Sidewall Boundary-Layer Influence on Shock Wave/Turbulent Boundary-Layer Interactions

Abstract

Gl, G2 = shock generator # 1, # 2 M = Mach number P = pressure Re^ — freestream unit Reynolds number Redot = Reynolds number based on 60* S, R = separation, reattachment T = temperature W = test surface span x = axial coordinate xi = shock intercept with test surface in the absence of any boundary layer y* = vertical coordinate of sonic line a = shock generator angle of attack 6 = boundary-layer thickness 6* = displacement thickness 6 = momentum thickness