Off-design Reynolds number effects for a supersonic transport

A high-Reynolds-number wind-tunnel investigation was conducted to assess Reynolds-number effects on the aerodynamic performance characteristics of a realistic, second-generation, supersonic transport concept. The tests included longitudinal studies at transonic and low-speed, high-lift conditions across a range of chord Reynolds numbers (8 x 106 to 120 x 106). Results presented focus on Reynolds-number and static aeroelastic sensitivities at Mach 0.30 and 0.90 for a configuration without a tail. Static aeroclastic effects, which mask Reynolds-number effects, were observed. Reynolds-number effects were generally small, and the drag data followed established trends of skin friction as a function of Reynolds number. Wing boundary layers thinned as Reynolds number increased producing a more nose-down pitching moment because of the increased effective wing camber. This study extends the existing Reynolds-number database for supersonic transports operating at off-design conditions.