Explore topic-wise MCQs in Aerodynamics Questions and Answers.

This section includes 4 Mcqs, each offering curated multiple-choice questions to sharpen your Aerodynamics Questions and Answers knowledge and support exam preparation. Choose a topic below to get started.

1.

The value of integral ∫\(_0^?\frac {cos⁡n\theta d\theta }{cos⁡\theta-cos∅}\)=π\(\frac {sin⁡ n∅}{sin ⁡∅}\) is valid for the limit 0 to_____

A. π
B. 2π
C. –π
D. nπ
Answer» B. 2π
Discussion
2.

Find the induced velocity in the direction normal to the camber line a point on where the slope is 0.087. Given the angle of attack is 5° and free-stream velocity is 20 units. Use thin airfoil approximation.

A. 0
B. 101.74 units
C. 98.26 units
D. 3.48 units
Answer» B. 101.74 units
Discussion
3.

Given the component of free-stream velocity in the direction perpendicular to the camber line is 15 units and the velocity induced by the vortex sheet is 4 units at a point. The angle of attack for the thin airfoil is α. Then which of the following condition is true in case of thin airfoil theory?

A. 15sinα+4=0
B. 15+4=0
C. 15cosα+4=0
D. 15tanα-4=0
Answer» C. 15cosα+4=0
Discussion
4.

What is the Kutta Condition in terms of strength (γ) of the thin airfoil?

A. γ = 0
B. γ(LE) = 0
C. \(\frac {D\gamma }{Dt}\)=0
D. γ(TE) = 0
Answer» E.
Discussion