A wing alone aircraft has aerodynamic centre pitching moment coefficient of -0.126. If lift coefficient at zero AOA is 0.38 then, find Cm0. Consider Xcg=0.3.(a) -0.107(b) -7.89(c) 1.457(d) 0.9845I got this question in unit test.My enquiry is from Longitudinal Static Stability and Control-1 in portion Stability, Control, and Handling Qualities of Aircraft Design

A wing alone aircraft has aerodynamic centre pitching moment coefficie

1.	A wing alone aircraft has aerodynamic centre pitching moment coefficient of -0.126. If lift coefficient at zero AOA is 0.38 then, find Cm0. Consider Xcg=0.3.(a) -0.107(b) -7.89(c) 1.457(d) 0.9845I got this question in unit test.My enquiry is from Longitudinal Static Stability and Control-1 in portion Stability, Control, and Handling Qualities of Aircraft Design
Answer» The correct ANSWER is (a) -0.107 The best EXPLANATION: Given, wing alone ARRANGEMENT, CMac = -0.126, CL0 = 0.38. Now, CM0 is given by, Cm0 = CMac + CL0[Xcg-Xac] = -0.126 + 0.38[0.3-0.25] = -1.07.

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