Question

A supersonic 2D airfoil has Mach number of 1.5. Find Lift curve slope of the airfoil.

(a) 0.062 per degree

(b) 0.062 per rad

(c) 24 per degree

(d) 12.56 per degree

I have been asked this question in quiz.

I'm obligated to ask this question of Aerodynamics in portion Aerodynamics of Aircraft Design

Answer 1

Correct option is (a) 0.062 per degree

The best explanation: Given, mach number M = 1.5

2D lift curve slope = 4 / (M^2 – 1)^0.5

= 4 / (1.5^2 – 1)^0.5 = 3.57 per rad = 3.57/57.3 = 0.062 per degree.