Abstract:
Leading edge flows, present in the incidence range embracing the onset of general nose separation, have been studied experimentally. The effect of nose droop of these flows was established during the development of this device as a possible alternative to leading-edge flaps on the aircraft. Discrete air jets and vane type vortex generators were investigated in regard to both boundary-layer and hysteresis control. The influence of trailing-edge flaps on leading edge separation phenomena was also studied. The concepts outlined in regard to the nature of nose stalling problems and the quantitative data presented should have application in respect to general wing design.
