Use of thin, all movable control surfaces on aircraft and missiles indicates that divergence rather than flutter may be primary aeroelastic problem; chordwise divergence is treated with emphasis on slender delta wings; experimental and analytical results for wings having apex half-angles of 5, 10, 15 and 20°, including calculations based on small-aspect ratio theory, lifting surface theory, and strip theory.
Some divergence characteristics of low aspects ratio wings at transonic and supersonic speeds
NASA -- Tech Note
1960
43 pages
Report
English
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