The wing is at an angle of attack of 5° in an airflow velocity of 100 at standard sea-level conditions. Calculate the lift, drag, and moment about the quarter-chord per unit span.
1. By the method of dimensional analysis, derive the expression M = q~ Sec., for the aerodynamic moment on an airfoil, where the chord and c,. is the moment coefficient. 2. Consider an infinite wing with a NACA 1412 airfoil section and a chord length of 3 ft. The wing is at an angle of attack of 5° in an airflow velocity of 100 at standard sea-level conditions. Calculate the lift, drag, and moment about the quarter-chord per unit span.
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