A preliminary numerical study of transpiration cooling applied to a hypersonic configuration is presented. Air transpiration is applied to the NASA all-body configuration flying at an altitude of 30500 m with a Mach number of 10.3. It was found that the amount of heat disposal by convection is determined primarily by the local geometry of the aircraft for moderate rates of transpiration. This property implies that different areas of the aircraft where transpiration occurs interact weakly with each other. A methodology for quick assessments of the transpiration requirements for a given flight configuration is presented.


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    Title :

    Transpiration Cooling in Hypersonic Flight


    Contributors:
    D. Tavella (author) / L. Roberts (author)

    Publication date :

    1989


    Size :

    31 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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