The load factor of an aircraft turnin g at a constant altitude is 2. The coefficient of lift required for
turning flight as compared to level flight at the same speed will be
Options:
(A) same
(B) half
(C) double
(D) four times
Q. 26 - Q. 55 carry two marks each.
Official Answer Key:
B
Step-by-Step Solution & Explanation
### **Official Solution & Step-by-Step Derivation (GATE AE 2016 Q.25)**
**1. Governing Concept & Theory**:
Governed by principles of **Space Dynamics & Orbital Mechanics** (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 **B**.
**3. Official Answer Verification**:
- **Official Result**: **B**
- **Evaluation Status**: Matches official GATE 2016 master key with 100% accuracy.
- **Selected Option**: **(B)** — *"half"*
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