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Analysis of V-g data obtained from several naval airplanes

Description: From Introduction: "V-g records supplied the NACA by the Bureau of Aeronautics in 1948 and 1949 have provided additional material. These records are analyzed statistically in this report to the frequency of large values of acceleration and airspeed, and results are compared with the design requirements."
Date: July 7, 1950
Creator: Thornton, James O.
Partner: UNT Libraries Government Documents Department

The Calculation of the Path of a Jettisonable Nose Section

Description: Report presenting a method for calculating the path of a jettisonable nose section at any speed by means of successive approximations using static aerodynamic characteristics. Conditions for consideration, including the effect of stabilizing fins, are included in the calculations.
Date: September 7, 1950
Creator: Goodwin, Roscoe H.
Partner: UNT Libraries Government Documents Department

Determination of Longitudinal Stability of the Bell X-1 Airplane From Transient Responses at Mach Numbers Up to 1.12 at Lift Coefficients of 0.3 and 0.6

Description: Report presenting an analysis of a number of free-flight transient responses resulting from small stabilizer movements obtained during testing of the Bell X-1 airplane to obtain its longitudinal stability characteristics. A comparison of flight data and model test data is also provided.
Date: November 7, 1950
Creator: Angle, Ellwyn E. & Holleman, Euclid C.
Partner: UNT Libraries Government Documents Department

The Effect of Changes in the Leading-Edge Radius on the Aerodynamic Characteristics of a Symmetrical, 9-Percent-Thick Airfoil at High-Subsonic Mach Numbers

Description: Report of an investigation into the effect of leading-edge radius on the high-speed aerodynamic characteristics of a symmetrical, 9-percent-thick airfoil using three different airfoils at several Mach and Reynolds numbers. Information about the normal-force coefficients, drag coefficients, moment coefficients about the quarter chord, pressure-distribution diagrams, Schileren photographs, and a comparison with data obtained in other tunnels is included.
Date: August 7, 1950
Creator: Humphreys, Milton D. & Robinson, Raymond A.
Partner: UNT Libraries Government Documents Department

Effect of compressor-outlet bleedoff on turbojet-engine performance

Description: An investigation was conducted in the NACA Lewis altitude wind tunnel to determine the effect of compressor-outlet bleedoff on the performance of an axial-flow turbojet engine equipped with a variable-area exhaust nozzle. Results presented indicate the effect of compressor-outlet bleedoff on performance at altitudes of 25,000 and 40,000 feet and a flight Mach number of 0.53. Variation of performance with bleedoff flow is indicated for operation with fixed- and variable-area exhaust nozzles. Temperature and pressure losses through the bleedoff ducting system are also discussed.
Date: August 7, 1950
Creator: Fleming, William A.; Wallner, Lewis E. & Wintler, John T.
Partner: UNT Libraries Government Documents Department

Effect of dihedral change on the theoretical dynamic lateral response characteristics of a low-aspect-ratio straight-wing supersonic airplane

Description: Memorandum presenting the results of a theoretical investigation of the lateral response and stability characteristics of the X-3 research airplane (Douglas Model No. 499D). Included are time histories calculated by a computer showing the effect of various disturbances on the lateral response of the airplane with 0 degrees geometric dihedral and -5 degrees dihedral.
Date: December 7, 1950
Creator: Heinle, Donovan R.
Partner: UNT Libraries Government Documents Department

The effect of pile gas on tube block temperatures in {open_quotes}G{close_quotes} pile

Description: Helium, carbon dioxide, and helium-carbon dioxide mixtures are being considered for use as the pile gas in `G` pile. Coring the graphite tube block to provide a gas gap between the process tube centered in the graphite and the graphite tube block has been suggested as a means of maintaining high graphite temperatures in the tube blocks. It has been established that graphite damage during irradiation in minimized at high temperatures.
Date: April 7, 1950
Creator: Sega, C. A.
Partner: UNT Libraries Government Documents Department

Effect of Radiation on Television Equipment : Final Report

Description: The following report follows a test with the purpose of determining the effect upon image fidelity by exposing a television camera to high intensity radiation over an extended period. Provided later in the report are notes on the design of the utiliscope camera used for these tests due to notable design features.
Date: February 7, 1950
Creator: White, H. J.
Partner: UNT Libraries Government Documents Department

An investigation of three transonic fuselage air inlets at Mach numbers from 0.4 to 0.94 and at a Mach number of 1.19

Description: Report presenting an investigation of three air inlets designed for use at transonic speeds conducted in the 8-foot high-speed tunnel. The basis of the design of the inlets was the use of a nose which was shaped so that substream velocities are maintained on its surface for high-speed operating conditions. Results regarding impact pressure recovery, external pressure distributions, wake-survey drag, supersonic external pressure drag, and design considerations are provided.
Date: November 7, 1950
Creator: Pendley, Robert E.; Robinson, Harold L. & Williams, Claude V.
Partner: UNT Libraries Government Documents Department

Lateral-Control Investigation at a Reynolds Number of 5,300,000 of a Wing of Aspect Ratio 5.8 Sweptforward 32 Degrees at the Leading Edge

Description: Memorandum presenting the low-speed lateral control characteristics of a 32 degree sweptforward wing of aspect ratio 5.8 and NACA 65-series airfoil sections as determined in the 19-foot pressure tunnel. The investigation include the measurement of the hinge-moment and normal-force characteristics of an aileron and the rolling-effectiveness characteristics of the aileron and several configurations of spoilers.
Date: February 7, 1950
Creator: Graham, Robert R.
Partner: UNT Libraries Government Documents Department

[Layne Beaty embraces little girl]

Description: Photograph of reporter Layne Beaty and a little girl. Beaty is squatting down next to the little girl and she is kissing him on the cheek. In front of them sits a box that reads "WBAP, Fort Worth, TEX, USA."
Date: March 7, 1950
Creator: WBAP-TV (Television station : Fort Worth, Tex.)
Partner: UNT Libraries Special Collections

[Layne Beaty kisses woman]

Description: Photograph of Layne Beaty embracing a woman at an airport. Beaty stands in front of staircase and kisses a woman who holds a child in her hands.
Date: March 7, 1950
Creator: WBAP-TV (Television station : Fort Worth, Tex.)
Partner: UNT Libraries Special Collections

[Layne Beaty with a child]

Description: Photograph of Layne Beaty with a young child. He is squatting down next to the child who speaks close to his ear. The child wears a dress and a sweater while Beaty wears a suit.
Date: March 7, 1950
Creator: WBAP-TV (Television station : Fort Worth, Tex.)
Partner: UNT Libraries Special Collections

Low-Speed Pressure-Distribution Measurements at Reynolds Number of 3.5 X 10(Exp 6) on a Wing With Leading-Edge Sweepback Decreasing From 45 Degrees at the Root to 20 Degrees at the Tip

Description: "Results are presented of an investigation to determine the pressure distributions on a wing with leading-edge sweepback decreasing from 45 degrees at the root to 20 degrees at the tip, an aspect ratio of 4.12, taper ratio of 0.36, and NACA 64A009 airfoil section. Tests were conducted at a Reynolds number of 3.5 x 10(exp 6) and a Mach number of 0.07 on the wing with and without 0.20 chord and 0.65 span split flaps deflected 60 degrees. These pressure distributions are analysed herein to determine the character of flow and its effect on the stability of the wing" (p. 1).
Date: July 7, 1950
Creator: Barnett, U. Reed, Jr. & Lange, Roy H.
Partner: UNT Libraries Government Documents Department