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Wind Tunnel Tests of Supersonic Lifting Bodies at Mach Number 1.5 to 4.0.

Charles J. Nietubicz

Abstract

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 lift/drag data being invariant with respect to Mach number. The maximum value of lift/drag reached approximately 3.0. (Author)

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Key concepts: Mach number, Supersonic wind tunnel, Drag divergence Mach number, Wave drag, Aerodynamics, Wind tunnel, Supersonic speed, Lift (data mining)