Review on active thermal protection and its heat transfer for airbreathing hypersonic vehicles

Hydrogen/air supersonic combustion for future hypersonic vehicles

Effect of geometric parameters on the drag of the cavity flameholder based on the variance analysis method

Investigation of combustion and flame stabilization modes in a hydrogen fueled scramjet combustor

Hypersonic flightisexpectedtobeachievedinthecomingyearsbyuseofsupersoniccombustionramjet.Oneofthe main issues is the thermal management of the overall vehicle and more specifically the cooling of the engine. To simulate the behavior of an actively cooled supersonic combustion ramjet byuse of supercritical endothermic fuel, a one-dimensional transient numerical model has been developed with heat and mass transfer, fluid mechanics and detailed pyrolysis chemistry. A supplementary step by step validation of the model is presented in this paper thanks to numerical and experimental comparison test cases. Fluid temperature profiles are in good agreement for steadystate calculations despite unconsidered 2-D effects due to momentum and thermal boundary layers. Heat fluxes conservation is verified. Thermal and hydraulic transient behavior are close to those of validation data. The present numericalmodelingisquantitativelyvalidatedundersteadystateandtransientconditions.Goodagreementisfound with experimental results on a chemical aspect. The model is suitable for conducting parametric studies on fuel pyrolysis in supercritical states and to use it for engineering applications as a predimensioning tool.

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Y. Tsujikawa

Papers

Effects of hydrogen active cooling on scramjet engine performance