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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 | References | Similar Articles | Additional Information
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.
- John W. Miles, A general solution for the rectangular airfoil in supersonic flow, Quart. Appl. Math. 11 (1953), 1–8. MR 53715, DOI https://doi.org/10.1090/S0033-569X-1953-53715-2
- P. A. Lagerstrom, Linearized supersonic theory of conical wings, Tech. Notes Nat. Adv. Comm. Aeronaut. 1948 (1948), no. 1685, viii+161. MR 0026501
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Article copyright:
© Copyright 1953
American Mathematical Society