Quarterly of Applied Mathematics

Quarterly of Applied Mathematics

Online ISSN 1552-4485; Print ISSN 0033-569X



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.

References [Enhancements On Off] (What's this?)

  • [1] J. W. Miles, A general solution for the rectangular airfoil in supersonic flow, Q. Appl. Math., 11, 1-8 (1952). MR 0053715
  • [2] 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. MR 0026501

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DOI: https://doi.org/10.1090/qam/57122
Article copyright: © Copyright 1953 American Mathematical Society

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