An analytical and experimental investigation has been made to provide a space shuttle orbiter wing design that met the guideline requirements of landing performance, stability, and hypersonic trim for a specified center-of-gravity envelope. The analytical study was facilitated by the use of the Optimal Design Integration system (ODIN) and the experimental part of the investigation was conducted in the Langley low-turbulence pressure tunnel and the Langley continuous-flow hypersonic tunnel.


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    Title :

    Computer-aided space shuttle orbiter wing design study


    Contributors:
    Phillips, W. P. (author) / Decker, J. P. (author) / Rau, T. R. (author) / Glatt, C. R. (author)

    Publication date :

    1974-05-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English


    Keywords :



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