Micro-actuators for control of delta wing with sharp leading edge

Abstract

Low speed wind tunnel measurements were conducted with a 0.4 m span 57.3° sweep delta wing with a sharp leading edge. Rectangular leading edge flaps ranging in width from 1.5 mm to 3 mm were used to generate and control separation vortices over the suction side of the delta wing. The flaps were inclined from an angle perpendicular to the pressure side through 180°. The purpose of the measurements is to assess the potential of using small leading edge flaps on a sharp edge delta for roll control. Static tests measured the force and moment generated by the deflection of the flaps. Flow visualization illustrated the resulting change in the vortex origin. The maximum resultant torque is about half as large as results from rounded leading edge experiments, but provides similar control at high angles of attack.