Explore topic-wise MCQs in Aerodynamics.

This section includes 9 Mcqs, each offering curated multiple-choice questions to sharpen your Aerodynamics knowledge and support exam preparation. Choose a topic below to get started.

1.

The total drag coefficient for a wing is given by______

A. c<sub>d</sub>= ( frac {D_f+D_P+D_i}{Sq_ } )
B. C<sub>d</sub>= ( frac {D_f+D_P}{Sq_ } )
C. C<sub>d</sub>= ( frac {D_f+D_P+D_i}{Sq_ } )
D. C<sub>d</sub>= ( frac {D_f+D_P}{Sq_ } )+D<sub>i</sub>
Answer» D. C<sub>d</sub>= ( frac {D_f+D_P}{Sq_ } )+D<sub>i</sub>
Discussion
2.

The correct formula for profile drag coefficient over the finite wing is_______

A. c<sub>d</sub>= ( frac {D_f+D_P}{Sq_ } )
B. c<sub>d</sub>= ( frac {D_P}{Sq_ } )
C. c<sub>d</sub>= ( frac {D_f}{Sq_ } )
D. c<sub>d</sub>= ( frac {D_f+D_P+D_i}{Sq_ } )
Answer» B. c<sub>d</sub>= ( frac {D_P}{Sq_ } )
Discussion
3.

Identify the source which does not cause drag on a finite wing.

A. Skin friction
B. Flow separation
C. Trailing vortices
D. Power provide by aircraft engine
Answer» E.
Discussion
4.

The trailing vortex increases the requirement of power by the aircraft engine.

A. False
B. True
Answer» C.
Discussion
5.

For an inviscid, incompressible flow over finite wings, D Alembert s paradox occurs.

A. True
B. False
Answer» C.
Discussion
6.

Select the incorrect statement for a flow over wings.

A. Induced drag comes from pressure- drag
B. Pressure imbalance makes D Alembert s paradox does not occur
C. 3D flow over wings cause induced drag
D. Induced drag is a type of pressure- drag
Answer» B. Pressure imbalance makes D Alembert s paradox does not occur
Discussion
7.

Which is the correct statement with regards to the flow over a finite wing?

A. Local lift is vertical
B. Downward velocity increases lift
C. Local lift is inclined to vertical by induced angle of attack
D. Free-stream velocity causes all the drag
Answer» D. Free-stream velocity causes all the drag
Discussion
8.

Induced drag is generated by a component of lift for a finite wing.

A. True
B. False
Answer» B. False
Discussion
9.

For a finite wing, the local airfoil section sees the angle of attack which is called as ____

A. Downwash angle
B. Induced angle of attack
C. Relative angle of attack
D. Effective angle of attack
Answer» E.
Discussion