Question

What will be the location of maximum camber for NACA 13250 with chord length of 2m?

(a) 0.32m from leading edge

(b) 0.32 from trailing edge

(c) 0.32m from trailing edge

(d) 0.32 from leading edge

This question was addressed to me in final exam.

Enquiry is from Airfoil Selection-3 in section Airfoil and Geometry Selection of Aircraft Design

Answer 1

Correct option is (a) 0.32m from leading edge

For explanation: Given, NACA 13250 airfoil

Based on NACA -5 digit series, location of maximum camber = (second and third digit)/2 in hundredth of chord from leading edge

= (32/2) * 0.01 * chord = (32/2)*0.01*2 = 0.32m from leading edge.