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An experimental study of the effect of fuel stagnation temperature on mixing in a supersonic hydrogen -air ame is described. The combustor consisted of a constant-area rectangular duct with a centrally located fuel-injection strut that spanned the width. A high-enthalpy stream of air was supplied by a free-piston shock tunnel, and heated hydrogen fuel, supplied by a gun-tunnel, was injected into the freestream as a co owing planar jet. The freestream total enthalpies were 5.6, 6.5, and 9 MJ/kg, and fuel stagnation temperatures were 300, 450, and 700 K. Raising the fuel stagnation temperature increased the fuel velocity to be near that of the airstream and resulted in a decrease in the mixing rate. Even as the fuel and air velocities became equal, signi cant mixing still occurred because of a large difference in density. Increasing the freestream enthalpy reduced the difference between the initial air temperature and the adiabatic ame temperature, which in turn reduced the heat addition, and subsequently, the amount of pressure rise in the duct.