Abstract:
According to the linearized theory of supersonic flow, both the local slope of the mean surface of a wing producing a specified distribution of lift and the pressure on a wing due to a specified distribution of volume are given as singular double integrals. The numerical evaluation of these is described for planforms with curved subsonic leading edges and supersonic trailing edges for the cases in which the lift distribution tends to zero like the square root of the distance from the leading edge and the volume distribution has a finite slope there. Examples are given illustrating the use of these methods in the design of slender wings.
