Abstract
SummaryFor supersonic wings it is known that the presence of a tip reduces the lift and the performance compared with the corresponding values for the two-dimensional wing. It appeared from some work by K. Stewartson that the addition of a vane at the wing tip might counteract this effect. The purpose of this paper is to determine the effect due to the presence of the vane. For this purpose a wing in the form of a semi-infinite wedge whose leading edge is swept back is supposed placed at incidence to the flow, with a symmetric triangular vane with diamond-shaped base attached to it, its vertex being at the tip of the leading edge, and its plane of symmetry parallel to the flow. The problem is of the “conical field” type and is solved by the method of S. Goldstein and G. N. Ward.The problem is divided into its anti-symmetrical and symmetrical parts. The results obtained in Ref. 1 are applied to determine the field in each case, both outside and inside the Mach cone of the vertex.
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