Compressible, turbulent flow with boundary-layer heat addition

摘要: One proposed method of achieving a reduction in viscous drag or skin friction scramjet combustors is through hydrogen combustion the boundary layer. Previous experimental work performed at University Queensland indicated that reductions 80% were possible. This paper studies effects heat release on supersonic layers conditions typically found within combustor duct using three-dimensional turbulent compressible flow solver with finite volume formulation for solution Navier-Stokes equations. Large-Eddy Simulation (LES) approximate deconvolution model includes turbulence. Three supersonic, perfect gas, flat-plate are studied. The first condition validation case Mach 2.88 Reynolds number 2 × 10 (based incoming layer thickness, Re). next two cases 4.42 and 4.21 flows (Re) 8.4 6.3 respectively. results obtained all three compare very well theoretical data give insight into changes kinetic energy stress profiles occur processes via addition.