A Three-Dimensional Study of Fin-Induced Shock Wave Turbulent Boundary Layer Interaction.

Surface pressure distributions and oil streak patterns have been measured in the three-dimensional flowfield caused by the interaction of a skewed shock wave with a two-dimensional turbulent boundary layer. The boundary layer was developing on a 45 deg sweptback, sharp leading edged plate. Tests were made at a freestream Mach number of 2.95, a freestream unit Reynolds number of 63,000,000/m (1,600,000/in), a stagnation temperature of about 265 K and at near adiabatic wall temperature. Measurements have been made for generator angles in the range 0 to 12 deg in 2 deg increments. These measurements represent the first phase of a study which will include heat transfer measurements and details of the flowfield. The measured data are presented and compared with data obtained under the same shock wave conditions but with a different boundary layer. (Author)