The Downwash of Swept-back Wings having the Leading Edge Separation

The effects of the leading edge separation on the downwash of swept-back wings is discussed by the theoretical and experimental considerations. It is concluded that the occurrence of the part-span vortices extremely increase the downwash at tailplane. The downwash of swept-back wings having the leading edge separation should not be calculated only from the lift distribution, but also from the consideration of the existence of the leading edge separation vortices.