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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 radI 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» CORRECT ANSWER is (a) 0.076 PER RAD

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


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