Experimental characterization and analysis of unsteady normal-shock boundary-layer interaction
摘要
This study experimentally investigates the interaction of a normal shock wave and the turbulent boundary layer at an upstream Mach number of 1.35 in the transonic wind tunnel S8Ch at ONERA Meudon. Wall-mounted unsteady pressure measurements and high-speed schlieren imaging were combined to measure the shock–boundary layer interaction (SBLI). A small separation region was observed along the centerline. Spectral analysis of the reconstructed wall pressure signals revealed distinct frequency ranges associated with different flow features: shock wave (