Engineering, 07.04.2020 00:52 ChloeN8912

For the NACA 2412 airfoil, the lift coefficient and moment coefficient about the quarter-chord at −6◦ angle of attack are −0.39 and −0.045, respectively. At 4◦ angle of attack, these coefficients are 0.65 and −0.037, respectively.
Calculate the location of the aerodynamic center.

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For the NACA 2412 airfoil, the lift coefficient and moment coefficient about the quarter-chord at −6...

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