Tests made in Langley Unitary Plan wind tunnel at 1.76 to 2.87 Mach; depth of cavity behind panel has pronounced effect on flutter; reducing depth from 1 1/2 to 1/2 in. reduced dynamic pressure at start of flutter by 40%; when spacers on back of panel were against bottom of cavity, flutter was eliminated.


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    Title :

    Supersonic panel flutter test results for flat fiber-glass sandwich panels with foamed cores


    Additional title:

    NASA -- Tech Note


    Contributors:


    Publication date :

    1961


    Size :

    15 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :