Preliminary Calibration of a Generic Scramjet Combustor

摘要: Abstract : The results of a preliminary investigation the combustion hydrogen fuel at hypersonic flow conditions are provided. tests were performed in generic, constant-area combustor model with test gas supplied by free-piston-driven reflected-shock tunnel. Static pressure measurements along wall indicated that burning did occur for inlet P(sub static) = approx. 19kPa, T(sub 1080K and velocity 3630 m/s equivalence ratio 0.9. These obtained operating tunnel stagnation enthalpy H sub s 8.1 M J/kg , P 52MPa contoured nozzle nominal exit Mach number 5.5.