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  Partner: UNT Libraries Government Documents Department
 Decade: 1940-1949
 Serial/Series Title: NACA Research Memorandums
Effect of inlet-air parameters on combustion limit and flame length in 8-inch-diameter ram-jet combustion chamber

Effect of inlet-air parameters on combustion limit and flame length in 8-inch-diameter ram-jet combustion chamber

Date: July 22, 1948
Creator: Miller, R C & Cervenka, A J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of Mach number on performance of an axial-flow compressor rotor-blade row

Effect of Mach number on performance of an axial-flow compressor rotor-blade row

Date: September 28, 1948
Creator: Dugan, Paul D; Mahoney, John J & Benser, William A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Control requirements and control parameters for a ram jet with variable-area exhaust nozzle

Control requirements and control parameters for a ram jet with variable-area exhaust nozzle

Date: November 17, 1948
Creator: Boksenbom, Aaron S & Novik, David
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Design and performance of experimental axial-discharge mixed-flow compressor II : performance of impeller

Design and performance of experimental axial-discharge mixed-flow compressor II : performance of impeller

Date: August 12, 1948
Creator: Wilcox, Ward W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Design and performance of experimental axial-discharge mixed-flow compressor I : impeller design theory

Design and performance of experimental axial-discharge mixed-flow compressor I : impeller design theory

Date: August 12, 1948
Creator: Goldstein, Arthur W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Determination of average heat-transfer coefficients for a cascade of symmetrical impulse turbine blades I : heat transfer from blades to cold air

Determination of average heat-transfer coefficients for a cascade of symmetrical impulse turbine blades I : heat transfer from blades to cold air

Date: November 10, 1948
Creator: Meyer, Gene L
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Evaluation of gust and draft velocities from flights of an AT-6 airplane within cumulus clouds July 1, 1947 to July 22, 1947 at Clinton County Army Air Field, Ohio

Evaluation of gust and draft velocities from flights of an AT-6 airplane within cumulus clouds July 1, 1947 to July 22, 1947 at Clinton County Army Air Field, Ohio

Date: March 22, 1948
Creator: Funk, Jack
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Evaluation of gust and draft velocities from flights of P-61C airplanes within thunderstorms July 31, 1947 to August 6, 1947 at Clinton County Army Air Field, Ohio

Evaluation of gust and draft velocities from flights of P-61C airplanes within thunderstorms July 31, 1947 to August 6, 1947 at Clinton County Army Air Field, Ohio

Date: February 13, 1948
Creator: Funk, Jack
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Free-flight investigation at transonic and supersonic speeds of a wing-aileron configuration simulating the D-558-2 airplane

Free-flight investigation at transonic and supersonic speeds of a wing-aileron configuration simulating the D-558-2 airplane

Date: July 21, 1948
Creator: Sandahl, Carl A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Free-flight investigation at transonic and supersonic speeds of the rolling effectiveness of a 42.7 degree sweptback wing having partial-span ailerons

Free-flight investigation at transonic and supersonic speeds of the rolling effectiveness of a 42.7 degree sweptback wing having partial-span ailerons

Date: October 25, 1948
Creator: Sandahl, Carl A
Description: An investigation of the rolling effectiveness at transonic and supersonic speeds of partial-span ailerons on a 42.7 degree sweptback wing having symmetrical circular-arc airfoil sections of 10-percent thickness ratio normal to the wing quarter-chord line has been made by means of rocket-propelled test vehicles. The results are compared with results of a supersonic wind-tunnel test at Mach number 1.9.
Contributing Partner: UNT Libraries Government Documents Department
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