Question

For a symmetrical airfoil drag coefficient at zero lift is 0.05 and induced drag coefficient is 0.0025. Find the total drag coefficient.

(a) 0.0525

(b) 0.45

(c) 5.25

(d) 52.5

This question was addressed to me in unit test.

I need to ask this question from Aerodynamic Coefficients in division Aerodynamics of Aircraft Design

Answer 1

The correct option is (a) 0.0525

The best explanation: Total drag coefficient = drag coefficient at zero lift + induced drag coefficient

= 0.05+0.0025 = 0.0525.