If moment coefficient about aerodynamic centre of wing is -0.216 and lift coefficient of wing is 1.2. Find moment coefficient about cg. Given cg location as Xcg = 0.3.(a) -0.156(b) 0.123(c) 0.56(d) -1.56I got this question in unit test.My question comes from Longitudinal Static Stability and Control-1 in section Stability, Control, and Handling Qualities of Aircraft Design

If moment coefficient about aerodynamic centre of wing is -0.216 and l

1.	If moment coefficient about aerodynamic centre of wing is -0.216 and lift coefficient of wing is 1.2. Find moment coefficient about cg. Given cg location as Xcg = 0.3.(a) -0.156(b) 0.123(c) 0.56(d) -1.56I got this question in unit test.My question comes from Longitudinal Static Stability and Control-1 in section Stability, Control, and Handling Qualities of Aircraft Design
Answer» Correct choice is (a) -0.156 For explanation I would say: Moment COEFFICIENT about CG = Moment coefficient about AERODYNAMIC CENTRE of + (wing LIFT coefficient*[Xcg-Xac]) = -0.216 + (1.2[0.3-0.25]) = -0.156.

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