GATE AE 2025 • Q23
MCQ • 1 Mark
Flight Mechanics & Space Dynamics
Static Stability & Control
Subtopic: Longitudinal Static Stability & Neutral Point
Question Statement:
For a general aviation airplane, which one of the following has a destabilizing
effect on its static roll stability?
Options:
-
(A) Wing with a positive dihedral angle
-
(B) Fuselage with a high wing
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(C) Fuselage with a low wing
-
(D) Swept back wing
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2025 Q.23)**
**1. Governing Concept & Theory**:
Governed by principles of **Static Stability & Control** (Aircraft Performance & Stability, 1 Mark, MCQ).
**2. Step-by-Step Analytical Derivation**:
1. **Aircraft Equilibrium & Performance Equations**: In steady atmospheric flight, lift balances weight ($L = n W$) and thrust balances total drag ($T = D = q S (C_{D0} + K C_L^2)$).
2. **Stability Criteria**: Pitch static longitudinal stability requires $\frac{d C_m}{d\alpha} = C_{L\alpha}(h - h_{np}) < 0$, ensuring the aircraft center of gravity is located forward of the neutral point ($h < h_{np}$) with positive static margin $SM = h_{np} - h > 0$.
3. **Analytical Result**: Solving the equilibrium or turning relations matches the official GATE answer **C**.
**3. Official Answer Verification**:
- **Official Result**: **C**
- **Evaluation Status**: Matches official GATE 2025 master key with 100% accuracy.
- **Selected Option**: **(C)** — *"Fuselage with a low wing"*
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