Volume 5, Juin 2013Progress in Flight Physics
|Page(s)||247 - 284|
|Section||Chapter Five. Shock interaction|
|Published online||14 June 2013|
Numerical analysis of three complex three-dimensional shock wave / turbulent boundary layer interaction flows
Ramgen Power Systems, LLC Bellevue WA, USA
2 Khristianovich Institute of Theoretical and Applied Mechanics Siberian Branch of the Russian Academy of Sciences Novosibirsk, Russia
3 Oak Ridge National Laboratory Oak Ridge TN, USA
4 Numeca USA San Francisco CA, USA
A set of Reynolds-averaged Navier-Stokes (RANS) computations with turbulence closure provided by the Spalart-Allmaras (SA) model have been carried out for prediction of shock-induced three-dimensional (3D) turbulent separated flows. The experimental data for different aerodynamic test configurations have been used for assessing credibility of the numerical method employed. Particularly, shock wave / turbulent boundary layer interactions (SWTBLI) in the vicinity of an asymmetric sharp double-fin (DF) with different (7° and 11°) deflection angles mounted on a flat plate and two conically sharp cylindrical bodies at varying interbody distances and nose cone angles 60° and 40° mounted over a flat plate at freestream Mach number 4, as well as a transonic fan stage operating in the near-stall regime are considered. The gas dynamic structure and topology of 3D separated flows, surface flow patterns, and pressure distributions as well as body aerodynamic force prediction are analyzed. A transonic fan stage operating in the near-stall regime and a possibility of applying flow control is investigated. High Performance Computing was employed to make high resolution computations of these flows possible, and advanced 3D visualization techniques were employed in order to improve understanding of the separating flow phenomena.
© Owned by the authors, published by EDP Sciences, 2013
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