Computation and visualization of the inviscid drag coefficient and polar surfaces of the wedged delta wing in supersonic flow

The authors propose here the three-dimensional representations of the inviscid drag coefficient C-d((i))) (as function of the angle of attack alpha and of the Mach number M(infinity) of the incoming flow) and of the inviscid polar of the wedged delta wing in supersonic flow. A continuous behaviour of the class C-1 of the both surfaces along the sonic lines which separate the domains in which the delta wing has subsonic and, respectively, supersonic leading edges is to be observed, even the solutions of the boundary value problems of the axial disturbance velocities of the thin and thick-symmetrical delta wing components are, in these both regions, very different.