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Effects of a J34 Turbojet Engine on Supersonic Diffuser Performance

Report presenting testing of a translating cone inlet with a variable bypass at Mach numbers 1.6, 1.8, and 2.0 with both a choked exit plug and a J34 turbojet engine. The main difference between the two options was increased inlet subcritical stability with the engine. Results regarding basic diffuser performance, inlet stability, buzz amplitude and frequency, and diffuser-exit profiles are provided.

Date: January 4, 1956

Creator: Beheim, Milton A. & Englert, Gerald W.

Item Type: Report

Partner: UNT Libraries Government Documents Department

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The Nature of Air Flow About the Tail of an Airplane in a Spin

"Air flow about the fuselage and empennage during a high-angle-of-attack spin was made visible in flight by means of titanium-tetrachloride smoke and was photographed with a motion-picture camera. The angular relation of the direction of the smoke streamer to the airplane axes was computed and compared with the angular direction of the motion in space derived from instrument measurement of the spin of the airplane for a nearly identical mass distribution. The results showed that the fin and upp… more

Date: May 1932

Creator: Scudder, N. F. & Miller, M. P.

Item Type: Report

Partner: UNT Libraries Government Documents Department

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Methods of Visually Determining the Air Flow Around Airplanes

"This report describes methods used by the National Advisory Committee for Aeronautics to study visually the air flow around airplanes. The use of streamers, oil and exhaust gas streaks, lampblack and kerosene, powdered materials, and kerosene smoke is briefly described. The generation and distribution of smoke from candles and from titanium tetrachloride are described in greater detail because they appear most advantageous for general application. Examples are included showing results of the v… more

Date: July 1932

Creator: Gough, Melvin N. & Johnson, Ernest

Item Type: Report

Partner: UNT Libraries Government Documents Department

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Considerations of air flow in combustion chambers of high-speed compression-ignition engines

The air flow in combustion chambers is divided into three fundamental classes - induced, forced, and residual. A generalized resume is given of the present status of air flow investigations and of the work done at this and other laboratories to determine the direction and velocity of air movement in auxiliary and integral combustion chambers. The effects of air flow on engine performance are mentioned to show that although air flow improves the combustion efficiency, considerable induction, fri… more

Date: April 1932

Creator: Spanogle, J. A. & Moore, C. S.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

The 7 by 10 Foot Wind Tunnel of the National Advisory Committee for Aeronautics

This report presents a description of the 7 by 10 foot wind tunnel and associated apparatus of the National Advisory Committee for Aeronautics. Included also are calibration test results and characteristic test data of both static force tests and autorotation tests made in the tunnel.

Date: October 22, 1931

Creator: Harris, Thomas A.

Item Type: Report

Partner: UNT Libraries Government Documents Department

open access

Pressure distribution over airfoils at high speeds

This report deals with the pressure distribution over airfoils at high speeds, and describes an extension of an investigation of the aerodynamic characteristics of certain airfoils which was presented in NACA Technical Report no. 207. The results presented in report no. 207 have been confirmed and extended to higher speeds through a more extensive and systematic series of tests. Observations were also made of the air flow near the surface of the airfoils, and the large changes in lift coefficie… more

Date: 1927

Creator: Briggs, L. J. & Dryden, H. L.

Item Type: Report

Partner: UNT Libraries Government Documents Department