A study of normal shock-wave turbulent boundary-layer interactions at Mach numbers of 1.3, 1,4 and 1.5

Seven flows involving the interaction between a normal shock wave and a two dimensional turbulent boundary layer were studied. The measurements were made at free-stream Mach numbers of 1.3, 1.4 and 1.5 and at Reynolds numbers based on an effective streamwise run of 1 to 30 million. The results were obtained from comprehensive traverses with pitot and static probes. Standard boundary layer integral parameters based on wall and measured static pressures are presented, together with velocity profiles and the Mach number distribution over the interaction region. The law of the wall and the law of the wake under the influence of strong normal pressure gradients were also investigated.