Empirical anaytic methods are presented for calculating thermal and pressure distributions in three-dimensional, shock-wave turbulent-boundary-layer, interaction-flow regions on the surface of controllable hypersonic aircraft and missiles. The methods, based on several experimental investigations, are useful and reliable for estimating both the extent and magnitude of the increased thermal and pressure loads on the vehicle surfaces.


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    Title :

    Methods for Estimating Pressure and Thermal Loads Induced by Elevon Deflections on Hypersonic-Vehicle Surfaces with Turbulent Boundary Layers


    Contributors:

    Publication date :

    1981


    Size :

    41 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English