Consider a rectangular wing mounted in a low-speed subsonic wing tunnel. The wing model completely spans the test-section so that the flow "sees" essentially an infinite wing. If the wing has a NACA 23012 airfoil section and a chord of 0.3 m, calculate the lift, drag, and moment about the quarter-chord per unit span when the airflow pressure, temperature, and velocity are 1 atm, 303 K, and 42 m/s, respectively. The angle of attack is 8°.
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