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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    Titel :

    Computer-aided space shuttle orbiter wing design study


    Beteiligte:
    Phillips, W. P. (Autor:in) / Decker, J. P. (Autor:in) / Rau, T. R. (Autor:in) / Glatt, C. R. (Autor:in)

    Erscheinungsdatum :

    01.05.1974


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :



    Computer-Aided Space Shuttle Orbiter Wing Design Study

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    Aerodynamic Heating of a Space Shuttle delta-Wing Orbiter

    W. K. Lockman / C. E. Derose | NTIS | 1971