Flat, rectangular aircraft panels are parametrically simulated on operational analog computer as thin elastic plates simply supported over cavity containing still air and exposed to supersonic potential flow parallel to plane of panel; modified-thickness ratio, shown to be primary panel flutter parameter, is determined for length-width ratios between 0.2 and 5.0 and plotted vs length-width ratio to define basic reference panel flutter boundary which is presented along with few nonlinear effects.


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    Title :

    Simulation of supersonic aircraft panel aeroelastic instabilities


    Additional title:

    AIAA -- Tech Papers


    Contributors:
    Moore, M.T. (author) / Luce, R.G. (author)

    Conference:

    Meeting of the AIAA -- Simulation for Aerospace Flight Conference ; 1963 Flutter



    Publication date :

    1963


    Size :

    8 pages


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English


    Keywords :