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. (Author)


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    Title :

    Computer-Aided Space Shuttle Orbiter Wing Design Study


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

    Publication date :

    1974


    Size :

    84 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





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