonlinear stability derivatives on the longitudinal motions of an aircraft have been investigated. Nonlinear functions of pitching-moment and lift coefficients with angle of attack were considered. Analog results of aircraft motions in response to step elevator deflections and to the action of the proportional control systems are presented. The occurrence of continuous hunting oscillations was predicted and demonstrated for the attitude … more
Date: December 29, 1950
Creator: Curfman, Howard J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Transonic Flow Past Cone Cylinders

Description: "Experimental results are presented for transonic flow post cone-cylinder, axially symmetric bodies. The drag coefficient and surface Mach number are studied as the free-stream Mach number is varied and, wherever possible, the experimental results are compared with theoretical predictions. Interferometric results for several typical flow configurations are shown and an example of shock-free supersonic-to-subsonic compression is experimentally demonstrated" (p. 963).
Date: April 15, 1953
Creator: Solomon, George E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A unified two-dimensional approach to the calculation of three-dimensional hypersonic flows, with application to bodies of revolution

Description: A procedure for calculating three-dimensional steady and nonsteady supersonic flows with the method of characteristics is developed and discussed. An approximate method is deduced from the characteristics method and shown to be of practical value at high supersonic speeds.
Date: August 15, 1952
Creator: Eggers, A. J., Jr. & Savin, Raymond C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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High-Resolution Autoradiography

Description: This investigation was made to adapt wet-process autoradiography to metallurgical samples to obtain high resolution of segregated radioactive elements in microstructures. Results are confined to development of the technique, which was perfected to a resolution of less than 10 microns. The radioactive samples included carbon-14 carburized iron and steel, nickel-63 electroplated samples, a powder product containing nickel-63, and tungsten-185 in N-155 alloy.
Date: June 1, 1953
Creator: Towe, George C.; Gomberg, Henry J. & Freemen, J. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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