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NUMERICAL SIMULATION OF STABILITY OF A SUPERSONIC NEAR-WALL FLOW PAST ROUNDED COMPRESSION CORNER

DOI: 10.1615/ICHMT.2008.CHT.1930
9 pages

Alexander Vitalyevich Fedorov
Central Aerohydrodynamic Institute (TsAGI), 1, Zhukovsky Str., Zhukovsky, Moscow Region, 140180, Russian Federation; Moscow Institute of Physics and Technology (MIPT), 9 Institutskiy Per., Dolgoprudny, Moscow Region, 141700, Russian Federation

Andrey V. Novikov
Central Aerohydrodynamic Institute (TsAGI), Zhukovsky, Moscow region 140180, Russia

Abstract

Two-dimensional (2D) direct numerical simulation of unsteady supersonic flow past a compression corner of different roundings is carried out for regimes relevant to boundary layer separation. The compressible 2D Navier−Stokes equations are solved for unstable disturbances generated by a local forcing (periodic suction-blowing) inside the boundary layer in the vicinity of the forebody leading edge upstream of the separation bubble. Numerical results are compared with results of similar calculations for a flat plate. It is shown that the second-mode waves of the boundary layer are stabilized in the separation bubble, while they grow intensively behind the reattachment point. Acoustic modes excited inside the separation bubble are investigated using numerical calculations and asymptotic analysis.

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