EFFECTS OF COMBUSTION ON THE INTERACTION OF AN UNDEREXPANDED WALL HYDROGEN JET WITH A SUPERSONIC-FLOW IN A PLANAR CHANNEL

Calculations are presented on the combustion of an underexpanded hydro gen jet injected into a hot supersonic flow along the wall of a planar channel. The parabolized Navier-Stokes equations are solved by Marsh' s method and by global iteration with respect to the pressure. The mai n attention is given to how the combustion affects the interaction bet ween the wall turbulent jet and the shock waves it generates. The comb ustion produces a substantial increase in the non-uniformity of the st atic pressure pattern and causes subsonic zones within the supersonic flow, and sometimes causes detachment in the region where the stronges t shock wave interacts with the boundary layer. Calculations for vario us injection pressures show that there is a marked but not single-valu ed dependence of the ignition delay length on the jet underexpansion.