Question

If CLɑ wing = 1.2 per rad then, determine CMɑ. Given Xcg=0.29.

(a) 0.076 per rad

(b) 45 per rad

(c) 0.09 per rad

(d) 1.45 per rad

I had been asked this question in an interview for job.

I would like to ask this question from Longitudinal Static Stability and Control-1 in division Stability, Control, and Handling Qualities of Aircraft Design

Answer 1

Correct answer is (a) 0.076 per rad

Easy explanation: CMɑ = CLɑ*[Xcg-Xac] = 1.2*[0.29-0.25] = 0.076 per rad.