Much research in the field of hypersonic propulsion is being carried out, and one mode of propulsion, viable especially for higher Mach numbers, is the shock-induced combustion ramjet (shcramjet). To resolve the shcramjet flowfield, a lower-upper symmetric successive overrelaxation (LUSSOR) scheme has been used to solve the Euler equations (axisymmetric or planar) for steady-state flow. The shock-induced finite-rate hydrogen-air combustion process was modeled by 33 reactions between 13 species (H_2, O_2, H, O, OH, H_2O, H_2O_2, N, NO, HNO, N_2, NO_2). The pressure distribution acting on these axisymmetric bodies was determined and used to obtain various aerodynamic and propulsive characteristics of external compression ramjets over the range of flight Mach numbers 10 <= M_infinity <=18. In conjunction with this research, a detailed numerical study of the non-equilibrium shock-induced combustion flowfield generated by a wedge-like body has been performed.
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