For the NACA 2412 airfoil, the lift coefficient and moment coefficient about the quarter-chord at 6 angle
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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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Labindao Antoque
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