AERODYNAMIC CHARACTERISTICS OF ROLLED SST CONFIGURATION WITH LE AND TE FLAPS AT HIGH ANGLES OF ATTACK

Wind tunnel tests were conduced to investigate roll characteristics of an SST configuration both with leading-edge flaps on the inboard and outboard wing and with trailing-edge flaps. Force measurements, surface pressure measurements and flow visualization tests were performed for the configuration with or without flap deflection. The test results indicated that rolling moments are stable for the models both with and without flap deflection at low incidence angles. At high incidence angles, unstable rolling moment was observed at limited roll angle for the model without flap deflection. Drastic change of rolling moment was observed at higher incidence angles when each flaps deflection.