To provide data on stability and control characteristics of gliders, flight tests were made over angle of attack range from 10 to 35° with and without artificial pitch and roll damping added; force tests were made from -4 to 40° angle of attack to determine static stability and control characteristics and from 0 to 30° angle of attack to determine dynamic stability derivatives.
Investigation of low-subsonic flight characteristics of model of hypersonic boost-glide configuration having 78° delta wing
NASA -- Tech Note
1961
31 pages
Aufsatz (Zeitschrift)
Englisch
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