03.3 - Basic Fluid Dynamics and Flow Control
STUDY ON THE STATISTICAL CHARACTERISTICS OF SKIN FRICTION OF SHOCK WAVE/ TURBULENT BOUDARY LAYER INTERATION IN A HOLLOW FLARE CONFIGURATION AT MACH 6
P.F. Shen ¹, H.Y. Cai, School of Aeronautics, Northwestern Polytechnical University, China; P.X. Liu¹, D. Sun¹, X.X. Yuan¹; ¹State Key Laboratory of Aerodynamics, China
Shock Wave/Turbulent Boundary Layer Interaction is common on the surfaces of current hypersonic vehicles with strong nonlinear effect on turbulent boundary layer. The present work mainly focuses on the skin friction of Shock Wave/Turbulent Boundary Layer Interaction. The exact coherent vortical structures and statistical properties have been obtained. And Reynolds-average skin friction could be decomposed into 5 parts. Results of decomposition indicate that turbulent dissipation part and viscous dissipation part mainly contribute on the full skin friction. After shock wave interaction, convection and turbulent dissipation increase obviously while viscous dissipation decreases respectively, and absolute value of streamwise heterogeneous item increases obviously but its sign becomes vice while it is positive on plate turbulent boundary layer.