NASA has contracted with the Central Institute of Aviation Motors CIAM to perform a flight test and ground test and provide a scramjet engine for ground test in the United States. The objective of this contract is to obtain ground to flight correlation for a supersonic combustion ramjet (scramjet) engine operating point at a Mach number of 6.5. This paper presents results from a flow path performance and thermal evaluation performed on the design proposed by the CIAM. This study shows that the engine will perform in the scramjet mode for stoichiometric operation at a flight Mach number of 6.5. Thermal assessment of the structure indicates that the combustor cooling liner will provide adequate cooling for a Mach number of 6.5 test condition and that optional material proposed by CIAM for the cowl leading-edge design are required to allow operation with or without a type IV shock-shock interaction.


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    Title :

    Comparative Flow Path Analysis and Design Assessment of an Axisymetric Hydrogen Fueled Scramjet Flight Test Engine at a Mach Number of 6.5


    Contributors:
    C. McClinton (author) / A. Roundakov (author) / V. Semenov (author) / V. Kopehenov (author)

    Publication date :

    2004


    Size :

    20 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English