A note on subsonic edges in unsteady supersonic flow
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 0053715, 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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