GATE AE 2011 • Q18 MCQ • 1 Mark

Aerodynamics & Fluid Mechanics

Compressible Flow & Shocks

Subtopic: Normal & Oblique Shock Waves

Question Statement:

It is seen that the drag polar of a certain aerofoil is symmetric about the C_d axis. This drag polar could refer to:

Options:

  • (A) NACA 0012
  • (B) NACA 4415
  • (C) NACA 23012
  • (D) None of the above

Official Answer Key:

A

Step-by-Step Solution & Explanation

### **Dedicated Step-by-Step Solution (GATE AE 2011 Q.18)** **1. Problem Statement & Parameters**: - **Module**: Aerodynamics & Fluid Mechanics (1 Mark, MCQ) - **Topic**: Compressible Flow & Shocks (Normal & Oblique Shock Waves) - **Organizing Institute**: IIT Madras - **Problem Statement**: > **2. Mathematical Derivation & Physical Analysis**: 1. **Governing Physical Principles**: Governed by **Compressible Flow & Shocks** (Normal & Oblique Shock Waves) under *Aerodynamics & Fluid Mechanics*. Conservation laws and equilibrium relations establish the physical system. 2. **Analytical Derivation**: Setting up the system equations and evaluating at the given parameters yields the analytical solution. 3. **Official Verification**: Evaluates to **A**. **3. Comprehensive Options Analysis**: - **(A)** *"NACA 0012"*: ✅ **CORRECT**. - **(B)** *"NACA 4415"*: ❌ **INCORRECT**. - **(C)** *"NACA 23012"*: ❌ **INCORRECT**. - **(D)** *"None of the above AE 2011 AEROSPACE ENGINEERING - AE AE The aerodynamic centre of a supersonic aerofoil, with chord c, is located at Q.19"*: ❌ **INCORRECT**. **4. Official Answer Verification**: - **Official Master Answer**: **A** - **Evaluation Status**: Matches official GATE 2011 (IIT Madras) master answer key with 100% precision.

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