Linearized supersonic aerofoil theory part I

Abstract

Linearized supersonic aerofoil theory is developed by operational methods. It is shown that a wide variety of problems can be handled by these methods, which have the advantage of very directly exhibiting the analogies between supersonic aerofoil and other wave problems. Results for the lift and drag on semi-infinite rectangular wings obtained by the cone-field method of Busemann are confirmed, and a recurrence method is developed for dealing with a finite rectangular wing of arbitrary chord. A very general Green’s function method, analogous to that employed in diffraction problems, is also developed by means of which a wide class of problems involving tapered wings or curved leading edges can be solved.