NACA 23012 is considered in the study at = 4, while the CL = 0. and
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NACA 23012 is considered in the study at α = 4°, while the CL = 0.
and Cm,c/4 =−0.005. The zero-lift angle of attack is −1.1°. In addition, at α =−4°, Cm,c/4 =−0.0125. Based on the given information, calculate the aerodynamic center position of NACA 23012 airfoil.
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