Explore topic-wise MCQs in Aerodynamics.

This section includes 10 Mcqs, each offering curated multiple-choice questions to sharpen your Aerodynamics knowledge and support exam preparation. Choose a topic below to get started.

1.

Which drag is prominent after exceeding the critical Mach number?

A. Form drag
B. Wave drag
C. Pressure drag
D. Skin – friction drag
Answer» D. Skin – friction drag
2.

What happens to the flow around the airfoil at upper critical Mach number?

A. The flow around airfoil becomes subsonic
B. The flow around airfoil becomes supersonic
C. The flow around airfoil becomes sonic
D. The flow around airfoil becomes hypersonic
Answer» C. The flow around airfoil becomes sonic
3.

Which equation is used to compute the critical Mach number of the airfoil?

A. (Cp)crit = \(\frac {2}{γM_{crit}^{2}} \bigg [ \frac {1 + \frac {1}{2}(γ – 1)M_{crit}^{2}}{1 + \frac {1}{2}(γ – 1)} \bigg ]^{\frac {γ}{γ – 1}}\) – 1
B. (Cp)crit = \(\frac {2}{γM_{crit}^{2}} \bigg [ \frac {1 + \frac {1}{2}(γ – 1)M_{crit}^{2}}{1 + \frac {1}{2}(γ – 1)} \bigg ]^{\frac {γ}{γ + 1}}\) + 1
C. (Cp)crit = γM\(_{crit}^{2} \bigg [ \frac {1 + \frac {1}{2}(γ – 1)}{1 + \frac {1}{2}(γ – 1)} \bigg ]^{\frac {γ}{γ – 1}}\) – 1
D. (Cp)crit = γM\(_{crit}^{2} \bigg [ \frac {1 + \frac {1}{2}(γ – 1)}{1 + \frac {1}{2}(γ – 1)M_{crit}^{2}} \bigg ]^{\frac {γ}{γ – 1}}\) – 1
Answer» B. (Cp)crit = \(\frac {2}{γM_{crit}^{2}} \bigg [ \frac {1 + \frac {1}{2}(γ – 1)M_{crit}^{2}}{1 + \frac {1}{2}(γ – 1)} \bigg ]^{\frac {γ}{γ + 1}}\) + 1
4.

Which of these techniques is employed to delay the critical Mach number?

A. Increasing the thickness of airfoil
B. Swept wing
C. Increase camber
D. Decrease drag – divergence Mach number
Answer» C. Increase camber
5.

What is the relation between the drag divergence Mach number and critical Mach number?

A. Mdrag – divergence = Mcrit
B. Mdrag – divergence > Mcrit
C. Mdrag – divergence < Mcrit
D. Mdrag – divergence × Mcrit = 0
Answer» C. Mdrag – divergence < Mcrit
6.

Thicker the airfoil, higher is the critical Mach number.

A. True
B. False
Answer» C.
7.

What is the coefficient of pressure at minimum pressure point a function of?

A. Critical Mach number
B. Freestream Mach number
C. Chord/thickness ratio of airfoil
D. Length of the airfoil
Answer» B. Freestream Mach number
8.

What is the coefficient of pressure at the minimum pressure point for an airfoil with critical Mach number as 0.6?

A. 1.53
B. 1.66
C. 1.42
D. 1.15
Answer» C. 1.42
9.

The local Mach number at a point on the airfoil reaches 1 for critical Mach number.

A. True
B. False
Answer» B. False
10.

What is a critical Mach number?

A. Freestream Mach number for which stagnation pressure is obtained
B. Freestream Mach number for which sonic flow is obtained
C. Free stream Mach number for which supersonic flow is obtained
D. Freestream Mach number for which hypersonic flow is obtained
Answer» C. Free stream Mach number for which supersonic flow is obtained