![]() It is found that the analyzed silane chemical kinetic models are extremely sensitive to temperature and pressure at key combustor conditions. Furthermore, the ignition properties of silane/hydrogen mixtures are evaluated at conditions extracted from representative streamlines calculated in a computational-fluid-dynamics simulation of a model scramjet configuration tested at the Alliant Techsystems/General Applied Science Laboratory at Mach 10. Numerical predictions of silane/hydrogen ignition characteristics are compared to experimental measurements of explosion limits and shock-tube ignition delay times. ![]() An assessment of the ignition characteristics of several silane/hydrogen combustion models under conditions that are relevant to hypersonic combustion applications is presented.
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