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
View Answer
Ans : C
Explanation: Kutta–Joukowski theorem relates lift to circulation much like the Magnus effect relates side force (called Magnus force) to rotation
Question 2
Which theorem applies to two-dimensional flow around a fixed airfoil?
A. Vortex
B. Lift force
C. Circulation
D. Heuristic
View Answer
Ans : B
Explanation: Life force : The theorem applies to two-dimensional flow around a fixed airfoil (or any shape of infinite span).
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
View Answer
Ans : A
Explanation: A differential version of this theorem applies on each element of the plate and is the basis of thin-airfoil theory.
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
View Answer
Ans : D
Explanation: 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 Lagally theorem.
Question 5
The Kutta–Joukowski theorem is a fundamental theorem in aerodynamics
A. TRUE
B. FALSE
C. Can be true or false
D. Can not say
View Answer
Ans : A
Explanation: The Kutta–Joukowski theorem is a fundamental theorem in aerodynamics used for the calculation of lift of an airfoil and any two-dimensional bodies including circular cylinders translating in a uniform fluid at a constant speed large enough so that the flow seen in the body-fixed frame is steady and unseparated.
Question 6
In the derivation of the Kutta–Joukowski theorem the airfoil is usually mapped onto a circular cylinder.
A. TRUE
B. FALSE
C. Can be true or false
D. Can not say
View Answer
Ans : A
Explanation: In the derivation of the Kutta–Joukowski theorem the airfoil is usually mapped onto a circular cylinder.
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
View Answer
Ans : B
Explanation: A lift producing airfoil either has camber or is translating in a uniform fluid at an angle of attack greater than zero. Moreover, it must have a sharp trailing edge. An airfoil generates lift by exerting a downward force on the air as it flows past.
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
View Answer
Ans : C
Explanation: Fluid moving along the lower and upper surface of the airfoil should meet at the sharp trailing edge. Since viscous dissipation prevents the fluid to turn around the sharp edge. This is known as the Kutta-Condition for real flow.
Question 9
What is the flow outside the airfoil?
A. Rotational
B. Circumferential
C. Constant
D. Irrotational
View Answer
Ans : D
Explanation: The flow outside the airfoil is irrotational and the circulation around any closed curve not enclosing airfoil is consequently zero. When the boundary layer separates, its displacement thickness increases sharply, which modifies the outside potential flow and pressure field.
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
View Answer
Ans : D
Explanation: Circulation is defined as the line integral around a closed loop enclosing the airfoil of the component of the velocity of the fluid tangent to the loop. To calculate the force on an airfoil, outside the boundary layer the vorticity is zero, everywhere the circulation is the same around every circuit.