Flight test of a supersonic experimental airplane was performed by Japan Aerospace Exploration Agency to improve advanced aerodynamic design technologies for the next generation SST. The experimental airplane was designed to reduce the drag on a supersonic cruise condition. Surface pressure distributions, boundary layer transition locations and aerodynamic forces in the flight test were obtained to validate the aerodynamic design concepts. The flight test results were evaluated by comparing with the prediction results obtained by CFD based optimum design tools. The flight test results were confirmed to be corresponding to the CFD results. Therefore, the aerodynamic design concepts for drag reduction were demonstrated qualitatively and quantitatively by the NEXST-1 flight test.


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    Title :

    Demonstration of Aerodynamic Design Technologies on Supersonic Experimental Airplane (NEXST-1) by Flight Test


    Contributors:
    D. Y. Kwak (author) / N. Tokugawa (author) / K. Yoshida (author) / A. Ishikawa (author) / M. Noguchi (author)

    Publication date :

    2007


    Size :

    50 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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    CFD Analysis on Flight Test Results of Supersonic Experimental Airplane NEXST-1

    Ishikawa, Hiroaki / Kwak, Dongyoun / Yoshida, Kenji | AIAA | 2007



    CFD Analysis on Flight Test Results of Supersonic Experimental Airplane NEXST-1

    Ishikawa, H. / Kwak, D. / Yoshida, K. et al. | British Library Conference Proceedings | 2007