Hypersonic Hydrogen Combustion in the Thin Viscous Shock Layer

Different models of hypersonic diffusive hydrogen combustion in a thin viscous shuck layer (TVSL) at moderate Reynolds numbers have been developed. The study is based on computations of nonequilibrium multicomponent flowfield parameters of air-hydrogen mixture in the TVSL near the blunt probe. The structure of computed combustion zones is analyzed. Under conditions of slot and uniform injections the zone structures a re essentially different. Hydrogen injection conditions a re discovered at which the nonreacting hydrogen zone and the zone enriched with the hydrogen combustion products appear near the body surface. Hydrogen, water, and OH concentrations identify these zones. More effective cooling of the probe surface occurs at moderate injections compared to strong ones. Under the blowing conditions at moderate Reynolds numbers the most effective cooling of the body surface occurs at moderate uniform hydrogen injection. The results can he helpful fur predicting the degree of supersonic hydrogen combustion in hypersonic vehicle engines.