Three-dimensional hypersonic shock wave/turbulence boundary-layer interactions

Hypersonic experimental data for a series of three-dimensional shock wave/turbulent boundary-layer interaction is evaluated for possible applicationin the validation of turbulence models. The experiments were carried out in a hypersonic wind tunnel wherein a sharp plate having specific dimension is subjected to simulated turbulence under a speed of Mach 8.2. The evaluation reveals that that the experimental data are very useful in the analysis and documentation of three-dimensional flowfield.