A comprehensive postflight wind tunnel investigation of the Apollo Command Module was conducted to resolve several anomalies between flight (AS-202) and preflight aerodynamic data. Attention was focused on (1) simulating the actual vehicle 'as flown', (2) obtaining consistent pitch plane force measurements in the angle-of-attack range 150 < or = alpha < or = 180 deg, (3) the effect of Mach number over a range of 3 to 20, (4) the effect of Reynolds number, and (5) possible sting effects. Results indicated that prior failure to duplicate the asymmetrical wavy heat shield in preflight testing resulted in a significant error in trim angle-of-attack prediction. In addition, a strong viscous influence was found to extend down to an altitude of about 220,000 ft. Also, a Mach number influence to a value of about 14 was found which is substantially higher than previous blunt body investigations have indicated. (Author)
Postflight (As-202) APOLLO Command Module Aerodynamic Simulation Tests
1968
113 pages
Report
Keine Angabe
Englisch
Manned Spacecraft , Fluid Mechanics , Aerodynamics , Manned spacecraft , Aerodynamic characteristics , Simulation , Lunar craft , Wind tunnel models , Pitch(Motion) , Angle of attack , Mach number , Reynolds number , Tables , Blunt bodies , Model tests , Statistical analysis , Apollo , Postflight testing , Apollo command modules , Sting effects
Postflight Apollo command module aerodynamic simulation tests
Engineering Index Backfile | 1968
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