Explore topic-wise MCQs in Aerodynamics.

This section includes 8 Mcqs, each offering curated multiple-choice questions to sharpen your Aerodynamics knowledge and support exam preparation. Choose a topic below to get started.

1.

Up to which Mach number is Prandtl – Glauert rule applicable for subsonic flow?

A. 1
B. 0.5
C. 0.8
D. 0.65
Answer» D. 0.65
Discussion
2.

For a subsonic flow, how does the coefficient of pressure vary with increasing Mach number?

A. Increases
B. Decreases
C. Remains same
D. First increases, then decreases
Answer» B. Decreases
Discussion
3.

Linearized theory is applicable for transonic regions as well.

A. True
B. False
Answer» C.
Discussion
4.

What does the Prandtl – Glauert rule relate?

A. Shape of airfoil in transformed spaces
B. Incompressible flow to the compressible flow for same airfoil
C. Coefficient of lift to coefficient of pressure
D. Coefficient of drag to coefficient of pressure
Answer» C. Coefficient of lift to coefficient of pressure
Discussion
5.

The shape of the airfoil in both (x, y) and transformed (ξ, η) space are different.

A. True
B. False
Answer» C.
Discussion
6.

Which of the equations governs the linearized incompressible flow over an airfoil at subsonic velocity using transformed coordinate system?

A. Laplace’s equation
B. Euler’s equation
C. Navier – Stokes equation
D. Cauchy’s equation
Answer» B. Euler’s equation
Discussion
7.

Which of these is the linearized perturbation velocity potential equation over a thin airfoil in a subsonic compressible flow?

A. β2(ϕxx + ϕyy) = 0
B. ϕxx + ϕyy = 0
C. β2ϕxx + ϕyy = 0
D. β2ϕxx + ϕxy = 0
Answer» D. β2ϕxx + ϕxy = 0
Discussion
8.

What is the surface boundary condition for a thin airfoil at a subsonic flow? (Where shape of the airfoil is represented as y = f(x))

A. \(\frac {∂ϕ}{∂x}\) = V∞ \(\frac {df}{dx}\)
B. \(\frac {∂ϕ}{∂y} = \frac {df}{dy}\)
C. \(\frac {∂ϕ}{∂x}\) = – V\(_∞^2 \frac {df}{dx}\)
D. \(\frac {∂ϕ}{∂x} = \frac {dV_∞}{dx}\)
Answer» B. \(\frac {∂ϕ}{∂y} = \frac {df}{dy}\)
Discussion