Computation of shock-induced combustion using a detailed methane-air mechanism

摘要: The shock-induced combustion of methane-air mixtures in hypersonic flows is investigated using a new reaction mechanism consisting 19 reacting species and 52 elementary reactions. This reduced model derived from full kinetic via the detailed reduction technique. Zero-dimensional computations several shocktube experiments are presented first. computed values for ignition delay flame speed close agreement with experimental data results obtained mechanism. then combined fully implicit Navier-Stokes CFD code to simulate two-dimensional axisymmetric stoichiometric at Mach number M = 6.61. Good obtained. Furthermore, it shown that previous calculations were unable accurately predict this type flow due their use severely limited chemical mechanisms. Finally, applications ram accelerator concept also presented, based on novel double-ramp configuration.