A numerical scheme for calculating hypersonic flows involving shock-induced combustion is discussed. The analysis is limited to inviscid flow and includes chemical nonequilibrium and real-gas effects. Two types of flows are considered. First, the hypersonic, exothermic blunt-body flow problem is examined for mixtures of Hi/Oi and Hi/air, and the numerical results are compared with experimental results. Second, a hypervelocity mass launcher concept known as the "ram accelerator" is investigated in the velocity range of 5-7 km/s. Temperature contours and the distribution of various physical quantities along the ram accelerator projectile surface and tube wall are presented for a 14-deg nose projectile and for a gas mixture of 2Hi + Oi + 5He.

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