Abstract
The interaction of shock waves with supersonic film-cooling flows is investigated experimentally by high-speed particle-image velocimetry. A laminar jet is tangentially injected into a turbulent boundary layer at a freestream Mach number . The injection Mach numbers are and . The total temperature and static pressure of the injection match the freestream condition. A deflection of and generates a shock that impinges upon the film-cooling flow at two positions downstream of the injection slot. The flow structure of the shock/cooling-film interaction is highly sensitive to the injection Mach number. An increased injection Mach number (i.e., higher near-wall momentum) stabilizes the flow and drastically decreases the separation-bubble size. Because of the additional free shear layer and the near-wall jet, the large-scale low-frequency motion of the separation shock is reduced by one order of magnitude compared to the oscillation in standard shock/boundary-layer interaction.
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