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.
Supersonic panel flutter test results for flat fiber-glass sandwich panels with foamed cores
NASA -- Tech Note
1961
15 pages
Aufsatz (Zeitschrift)
Englisch
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