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
1987
9 pages
Report
No indication
English
Wing Divergence of Trimmed Aircraft
NTIS | 1986
|Aeroelastic divergence of trimmed aircraft
AIAA | 1986
|British Library Conference Proceedings | 2016
|