For the NACA 2412 airfoil, the lift coefficient and moment coefficientabout 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. NACA 2412 airfoilEq. (4.57)1.61.2Lift coefficient0.80.4Cm, el4-0.4Ед. (4.64)-0.1Moment-0,8coefficient-0.2-1.2-0.3O Re = 3.1 X 10O Re - 8,9 X 106-0.48.1624a, degreesFigure 4.10 Experimental data for lift coefficient and momentcoefficient about the quarter-chord point for an NACA 2412 airfoil.(Source: Data obtained from Abbott, I. H., and A. E. von Doenhoff:Theory of Wing Sections, McGraw-Hill Book Company, New York,1949; also, Dover Publications, Inc., New York, 1959.) Also shown is acomparison with theory described in Section 4.8.go

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Answered: NACA 2412 airfoil Eq. (4.57) 1.6 1.2…

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