Charts For Determining Jet Boundary Corrections For Complete Models In 7 By 10 Foot Closed Rectangular Wind Tunnels
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Investigation of the Variation of Maximum Lift for a Pitching Airplane Model and Comparison with Flight Results
Author | : Paul W. Harper |
Publisher | : |
Total Pages | : 704 |
Release | : 1948 |
Genre | : Airplanes |
ISBN | : |
Apparatus was developed which utilized a pitching airplane model to determine maximum wing loads as a function of the rate of change of angle of attack. In order to evaluate the pitching-model technique, the maximum lift coefficient was determined as a function of the rate of change of angle of attack over a Mach number range from approximately 0.2 to 0.6 in wind-tunnel tests of a 1/20-scale model of a conventional single-engine fighter airplane and was conpared with existing flight data of this airplane. The wind-tunnel and flight results were found to be in good agreement.
Method for Calculating Effects of Dissociation on Flow Variables in the Relaxation Zone Behind Normal Shock Waves
Author | : John S. Evans |
Publisher | : |
Total Pages | : 668 |
Release | : 1956 |
Genre | : Air flow |
ISBN | : |
Because the chemical reaction rates needed to predict the dependence of degree of dissociation on distance behind the shock are not known, order-of-magnitude estimates of their values have been used in a numerical example, the purpose of which is to illustrate the use of reaction-rate equations to predict relaxation time and distance behind the shock front.
Index of NACA Technical Publications
Author | : United States. National Advisory Committee for Aeronautics |
Publisher | : |
Total Pages | : 1370 |
Release | : 1949 |
Genre | : Aeronautics |
ISBN | : |
NASA Memorandum
Author | : United States. National Aeronautics and Space Administration |
Publisher | : |
Total Pages | : 590 |
Release | : 1959 |
Genre | : Aeronautics |
ISBN | : |