The transition point for a flow can be found using____

Average of Reynolds numbers at leading and trailing edges

For a real flow over an airfoil, with Reynolds number in the laminar region as it starts, select the incorrect choice.

Flow is both turbulent and laminar at different places

Flow at trailing edge is laminar

Flow is both turbulent and laminar at different places

There is a transition region between leading and trailing edge

Flow at trailing edge is turbulent

A given flow can be laminar all over an airfoil in a real case. Select the correct statement for the assumption given above.

True only for symmetric airfoils

The boundary layer thickness for turbulent flow at a distance x with Reynolds number Rex is . Which is____

Directly proportional to ( sqrt[5]{x} )

Inversely proportional to ( sqrt[5]{Re_x} )

For the same angle of attack and chord length, the boundary layer is thicker in_____

Will be equal in both the flows

Depends on the velocity of flow

Explore topic-wise MCQs in Aerodynamics.

This section includes 12 Mcqs, each offering curated multiple-choice questions to sharpen your Aerodynamics knowledge and support exam preparation. Choose a topic below to get started.

1.	All bodies have skin-friction contribution more than that from the pressure drag.
A.	False
B.	True
Answer» B. True

Discussion

2.	Which of the following gives a better approximate distribution of drag over thin airfoils? The given percentages are for skin- friction drag and pressure drag respectively.
A.	85, 15
B.	50, 50
C.	64, 35
D.	Inadequate data
Answer» B. 50, 50

Discussion

3.	When the free-stream velocity is made one-third, the transition point moves downstream. The given statement is true or false?
A.	True
B.	False
Answer» B. False

Discussion

4.	The transition point for a flow can be found using____
A.	Average of Reynolds numbers at leading and trailing edges
B.	It is always the mid-chord
C.	Hit and trial methods
D.	Critical Reynolds number
Answer» E.

Discussion

5.	For a real flow over an airfoil, with Reynolds number in the laminar region as it starts, select the incorrect choice.
A.	Flow at trailing edge is laminar
B.	Flow is both turbulent and laminar at different places
C.	There is a transition region between leading and trailing edge
D.	Flow at trailing edge is turbulent
Answer» B. Flow is both turbulent and laminar at different places

Discussion

6.	The skin-friction coefficient for turbulent flow C_f is proportional to Re_c. The proportionality constant is_____
A.	0.074
B.	0.64
C.	0.33
D.	1.328
Answer» B. 0.64

Discussion

7.	A given flow can be laminar all over an airfoil in a real case. Select the correct statement for the assumption given above.
A.	Always true
B.	Always false
C.	True only for symmetric airfoils
D.	Depends on the Reynolds number
Answer» C. True only for symmetric airfoils

Discussion

8.	The boundary layer thickness for turbulent flow at a distance x with Reynolds number Re_x is . Which is____
A.	Directly proportional to ( sqrt[5]{x} )
B.	Inversely proportional to ( sqrt[5]{Re_x} )
C.	Directly proportional to Re<sub>x</sub>
D.	Inversely proportional to x
Answer» C. Directly proportional to Re<sub>x</sub>

Discussion

9.	For a Reynolds number Re_c=10 10⁵ and chord length 1m, what is the turbulent boundary layer thickness at the trailing edge (in cm)?
A.	0.0216
B.	0.037
C.	2.16
D.	0.37
Answer» D. 0.37

Discussion

10.	The skin-friction drag coefficient for turbulent flow on the bottom surface of an airfoil, with chord length being 1m is _____ (Reynolds number at the trailing edge Re_c=32 10⁵)
A.	0.074
B.	0.0037
C.	0.027
D.	0.0074
Answer» C. 0.027

Discussion

11.	An exact analytical solution exists for turbulent flows also like laminar flow over airfoils.
A.	False
B.	True
Answer» B. True

Discussion

12.	For the same angle of attack and chord length, the boundary layer is thicker in_____
A.	Turbulent flows
B.	Laminar flows
C.	Will be equal in both the flows
D.	Depends on the velocity of flow
Answer» B. Laminar flows

Discussion

Explore topic-wise MCQs in Aerodynamics.

All bodies have skin-friction contribution more than that from the pressure drag.

Which of the following gives a better approximate distribution of drag over thin airfoils?The given percentages are for skin- friction drag and pressure drag respectively.

When the free-stream velocity is made one-third, the transition point moves downstream.The given statement is true or false?

The transition point for a flow can be found using____

For a real flow over an airfoil, with Reynolds number in the laminar region as it starts, select the incorrect choice.

The skin-friction coefficient for turbulent flow Cf is proportional to Rec. The proportionality constant is_____

A given flow can be laminar all over an airfoil in a real case. Select the correct statement for the assumption given above.

The boundary layer thickness for turbulent flow at a distance x with Reynolds number Rex is . Which is____

For a Reynolds number Rec=10 105 and chord length 1m, what is the turbulent boundary layer thickness at the trailing edge (in cm)?

The skin-friction drag coefficient for turbulent flow on the bottom surface of an airfoil, with chord length being 1m is _____ (Reynolds number at the trailing edge Rec=32 105)

An exact analytical solution exists for turbulent flows also like laminar flow over airfoils.

For the same angle of attack and chord length, the boundary layer is thicker in_____

Which of the following gives a better approximate distribution of drag over thin airfoils?
The given percentages are for skin- friction drag and pressure drag respectively.

When the free-stream velocity is made one-third, the transition point moves downstream.
The given statement is true or false?

The skin-friction coefficient for turbulent flow C_f is proportional to Re_c. The proportionality constant is_____

The boundary layer thickness for turbulent flow at a distance x with Reynolds number Re_x is . Which is____

For a Reynolds number Re_c=10 10⁵ and chord length 1m, what is the turbulent boundary layer thickness at the trailing edge (in cm)?

The skin-friction drag coefficient for turbulent flow on the bottom surface of an airfoil, with chord length being 1m is _____ (Reynolds number at the trailing edge Re_c=32 10⁵)