Aerodynamic characteristics at Mach number 0.2 of a wing-body concept for a hypersonic research airplane

The static aerodynamic characteristics were studied on a model wing-body concept for a high-speed research airplane in a low-turbulence pressure tunnel. The experiment consisted of configuration buildup from the basic body by adding a wing, center vertical tail, three-module scramjet, and six-module scramjet engine. The test Mach number was 0.2 at Reynolds numbers, based on fuselage length, ranging from 2.78 x 1 million to 23 x 2 million. The test angle-of-attack range was approximately -5 to 30 deg at constant angles of sideslip of 0 deg and 4 deg. The elevons were deflected from 5 deg to -15 deg. Roll and yaw control were investigated.