Aerospace Engineering > GATE 2025 > Aircraft Stability
A general aviation airplane is initially in steady and level flight. The stability coefficient &partial;Cm/&partial;q (Cm is the airplane pitching moment coefficient and q is the pitch rate) is negative. The airplane is perturbed with a small nose-up constant pitch rate. Assume that the horizontal tail does not stall during the perturbation, and unsteady effects are neglected. When compared to steady and level flight condition, which of the following statements is/are true during the perturbed motion?
A
The angle of attack of the horizontal tail increases.
B
The contribution of the horizontal tail to the airplane's pitching moment about the center of gravity is more stabilizing.
C
The lift generated by the horizontal tail increases.
D
The contribution of the horizontal tail to the airplane's pitching moment about center of gravity is less stabilizing.

Correct : b

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aerospace engineering gate 2025 aircraft stability pitching moment coefficient horizontal tail GATE aerospace engineering angle of attack horizontal tail lift horizontal tail pitching moment stability GATE 2025 question 38

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