In this study, the interaction of shock waves with supersonic film cooling flows is investigated experimentally. A laminar jet is tangentially injected into a turbulent boundary layer at a freestream Mach number Ma1 = 2.45. Two injection species, i.e., air and helium, are considered. The total temperature of the cooling film either matches the freestream condition or is reduced to obtain total temperature ratios in the range 0.75 weiterlesen