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Optimisation of the kinematics of flapping airfoils for micro air vehicle applications

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Academic year: 2021

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Figure 1.8: Wake structure for purely heaving airfoil producing thrust for h ∗ (t ∗ ) = 3c ∗ 4 sin
Figure 1.9: Wake vortex structure in the ring gait of birds corresponding to slow-speeds (left) and the continuous vortex gait used in cruise (right) conditions, both corresponding to minimal loss of energy in the wake (Rayner, 1988).
Figure 1.11: An insect-like micro air vehicle developed in Brigham Young University, Utah, U.S.A
Figure 1.12: The mesicopter: a micro air vehicle prototype based on the rotating wings principle developed at Stanford university, California, U.S.A
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