Wind-tunnel investigation was conducted 1) to simulate actual vehicle "as flown" (AS-202) in model construction, 2) to obtain consistent pitch plane force measurements in angle-of-attack range 150° equal to or less than α equal to or less than 180°, 3) to determine effects of Mach number (from 3 to 20) and Reynolds number, and 4) to evaluate possible sting effects; study showed that influence of ablator (heat shield) geometry prior to ablation causes significant change in trim angle of attack and resulting decrease in available lift-to-drag ratio.
Postflight Apollo command module aerodynamic simulation tests
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 5 , n 7
1968
6 pages
Article (Journal)
English
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