Wind tunnel test of the McDonnell Douglas Supersonic Cruise Aircraft, designed for a cruise Mach number of 2.2, was conducted in the NASA Ames Unitary Plan Wind Tunnels. Extensive force, pressure, and flow visualization data were obtained over a Mach number range from 0.5 to 2.4. Comparisons between theory and measurements of both forces and pressure concentrate on the results obtained in the supersonic tunnel. Schlieren and tuft pictures are presented to help provide an understanding of the nonlinearities observed at off-design conditions.
Aerodynamic validation of a SCAR design
1976-01-01
Conference paper
No indication
English
British Library Conference Proceedings | 2006
NTRS | 1976
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