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Kutta-Joukowski Theorem - Aerodynamics MCQ Questions

Kutta-Joukowski Theorem MCQs : Here you will find MCQ Questions related to "Kutta-Joukowski Theorem" in Aerodynamics. These Kutta-Joukowski Theorem MCQ Questions Will help you to improve your Aerodynamics knowledge and will prepare you for various Examinations like Competitive Exams, Placements, Interviews and other Entrance Exmaniations

Question 1

Kutta–Joukowski theorem relates lift to circulation much like the Magnus effect relates side force called?

A. Rotational force
B. Vortex force
C. Magnus force
D. Circular force

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Question 2

Which theorem applies to two-dimensional flow around a fixed airfoil?

A. Vortex
B. Lift force
C. Circulation
D. Heuristic

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Question 3

Which version of this theorem applies on each element of the plate and is the basis of thin-airfoil theory?

A. differential
B. integral
C. Both A and B
D. None of the above

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Question 4

When a (mass) source is fixed outside the body, a force correction due to this source can be expressed as the product of the strength of outside source and the induced velocity at this source by all the causes except this source. This is known as the?

A. Rotational theorem
B. Generalized Lagally theorem
C. Viscous theorem
D. Lagally theorem

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Question 5

The Kutta–Joukowski theorem is a fundamental theorem in aerodynamics

C. Can be true or false
D. Can not say

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Question 6

In the derivation of the Kutta–Joukowski theorem the airfoil is usually mapped onto a circular cylinder.

C. Can be true or false
D. Can not say

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Question 7

What is the angle of attack of lift producing airfoil?

A. Angle of attack less than zero
B. Angle of attack greater than zero
C. Angle of attack is zero
D. Angle of attack remains the same

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Question 8

How the fluid moves on the airfoil?

A. Lower surface
B. Upper and middle surface
C. Lower and upper surface
D. Upper surface

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Question 9

What is the flow outside the airfoil?

A. Rotational
B. Circumferential
C. Constant
D. Irrotational

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Question 10

Define circulation.

A. Line integral around an open loop enclosing the airfoil
B. Line integral around an in loop enclosing the airfoil
C. Line integral of airfoil
D. Line integral around a closed loop enclosing the airfoil

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