We have investigated the dynamic force acting on the controlled morphing wing due to unsteady maneuvering. The controlled morphing takes place in the spanwise direction, which includes spanwise bending and twisting. The main objective of our study is to use controlled wing morphing techniques to improve the lift characteristic and to investigate the effect of controlled morphing on the added mass peak. To that end, we have designed a flexible flat plate wing that can be morphed in a controlled way in spanwise direction with the flexion ratio of 0.67, aspect ratio (AR) 3, and chord length (c) 0.16 m. In the present work, we have worked with two kinematics at Reynolds Number (Re) 18,000 and angle of attack 30°. When the spanwise bending happens on the low-pressure side we see a reduced added mass peak followed by another peak. For spanwise bending on the high-pressure side, we see a higher added mass peak.
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