NUMERICAL STUDY OF HYPERVELOCITY FLOWS THROUGH A SCRAMJET COMBUSTOR

Results are reported from a numerical investigation of mixing and comb ustion of hydrogen injected into an airstream at high enthalpy (flight Mach number 17). Numerical computations performed using the general a erodynamic simulation program code are compared with experimental data obtained with a rectangular combustor model in the free-piston driven , reflected-shock tunnel facility T5, at the Graduate Aeronautical Lab oratories at the California Institute of Technology, Computed results show good agreement with the measured static wall pressures, Mixing pe rformance with the injection of hot hydrogen is shown to be in line wi th established correlations for scramjet design. Also, the issue of sp atial uniformity of the hydrogen-air mixture has been explored.