(Solved): Consider the data for the NACA 2412 airfoil given in Figure 4.10. Calculate the lift and moment abo ...

Consider the data for the NACA 2412 airfoil given in Figure 4.10. Calculate the lift and moment about the quarter chord (per unit span) for this airfoil when the angle of attack is $4^{?}$ and the freestream is at standard sea level conditions with a velocity of $50\mathrm{ft}/\mathrm{s}$. The chord of the airfoil is $2\mathrm{ft}$. Figure 4.10 Experimental data for lift coefficient and moment coefficient about the quarter-chord point for an NACA 2412 airfoil. (Source: Data obtained from Abbott and von Doenhoff. Reference II.) Also shown is a comparison with theory described in Section 4.8. Note: Convert everything to SI units.