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Investigations of generalized conical flow fields

The conical transformation of variables of M.D. Haskind and S. V. Falkovich is applied to the steady-state problem of thin delta wings with subsonic leading edges in a supersonic flow. It is shown that solutions may be obtained, in terms of elliptic functions, for lifting wings of zero thickness with prescribed angle-of-attack distribution, and for symmetric non-lifting where the perturbation pressure is prescribed on the wing surface (thickness case, mean-surface assumption); the wing boundary conditions are assumed to be given in terms of polynomials in the space variables in the plane of the wing. Some previously known results are obtained to illustrate the method of analysis.

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Investigations of generalized conical flow fields