An aerodynamic computer code was developed for calculating the pressure distribution on a missile or its components, e.g., body and wings and subsequently interpolating the results by surface fit at locations as specified for structural analysis using the NASTRAN computer code. The code is valid for high supersonic speeds and generalized attitudes of the missile. (Author)


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    Title :

    Aerodynamic Computer Code for Computing Pressure Loads on a Missile at High Supersonic Speeds and Generalized Attitudes


    Contributors:
    K. K. Wang (author)

    Publication date :

    1979


    Size :

    232 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English