descibe the incident in the lift in about 50 word
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The lift and drag characteristics of NACA 0012, 1408, 2412, and 4412 airfoils are characterized using a 6” by 6” subsonic wind tunnel equipped with a force balance. The axial and normal forces on the airfoil are measured at angles of attack ranging from -8° to 28° and used to determine lift and drag forces. Lift, drag, and drag polar curves are generated using experimental data. Lift coefficients are found to increase linearly with increasing angle of attack up to the critical angle of attack. Drag coefficients are found to increase quadratically with increasing angle of attack. Both lift and drag coefficients are found to increase with increasing camber. Experimental results for finite wingspan airfoils are compared to published section data for infinite wingspan airfoils, revealing significant differences.