Rolling and yawing moments due to both rolling velocity and acceleration were found to be highly dependent on frequency at angles of attack higher than 16°; oscillatory derivatives were much different at these high angles from same measured by steady state rolling flow tests.
Experimental determination of effects of frequency and amplitude of oscillation on roll-stability derivatives for 60° delta-wing airplane model
NASA -- Tech Note
1960
49 pages
Report
Englisch
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Engineering Index Backfile | 1959
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