By means of a simple theoretical model it is shown that wing divergence of a free aircraft can be defined using the static case of trimmed level flight. The same model also shows that the control angle per 'g' goes to zero at a speed near the fixed-root divergence speed and that there is a large change in the spanwise distribution of airload in going from a low speed to speeds above that of fixed-root divergence.
Wing Divergence of Trimmed Aircraft
1986
9 pages
Report
No indication
English
Wing Divergence of Trimmed Aircraft
NTIS | 1987
|Aeroelastic divergence of trimmed aircraft
AIAA | 1986
|British Library Conference Proceedings | 2016
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