Generalized conical-flow fields in supersonic wing theory

Harvard Lomax, Max A. Heaslet
naca-tn-2497
Sep 1951


Linearized, compressible-flow analysis is applied to the study of quasi-conical supersonic wing theory. Single-integral equations are derived which relate either the loading to the shape of a lifting surface or the thickness of a symmetrical wing to the pressure distribution for triangular wings with subsonic leading edges. The forms of these equations and their inversions are simplified through the introduction of the finite part and the generalized principal part of an integral.

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