Two-Dimensional Shock-Wave/Boundary-Layer Interaction in the Presence of Entropy Layer Volf Y. Borovoy, * Ivan V. Egorov, † Arkady S. Skuratov, ‡ and Irina V. Struminskaya § TsAGI, 140180 Zhukovsky, Russia DOI: 10.2514/1.J051496 Results of experimental and numerical study of gas flow and heat transfer in the region of interference of the impinging oblique shock wave with the near-wall flow on sharp and blunt plates are presented. The study is performed for the freestream Mach numbers from 5 to 10 and Reynolds numbers from 0.3 × 10 6 to 27 × 10 6 corresponding to the laminar and turbulent undisturbed boundary layers. The plate bluntness, location of the impinging shock, and the shock strength are varied. It is shown that the plate bluntness significantly reduces the heat transfer in the interference region due to the increase of separation-zone size and the reduction of gas density in the high-entropy layer. As the plate bluntness increases the heat transfer decays to a certain threshold value of the bluntness radius. The bluntness effect on the heat transfer increases and the bluntness threshold value decreases with the freestream Mach number. Nomenclature C p = pressure coefficient c p = specific heat at constant pressure e = total energy H = total enthalpy h = static enthalpy L = model length l s = length of the separation zone p = pressure q = square root of the turbulent kinetic energy q h = heat flux R = body radius r = bluntness radius of the plate leading edge Re 1 = unit Reynolds number, 1∕m Re ∞L = Reynolds number based on the parameters of undisturbed flow and the model length St = q h ∕ρ ∞ u ∞ c p T t − T w  Stanton number T = temperature t = time u, v = velocity components x, y = Cartesian coordinantes x g , y g = distances between the plate and the shock wave generator β = slope angle of the shock wave γ = specific heat ratio Δ = thickness of the high-entropy layer δ = boundary-layer thickness δ  = boundary-layer displacement thickness η, ξ = curvilinear coordinates θ = flow deflection angle behind an oblique shock wave λ, λ T = coefficients of molecular and turbulent heat con- ductivity μ, μ T = coefficients of molecular and turbulent viscosity ρ = density τ = viscous stress tensor χ L = parameter of viscous-inviscid interaction ω = turbulent eddy frequency Subscripts b = on the blunt plate g = generator of the impinging shock L = based on the plate length m = maximum value ms = maximum value on the sharp plate o = without impinging shock os = on the sharp plate without impinging shock S = separation point s = on the sharp plate sh = point of shock incidence (or of its continuation) st = at isentropic stagnation of the flow behind the normal shock sw = point where the high-entropy layer is swallowed by the boundary layer t = total flow parameters t∞ = at isentropic stagnation of the undisturbed flow th = threshold value w = on the plate surface 1 = behind the impinging shock 2 = behind the reflected shock Δ = in the high-entropy layer ∞ = undisturbed flow I. Introduction T HE shock-wave interaction with the streamlined body surface is one of the fundamental problems of modern aerodynamics. This problem is important for actual high-speed vehicles having wings, control surfaces, and air inlets. The presence of compressing surfaces (wedges and cones) generating oblique shock waves is a charac- teristic feature of a supersonic or hypersonic air inlet. The leading edges of a hypersonic inlet must be blunted to restrict the surface temperature, and the bluntness should be small in order to reduce total pressure losses. Due to the impact of these factors the heat flux at the inlet achieves extreme values. Both the leading edges and vast zones of the channel inner surface, where the shock waves interact with the boundary layer, are subjected to intense heating. Presented as Paper 2011-731 at the 49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, Orlando, Florida, 4–7 January 2011; received 18 August 2011; revision received 23 May 2012; accepted for publication 1 June 2012; published online 19 November 2012. Copyright © 2012 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. Copies of this paper may be made for personal or internal use, on condition that the copier pay the $10.00 per-copy fee to the Copyright Clearance Center, Inc., 222 Rosewood Drive, Danvers, MA 01923; include the code 1533-385X/12 and $10.00 in correspondence with the CCC. *Chief Scientist, Hypersonic Aerothermodynamics Department; volf .borovoy@gmail.com. † Head of Hypersonic Aerothermodynamics Department, 1 Zhukovsky St.; ivan.egorov@tsagi.ru. ‡ Head of Scientific Sector, Hypersonic Aerothermodynamics Department; skuratov@progtech.ru. § Senior Research Engineer, Hypersonic Aerothermodynamics Department. 80 AIAA JOURNAL Vol. 51, No. 1, January 2013 Downloaded by Duke University on January 16, 2013 | http://arc.aiaa.org | DOI: 10.2514/1.J051496