For the NACA 2412 airfoil, the data in Fig. 2.6a show that, at α = 6°, c1 = 0.85 and . In...

For the NACA 2412 airfoil, the data in Fig. 2.6a show that, at α = 6°, c₁ = 0.85 and . In Example 2.4, the location of the aerodynamic center is calculated , where x_a.c. is measured relative to the quarter-chord point. From this information, calculate the value of the moment coefficient about the aerodynamic center, and check your resuit with the measured data in Fig. 2.6b.