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Consider an infinite wing with a NACA 1412 airfoil section and a chord length of 1.5...

Consider an infinite wing with a NACA 1412 airfoil section and a chord length of 1.5 ft. The wing is at an angle of attack of 5° in an airflow velocity of 170 ft/s at standard sea-level conditions. Calculate the lift, drag, and moment about the quarter-chord per unit span. Refer to the Appendix graphs given below for the standard values. (Round the final answers to two decimal places.)

1)The lift per unit span is _______lb.

2)The drag per unit span is _______lb.

3)The moment about the quarter-chord per unit span is _______lb.

Engineering   Mechanical-Engineering   
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