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If aircraft is in straight flight (cruise with lift of 100N) then, what will be the value of net rolling moment? Consider ideal conditions.

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If aircraft is in straight flight (cruise with lift of 100N) then, what will be the value of net rolling moment? Consider ideal conditions.

(a) 0 unit

(b) 12 Nm

(c) 23 unit

(d) 25 N/m

The question was asked in a national level competition.

I'd like to ask this question from Lateral-Directional Static Stability and Control topic in division Stability, Control, and Handling Qualities of Aircraft Design

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The correct choice is (a) 0 unit

For explanation: Given, aircraft is in cruise, lift = 100N.

At cruise condition, net rolling moment is zero. As at cruise all the forces and moments are in equilibrium or in balanced.

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