24th Joint Propulsion Conference · 1988 · 37 citations · 1 references
EngineeringAerospace EngineeringMechanical EngineeringCombustionFluid DynamicsHeat TransferCombustion DiagnosticsCombustion FundamentalsCombustion In EnginesCombustion KineticsCombustion ProcessesSupersonic AerodynamicsCombustor AerodynamicsCombustor DynamicsCombustorsFlow Field VisualizationLaser DiagnosticsLaser-based DiagnosticsStagnation Point AnalysisSupersonic Combustion
Accurate, spatially-resolved measurements can be conducted of a model supersonic combustor in a clean air/continuous flow supersonic combustion facility whose long run times will allow not only the point-by-point mapping of flow field variables with laser diagnostics but facilitate the simulation of steady-state combustor conditions. The facility will provide a Mach 2 freestream with static pressures in the 1 to 1/6 atm range, and stagnation temperatures of up to 2000 K.
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