Large-eddy simulation of shock/cooling-film interaction

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[1] Konopka, Martin
[2] Meinke, Matthias
[3] Schröder, Wolfgang
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Konopka, M. | 1600年 / AIAA International卷 / 50期
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The interaction of shock waves with supersonic cooling films is analyzed using large-eddy simulations. The laminar cooling flow is injected at Mach 1.2 through a slot into a fully turbulent boundary layer at Mach 2.44. For this injection condition; three configurations are investigated. A zero-pressure-gradient flow is compared with two configurations where shock waves are generated by a flow deflection of 5 deg. The shock waves impinge onto the cooling flow at two positions downstream of the slot. When the impingement is located within the potential-core region of the cooling flow; the adiabatic cooling effectiveness is reduced by as much as 36% compared to the zeropressure- gradient configuration because the shock/cooling-film interaction excites a transition of the laminar slot boundary layer. Additionally; turbulence levels are significantly increased by the shock wave; and high temperature fluctuations occur. When the shock-wave impingement is located further downstream of the slot; there is an even steeper slope in cooling effectiveness in the streamwise direction. That is; the slope is 37 and21% steeper compared to the zero-pressure gradient and the potential-core cases. The turbulent Prandtl number varied over the flow region of the shock/cooling-film interaction from 0.5 to 2. Copyright © 2012 by M. Konopka; M; Meinke; and W. Schröder. Published by the American Institute of Aeronautics and Astronautics; Inc; with permission. All rights reserved;
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