Aerodynamic forces and moments associated with flapping oscilla-tions of finite wings at low speeds are considered. A comparison of theoretical and experimental results is made for a rectangular wing of aspect ratio 2. Calculated results are also given for three tapered wings of aspect ratio 3 with varying amounts of sweepback. The calcu¬lations are based on a numerical solution of the integral equation of subsonic lifting-surface theory. The experimental techniques employed are essentially those used in previous measurements associated with pitching oscillations. Theory and experiment are generally in good agreement with regard to magnitude of the forces and moments, but dif¬fer with regard to phase angle.
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