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.

Linearized pressure distribution for higher deflection angle is inaccurate.

A. True
B. False
Answer» B. False
Discussion
2.

What is the coefficient of lift according to the linearized theory over a flat plate kept at an inclination of 3 degrees having a freestream Mach number of 2?

A. 0.01
B. 0.12
C. 0.85
D. 0.52
Answer» C. 0.85
Discussion
3.

How does the coefficient of pressure vary for supersonic flow as the Mach number decreases?

A. Increases
B. Decreases
C. Remains same
D. First increases, then decreases
Answer» B. Decreases
Discussion
4.

How does the coefficient of pressure vary for subsonic flow as the Mach number increases?

A. Increasesb) Decreases
B. Decreasesb) Remains samed) First increases, then decreases
C.
Answer» B. Decreasesb) Remains samed) First increases, then decreases
Discussion
5.

Coefficient of pressure over the forward section of the hump in supersonic flow is negative.

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

What is the coefficient of pressure over an airfoil at supersonic flow at Mach 2 which is inclined to the freestream at 1.4 degrees?

A. 1.1
B. 1.92
C. 1.62
D. 2.81
Answer» D. 2.81
Discussion
7.

Which of these is the relation for linearized pressure coefficient for two – dimensional bodies?

A. Cp = \(\frac {- 2u^{‘}}{V_∞}\)
B. Cp = \(\frac {- 2v^{‘}}{V_∞}\)
C. Cp = \(\frac {- 2w}{V_∞}\)
D. Cp = \(\frac {2u^{‘}}{V_∞}\)
Answer» B. Cp = \(\frac {- 2v^{‘}}{V_∞}\)
Discussion
8.

What is the relation between coefficient of pressure in terms of gamma and Mach number?

A. Cp = \(\frac {1}{γM_∞^2}\)) (1 – \(\frac {p}{p_∞}\))
B. Cp = \(\frac {2}{γM_∞^2}\)(\(\frac {p}{p_∞}\) – 1)
C. Cp = γM\(_∞^2\)(\(\frac {p}{p_∞}\))
D. Cp = \(\frac {γM_∞^2}{2} (\frac {p}{p_∞ – 1})\)
Answer» C. Cp = γM\(_∞^2\)(\(\frac {p}{p_∞}\))
Discussion