The maximum lift co-efficient for NACA 19584 (chord=2.5m) airfoil is____(a) 0.15(b) 0.315(c) 0.15N(d) 0.3NThis question was addressed to me by my college professor while I was bunking the class.My question is based upon Airfoil Selection-3 in portion Airfoil and Geometry Selection of Aircraft Design

The maximum lift co-efficient for NACA 19584 (chord=2.5m) airfoil is__

1.	The maximum lift co-efficient for NACA 19584 (chord=2.5m) airfoil is____(a) 0.15(b) 0.315(c) 0.15N(d) 0.3NThis question was addressed to me by my college professor while I was bunking the class.My question is based upon Airfoil Selection-3 in portion Airfoil and Geometry Selection of Aircraft Design
Answer» RIGHT option is (a) 0.15 Easiest explanation: Given, NACA 13250 airfoil Based on NACA -5 DIGIT SERIES, DESIGNED lift co-efficient = first digit0.15 = 10.15 = 0.15.

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