Flow establishment in a generic scramjet combustor

摘要: Abstract : The establishment of a quasi-steady flow in generic scramjet combustor is studied for the case time varying inflow to combustor. Such transient characteristic reflected-shock tunnel and expansion-tube test facilities. Several numerical simulations hypervelocity through straight-duct with either side-wall-step fuel injector or centrally-located strut are presented. Comparisons made between impulsively started but otherwise constant conditions (typical expansion tube tailored operation tunnel) relaxing produced by 'undertailored' reflected- shock-tunnel. Generally inviscid features, such as shock pattern pressure distribution, were unaffected inlet approached steady state approximately times indicated experimental correlations. However, viscous heat transfer skin friction, altered conditions. Keywords: Supersonic combustion ramjet engines; Shock tunnels; Mathematical models; Air flow; Jet engine inlets; Heat transfer; Fluid mechanics; Test evaluation; Steady Unsteady Hypersonic velocity/aerodynamics, Skin friction.