: Consider a wing with a rectangular planform mounted in a low-speed subsonic wind tunnel. The wing model completely spans the test section so that it may be considered an infinite wing. If the wing has a NACA 4412 airfoil section (see textbook Appendix) and a chord of 0.4, calculate the lift, drag, and moment about the quarter-chord per unit span when the freestream air pressure is 98 kPa, the freestream temperature is 280 K, the freestream velocity is 38 m/s, and the viscosity is 1.7894 ∙ 10−5 kg/(m ∙ s) at the following angles of attack: a) 5° b) 16° c) -2