| Computations are done on flow configurations that resemble the reaction zone in the scramjet combustor flows. First,hydrogen-air scramjet combustor is numerically simulated and analyzed by solving the general one-dimensional unsteady Euler equation. Second,compressible,reacting,turbulent flow solutions are obtained. An implicit LU-SGS (Lower-Symmetric Gauss-Seidel) finite-volume method is used for solving the full,compressible,two-dimensional Navier-Stokes and species transport equations. For turbulence closure a two equation(k-e) model is used. The combustion process in chemical nonequilibrium is modeled by a 7-species,8-reaction steps finite-rate chemistry and is implicitly coupled with the fluid motion. The flow fields of two-dimension for fuel-air equivalence ratio =0.35 are respectively calculated. Comparisons made with experimental data obtained at similar (but not identical) flow conditions were encouraging. |
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