Static aeroelastic equations are formulated for an aircraft performing idealized pull-out and rolling maneuvers. It is concluded from the solutions of these equations that an unaugmented aircraft flying at speeds near the fixed-root divergence speed of its wing suffers low values of control angle per g and control effectiveness in roll and that the distribution of incidence across the wing varies considerably with speed.
Wing Divergence and Structural Distortion
1985
30 pages
Report
No indication
English
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