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NUMERICAL INVESTIGATION OF SHOCK WAVE AND TURBULENT BOUNDARY LAYER INTERACTION ON AN AIRFOIL

Li-Wei Chen
Department of Modern Mechanics, University of Science and Technology of China Hefei, Anhui 230026, China

Chang-Yue Xu
Department of Modern Mechanics, University of Science and Technology of China Hefei, Anhui 230026, China

Xi-Yun Lu
Department of Mechanics and Mechanical Engineering, University of Science and Technology of China Hefei, Anhui 230026, China

Sinopsis

Shock wave and turbulent boundary layer interaction on an 18% thick circular-arc airfoil was studied numerically using detached-eddy simulation for a free-stream Mach number M = 0.76 and a Reynolds number Re = 1.1 × 107. Results have been validated carefully against experimental data. Based on the flow characteristics, three typical flow regimes are classified as attached boundary layer, moving shock wave/turbulent boundary layer interaction, and intermittent boundary layer separation region. The turbulent statistical quantities have been analyzed in detail and different behaviors are found in the three flow regimes. Some quantities, e.g. pressure-dilatation correlation and dilatational dissipation, have exhibited that the compressibility effect is enhanced due to the shock wave/boundary layer interaction. The results obtained in this study provide a physical insight into the understanding of the mechanisms underlying in this complex flow.