Experimental investigation of the turbulent Schmidt number in supersonic film cooling with shock interaction

The interaction of an impinging shock and a supersonic helium cooling film is investigated experimentally by high-speed particle-image velocimetry. A laminar helium jet is tangentially injected into a turbulent air freestream at a freestream Mach number ${Ma}_{\infty }=2.45$. The helium cooling film is injected at a Mach number ${Ma}_i=1.30$ at a total temperature ratio $T_{0,i}/T_{0,\infty }=0.75$. A deflection $\beta =8^{\circ }$ generates a shock that impinges upon the cooling film. A shock interaction case and a reference case without shock interaction are considered. The distributions of the turbulent mass flux and the turbulent Schmidt number are determined qualitatively. The results are compared with large-eddy simulation (LES) data by Konopka et al. (Phys Fluids 25(10):106101, 2013. 10.1063/1.4823745) for a comparable flow configuration. The streamwise and wall-normal turbulent mass fluxes are in qualitative agreement with the LES solutions. The turbulent Schmidt number differs significantly from unity. Without shock interaction, the turbulent Schmidt number is in the range $0.5\le {Sc}_t\le 1.5$ which is in agreement with the literature. With shock interaction, the turbulent Schmidt number varies drastically in the vicinity of the shock interaction. Thus, the experimental results confirm the numerical data showing a massively varying turbulent Schmidt number in supersonic film cooling flows, i.e., the standard assumption of a constant turbulent Schmidt number is valid neither without nor with shock interaction.