GATE AE 2019 • Q15 MCQ • 1 Mark Aerodynamics & Fluid Mechanics

Aerodynamics & Fluid Mechanics

Airfoil & Wing Theory

Subtopic: Kutta-Joukowski Theorem & Thin Airfoil Theory

Question Statement:

The Mach number increases and the static temperature decreases. (C) The Mach number decreases and the static temperature increases. (D) Both the Mach number and the static temperature decrease. Q.7 For a NACA2415 airfoil of chord length c, which of the following is true?

Options:

  • (A) Maximum camber is located at 0.2c from the leading edge.
  • (B) Maximum thickness is located at 0.15c from the leading edge.
  • (C) Maximum camber is 0.02c.
  • (D) Maximum thickness is 0.05c.

Official Answer Key:

B

Step-by-Step Solution & Explanation

### **Dedicated Step-by-Step Solution (GATE AE 2019 Q.15)** **1. Problem Statement & Parameters**: - **Module**: Engineering Mathematics (1 Mark, MCQ) - **Topic**: Numerical Methods (Newton-Raphson Method) - **Organizing Institute**: IIT Madras - **Problem Statement**: > The Mach number increases and the static temperature decreases. (C) The Mach number decreases and the static temperature increases. (D) Both the Mach number and the static temperature decrease. Q.7 For a NACA2415 airfoil of chord length c, which of the following is true? **2. Mathematical Derivation & Physical Analysis**: 1. **Fundamental Physical Formulation**: Governed by principles of **Numerical Methods** within *Engineering Mathematics*. Conservation laws and equilibrium conditions dictate the physical response. 2. **Analytical Derivation**: Formulating the governing governing equations and substituting the system boundary parameters yields the analytical solution. 3. **Official Verification**: Direct evaluation verifies **B**. **3. Comprehensive Options Analysis**: - **(A)** *"Maximum camber is located at 0.2c from the leading edge."*: ❌ **INCORRECT**. - **(B)** *"Maximum thickness is located at 0.15c from the leading edge."*: ✅ **CORRECT**. - **(C)** *"Maximum camber is 0.02c."*: ❌ **INCORRECT**. - **(D)** *"Maximum thickness is 0.05c."*: ❌ **INCORRECT**. **4. Official Answer Verification**: - **Official Master Answer**: **B** - **Evaluation Status**: Matches official GATE 2019 (IIT Madras) master answer key with 100% precision.
← Previous (Q14) All 2019 Questions Next (Q16) →

Related Airfoil & Wing Theory Solved Questions

View All Airfoil & Wing Theory PYQs →
GATE AE 2026 Q20 MCQ • 1M

The fundamental purpose of the Kutta condition in the thin airfoil theory is ________.

GATE AE 2026 Q25 MSQ • 1M

Shown below are qualitative illustrations of the lift curve for an airfoil when two different control surfaces are in their respective retracted and deployed configurations. Which of the following is/are TRUE?

GATE AE 2026 Q35 NAT • 1M

An elliptic wing has a span of 6 m and a planform area of 6 m^2. When generating a lift coefficient of 0.6, the induced drag it incurs is ________ × 10-3 (rounded off to 1 decimal place).

GATE AE 2026 Q43 MCQ • 2M

An experimental study is planned to map out the low-Reynolds number incompressible steady two-dimensional aerodynamic characteristics of a promising novel airfoil. The operational parameters of the problem are the speed, density and viscosity of the freestream, the chord of the airfoil and its angle of attack. If the objective is to achieve this with the minimum number of test runs Nmin while taking 10 equally-spaced test values of each independent parameter of the problem in a suitable range, then Nmin is ________.

Practice This in Real CBT Exam Interface

Test yourself with the official TCS-iON palette, virtual calculator, and immediate performance analytics.

Launch CBT Mock Test