CONTROL-SURFACE INTERACTION EFFECTS ON DELTA-WING WINDWARD PRESSURES AT A MACH NUMBER OF 6.83 AT HIGH ANGLES OF ATTACK

摘要

An experimental investigation has been conducted to determine the effects of nose incidence and trailing-edge-flap deflections on the windward pressure distribution over a 70° sweep delta wing at a Mach number of 6.83. The study was conducted over an angle-of-attack range from 30° to 90° with nose incidence of 0° to 20° and flap deflections of 10° to -90° at a Reynolds number of 0.6 X 106, based on mean aerodynamic chord.nNose incidence produced large overexpansion effects on stations Immediately behind the nose hinge line for the lower angles of attack, but did not significantly affect the pressure level over the rear portion of the wing. A similar overexpansion effect, produced by the middle panel, also occurred on negatively deflected flaps. These overexpansion effects were limited to angles of attack below about 70° and were not significantly affected by nose incidence. Large negative flap deflections caused a pressure reduction to occur ahead of the flap hinge line at the high angles of attack. Nose incidence had little effect on this flap-induced pressure reduction.