On the Wave Drag of Wing-Body Combination Moving at Supersonic Speeds

The present paper deals with the wave drag problem of wing-body combination at supersonic speeds by use of the linearized small perturbation theory. The potential functions due to body alone and wing alone are obtained, respectively, by source distributions on the body axis and the wing plane. Then, the interference potential function is so determined that the boundary conditions are satisfied on the wing plane and the symmetry plane. It consists of an additional source and a quadrupole distributions on the body axis. It turns out that the latter has negligible effects on the drag of wing-body combinations with a triangular wing. A general expressions of the wave drag of zero-lift wing-body combinations is obtained in terms of the thickness distribution of the wing and the sectional area distribution of the body. A numerical calculation is carried out for a cone-cylinder with a low-aspect-ratio delta wing.