Accession Number:

AD0257853

Title:

SUPERSONIC PANEL FLUTTER TEST RESULTS FOR FLAT FIBER-GLASS SANDWICH PANELS WITH FOAMED CORES

Descriptive Note:

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C

Personal Author(s):

Report Date:

1961-06-01

Pagination or Media Count:

1.0

Abstract:

Flutter tests were made on flat panels having a 14-inch-thick plastic-foam core covered with thin fiber-glass laminates. The testing was done in the Langley Unitary Plan wind tunnel at Mach numbers from 1.76 to 2.87. The flutter boundary for these panels was found to be near the flutter boundary of thin metal panels when compared on the basis of an equivalent panel stiffness. The results also demonstrated that the depth of the cavity behind the panel has a pronounced influence on flutter. Changing the cavity depth from 1 12 inches to 12 inch reduced the dynamic pressure at start of flutter by 40 percent. No flutter was obtained when the spacers on the back of the panel were against the bottom of the cavity. Author

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE