Engineering, 13.03.2020 00:01, 1630013

Find the expression for the moment about a point 3⁄4 chord behind the leading edge of a symmetrical airfoil. Verify this result by using the known fact that the center of pressure is at the 1⁄4 chord point for all angles of attack.

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Find the expression for the moment about a point 3⁄4 chord behind the leading edge of a symmetrical...