Expressions for the thrust losses of a scramjet engine are developed in terms of irreversible entropy increases and the degree of incomplete combustion. A method is developed which allows the calculation of the lost vehicle thrust due to different loss mechanisms within a given flow-field. This analysis demonstrates clearly the trade-off between mixing enhancement and resultant increased flow losses in scramjet combustors. An engine effectiveness parameter is defined in terms of thrust loss. Exergy and the thrust-potential method are related and compared.


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    Title :

    Thrust modeling for hypersonic engines


    Contributors:

    Conference:

    AIAA, International Aerospace Planes and Hypersonics Technologies Conference


    Publication date :

    1995-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




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