Effects of combustion and shock impingement on supersonic film cooling by hydrogen

Supersonic film cooling with H-2 coolant was numerically investigated by co nsidering the combustion of the coolant and the impingement of the shock wa ve. The influence of temperature fluctuation was included in calculating ch emical rate constants. The combustion region was formed apart from the wall , and there was little heat release from the flame. Therefore, the combusti on of H-2 had only a weak influence on the characteristics of the film cool ing. The location of ignition moved upstream considerably due to the temper ature fluctuations, However, the movement decreased the cooling efficiency very slightly. In addition, the effect of shock impingement on the film coo ling by reactive H-2 was almost the same as that of nonreactive N-2 with th e same coolant injection Mach number.