Volume 5, Juin 2013Progress in Flight Physics
|Page(s)||327 - 348|
|Section||Chapter Five. Shock interaction|
|Published online||14 June 2013|
Three-dimensional shock-wave/boundary-layer interaction at the presence of entropy layer
Central Aerohydrodynamic Institute (TsAGI)
An experimental and numerical investigation of a gas flow on a flat plate near a single fin and a fin pair, generating crossings shocks, is performed. The study is focused on the plate bluntness influence on the flow field and the heat transfer in the interaction region. The experiments are carried out in a short duration wind tunnel at Mach numbers M = 5, 6, and 8 and Reynolds numbers Re∞L up to 27·106. Luminescent substances are used for heat flux and pressure distribution measurements and for the surface flow visualization. In addition, the heat flux is measured with thermocouple sensors. For a numerical flow simulation, the three-dimensional (3D) Reynolds-averaged Navier-Stokes (RANS) equations are solved using the q-ω turbulence model. It is found that even a small plate blunting affects heat transfer and pressure distributions significantly. Moreover, in the case of crossing shocks, it can cause a global transformation of the flow structure in the area of the interaction between the shock waves and the boundary layer.
© Owned by the authors, published by EDP Sciences, 2013
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