Analytical calculation of bow shock waves from delta shaped supersonic lifting wings

Abstract

In this thesis an acceleration potential (source) is used to investigate the effect of force distribution on the generation and decay of the bow shock waves due to delta wings with straight and curved leading edges in a supersonic flow field. Formulas for the bow shock strength are derived for an observer perpendicular below the wing and for the lateral direction as well. It is concluded that the equivalent body of revolution is valid throughout the supersonic far flow field. The decay of the shock waves is predicted for the observer in the plane vertical to the wing. Also, the position of the characteristics is corrected up to first order.