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This quantity supplies effects, views and case experiences for the therapy of difficulties bobbing up in transonic aerodynamics, the research of the aerodynamics of flight at speeds close to the rate of sound. info at the triple deck conception and the transonic sector rule is usually offered.
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This quantity provides effects, views and case experiences for the remedy of difficulties bobbing up in transonic aerodynamics, the learn of the aerodynamics of flight at speeds close to the rate of sound. info at the triple deck conception and the transonic quarter rule is usually offered.
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Additional resources for Transonic Aerodynamics: Problems in Asymptotic Theory (Frontiers in Applied Mathematics)
P. Cook, Transonic Aerodynamics, North-Holland, Amsterdam, 1986.  P. G. Drazin and W. H. Reid, Hydrodynamic Stability, Cambridge University Press, Cambridge, 1981.  M. J. Lighthill, On boundary layers and upstream influence II, Supersonic flows without separation, Proc. Roy. Soc. London, Ser. A, 217 (1953), pp. 478-507.  C. C. Lin, E. Reissner, and H. S. Tsien, On two-dimensional non-steady motion of a slender body in a compressible fluid, J. Math. , 27 (1948), pp. 220-231.  A. F. Messiter, Boundary-layer flow near the trailing edge of a flat plate, SIAM J.
53-57 (in Russian).  O. S. Ryzhov, On an unsteady boundary layer with the self-induced pressure in the transonic velocity range of an external stream, Dokl. Akad. Nauk SSSR, 236 (1977), pp. 1091-1094 (in Russian).  , Asymptotic methods in transonic flow theory. In Symposium Transsonicum III, J. Zierep and H. , Springer-Verlag, Berlin, 1989, pp. 143-155.  O. S. Ryzhov and I. V. Savenkov, On the boundary-layer stability in the transonic velocity range of an external stream, Zh. Prikl. Mekh.
24g,h), and the no-slip conditions u = v = 0 on the obstacle surface y = yw(x) rather than at y — 0. Besides, the additional requirements u —> 0, p —> 0 should be met at the entry, x —>• -co, into the viscous sublayer. The results of numerical calculations presented in Fig. 4a,b show the streamline shapes in the vicinity of the hump yw — h(l + cosx), h = 2, — TT < x < TT for two values of KOO = ^3 . According to them the velocity field changes drastically when the subcritical regime is superseded by the supercritical one.