Numerical Simulation of Transpiration Cooling in a Laminar Hypersonic Boundary Layer

Two-dimensional simulations of transpiration cooling in a laminar, hypersonic boundary layer were performed using the thermochemical implicit nonequilibrium algorithm (TINA): Navier–Stokes solver. Coolant concentration and heat flux results are compared to data obtained from laminar experiments conducted Oxford High Density Tunnel employing flat-plate geometry at Mach 7. TINA successfully predicts mixing rate wall as function streamwise direction for all blowing ratios. The more successful predicting downstream injector on injector: especially low A collapse thermal effectiveness values calculated simulation is achieved, which agrees with correlations within an absolute value . It shown that, when close one injector, temperature gradient becomes negative locations immediately resulting flux. acceleration coolant promotes dissipation energy, reduction coolant, thereby induces injector.