Wind Tunnel Tests of Supersonic Lifting Bodies at Mach Number 1.5 to 4.0.
BALLISTIC RESEARCH LABS ABERDEEN PROVING GROUND MD
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Wind tunnel tests were conducted on four new wedge shaped configurations, one of which approached that of a wave rider design. Aerodynamic data are presented for Mach numbers 1.5 through 4.0 with angle of attack variation from -10 to 7 deg. The data are similar to previously reported results with the one exception being the near wave rider configuration. This configuration resulted in liftdrag data being invariant with respect to Mach number. The maximum value of liftdrag reached approximately 3.0. Author
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