A note on subsonic edges in unsteady supersonic flow
Author:
John W. Miles
Journal:
Quart. Appl. Math. 11 (1953), 363-367
MSC:
Primary 76.1X
DOI:
https://doi.org/10.1090/qam/57122
MathSciNet review:
57122
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Abstract: The pressure distribution due to the unsteady motion of a wing having a supersonic leading edge and a subsonic trailing edge is determined by applying a Lorentz transformation to the corresponding result for a rectangular wing. This result, valid as it stands for a subsonic leading edge, is then modified by the addition of an eigensolution in order to satisfy the Kutta condition.
J. W. Miles, A general solution for the rectangular airfoil in supersonic flow, Q. Appl. Math., 11, 1-8 (1952).
P. A. Lagerstrom, Linearized supersonic theory of conical wings, J. P. L. Prog. Rep. 4-36 Pasadena, 1947); reprinted as NACA TN 1685 (1948), 90-98.
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Article copyright:
© Copyright 1953
American Mathematical Society
