Boundary layer transition at hypersonic conditions is critical to the design of future high-speed aircraft and spacecraft. Accurate methods to predict transition would directly impact the aerothermodynamic environments used to size a hypersonic vehicle's thermal protection system. A transition prediction tool, based on wind tunnel derived discrete roughness correlations, was developed and implemented for the Space Shuttle return-to-flight program. This tool was also used to design a boundary layer transition flight experiment in order to assess correlation uncertainties, particularly with regard to high Mach-number transition and tunnel-to-flight scaling. A review is provided of the results obtained from the flight experiment in order to evaluate the transition prediction tool implemented for the Shuttle program.


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    Title :

    Flight Experiment Verification of Shuttle Boundary Layer Transition Prediction Tool


    Contributors:
    S. A. Berry (author) / K. T. Berger (author) / T. J. Horvath (author) / W. A. Wood (author)

    Publication date :

    2016


    Size :

    16 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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