ocr: LIFT SLUPE LURYE NACA 4412 NACA 65012 L1 1.501 L 1.501 1 1 I 1.35 esenD f 1.351 65015) t1 1.20 - 1.201 - - 1.051 C1 1.051 65018 - C 0.90 0 - 0.901 e e t 0.75 f 0.751 65009 0.601 t 0.601 1 0.451 C - 0.451 1 0.30 1 0.301 e e no 0.15 n - 0.151 T - 0.00 - - - T 0.00L - - - - -4-202 46810121416 U 2 4 6 8 - 10 12 14 Angle of Attack (deg) Angle of Attack (deg) AC Total Wing AC Lift == Max lift coefficient Lift slope up to 6 degrees may be used for the other indicated airfoils. Weight(oz) Arealsq in) Speed(MPH) Coefficient Enter Data Read
