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If CM0 is -0.052 and lift coefficient at zero angle CL0 is 0.92 then, find CMac. Consider rectangular wing.

If CM0 is -0.052 and lift coefficient at zero angle CL0 is 0.92 then, find CMac. Consider rectangular wing. Correct Answer -0.282

CMac = CM0 +CL0* For a typical rectangle wing, Xcg-Xac =0.25. Hence, CMac = CM0 + CL0*0.25 = -0.052+0.95*0.25 = -0.282.

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