An experiment on active flutter suppression of a cantilever wing with the control surface at the wing tip is described. The experiment was done in a low subsonic wind tunnel. The deflection of the wing was measured by strain gages located near the root of the wing. The aileron was driven by a servomotor. Comparison was made between the present and previous results. It is concluded that the coefficients of the control law may have a different effect on the stability of the two- and three-dimensional models.
Experiment on Active Flutter Suppression of a Cantilever Wing
1981
10 pages
Report
No indication
English
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