Abstract
The linearized method of conical fields (1, see also 2) is applied to determine the pressure distribution on certain flat-plate wings at incidence to a stream composed of two adjacent plane uniform supersonic jets with different velocities and densities, and separated by a plane vortex sheet. The leading edges of the wing are straight, intersect on the jet boundary, and lie outside the Mach semi-cones of this intersection (see Fig. 1); the edges may be either swept back or swept forward. The pressure coefficients on the upper wing surface inside the Mach semi-cone in the port and starboard jets are determined. It is shown that there are five typical cases for the pressure distribution, and the pressure coefficients on the upper surface have been computed with values of the parameters chosen to represent these five cases. The results are set out in Tables I and II and shown graphically in Figs. 8 to 12. Two examples of physical application may be cited. Firstly, the solution gives the pressure distribution on the part of a control surface of a supersonic aircraft which is subject to interference from a propelling jet. Secondly, the solution may be used to give a first approximation to the pressure distribution on a wing in a non-uniform parallel stream, by replacing this stream by a series of discrete adjacent uniform streams and applying the method of superposition described in (2).
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