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The ame stabilization and reaction processes in a scramjet combustion chamber have been experimentally investigated. Hydrogen was injected into a vitiated Mach 2.15 airstream by means of pylon-like fuel injectors. The supersonic ame was stabilized in a purely kinetical way; i.e., by means of fuel self-ignition. The ame-stabilization mechanisms have been studied. The interaction between the gasdynamics and the reaction kinetics are discussed. A small wedge has been mounted into the test combustor to modify the oblique shock structure. The response of the reacting ow on this change has been observed. To assess the reacting ow, only nonintrusive, optical measurement techniques have been employed: the schlieren technique to visualize the ow structure, the Rayleigh scattering technique to study the injected mixing jets, as well as the self-uorescence of the OH radical to determine location and intensity of the reaction zones. Additionally, the wall static pressure has been measured. NomenclatureA entrance = combustor entrance area A exit = combustor exit area M = Mach number Çm = mass ow rate p = static pressure p w = wall static pressure p 0 = total pressure Re = Reynolds number T = static temperature T entrance = static air temperature at combustor entrance T hydrogen = static temperature of hydrogen at fuel-injection ori ce T self-ignite = fuel self-ignition temperature T 0 = total temperature u = velocity w = mass fraction x = axial distance from pylon r = scattering cross section s self-ignite = self-ignition time scale U = equivalence ratio

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