A brief review of combustion and propulsion research currently underway at the Institute for Aerospace Studies is provided. Afterburning rocket exhaust plume properties are being investigated both experimentally and by mathematical analysis. The objective is to compile detailed data on turbulence qualities in simulated rocket exhaust jet flows under cold and combusting conditions. Computational fluid dynamic methods and an argon-ion two dimensional laser Doppler velocimetery are being used in a detailed investigation of the turbulent flowfield inside a small helicopter engine combustor. The data will be used to evaluate combustor modelling computer codes and mathematical modelling of processes inside a combustor. The effects of heat addition by shock induced combustion of a fuel-air gas mixture to supersonic flows are being studied as part of a project on aerodynamic and propulsive characteristics of shocked combustion ramjets. An upwind algorithm based on Roe's scheme has been developed to solve planar and axisymmetric parabolized Navier Stokes equations. This computational method was used to assess the viscous aerodynamic characteristics of a triple shock inlet at Mach 8. The design of an axisymmetric hypersonic nozzle, including equilibrium real gas effects and boundary layer effects, has been studied with application to such effects as varying stagnation conditions in the tunnel, including nonequilibrium real gas effects.


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    Title :

    Combustion and Propulsion


    Contributors:
    J. P. Sislian (author) / Y. Sheng (author) / L. Jiang (author) / R. A. Cusworth (author) / J. T. C. Hu (author)

    Publication date :

    1989


    Size :

    3 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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