Abstract
The method of matched asymptotic expansions is used to investigate the unsteady flow over a short flap deflected through an angle of order R−1/4 in a supersonic stream in a characteristic time ∼ R−1/4. The length of the flap and the pressure difference at the trailing edge are assumed to be such that an interaction region is formed near the flap for which the asymptotic description in the limit R → ∞ is analogous to the description of the flow in the neighborhood of the trailing edge of an oscillating plate [7]. A numerical method is proposed for calculating the unsteady flow and the heat fluxes in the viscous wall layer. The results of calculations make it possible to estimate the influence of the viscous interaction in unsteady flows on the aerodynamic coefficients of control elements of aircraft and the distribution of the heat fluxes over the surface of the body.
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Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 4, pp. 111–118, July–August, 1981.
I am grateful to V. Ya. Neiland for valuable advice in a discussion of the work.
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Kazakov, A.V. Unsteady viscous supersonic flow over a short flap. Fluid Dyn 16, 579–585 (1981). https://doi.org/10.1007/BF01094603
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DOI: https://doi.org/10.1007/BF01094603