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Experimental Investigation of the Effects of Compressive Stress on the Flutter of a Curved Panel and a Flat Panel at Supersonic Mach Numbers

Robert W. HessFrederick W. Gibson (NASA researcher.)

出版	National Aeronautics and Space Administration, 1962
URL	http://books.google.com.hk/books?id=48o_XBy0sGsC&hl=&source=gbs_api
EBook	FULL_PUBLIC_DOMAIN

註釋"An investigation was made of the effects of compressive stress on the flutter of a curved and a flat panel. The curved panel which was 0.0075-inch-thick stainless steel with a length-width ratio of 2.13 and a radius-to-thickness ratio of 1.133 was tested at a Mach number of 1.97. A flat aluminum panel, 0.032 inch thick with a length-width ratio of 2.13, was tested at Mach numbers of 1.63 to 1.84. The dynamic pressure at flutter decreased with increased axial compressive stress to a point where the panel was loaded to a stress near the calculated critical buckling stress. Beyond this point, the dynamic pressure at flutter increased with increasing compressive stress. The results of the flat-panel flutter tests indicate that caution should be exercised in using empirical panel fluter boundaries."--Summary.