Engineering Questions with Answers - Multiple Choice Questions

# Aerodynamics – Viscous Flow – 2

1 - Question

The d’Alembert’s Paradox is concerned with ____
a) Lift arising due to pressure distribution
b) High viscous effects
c) Drag being zero for non-zero lift
d) Kutta condition not satisfied
Explanation: The d’Alembert’s paradox arises due to the assumption of an inviscid fluid. The lift predicted with this assumption is correct but the drag comes out zero. Which is not true as pointed out by experiments or general observation.

2 - Question

The lift can be calculated accurately using the pressure distribution assuming an inviscid flow.
a) False
b) True
Explanation: The assumption of inviscid flow does not affect the lift since the shear force component along the lift direction is negligible. Only the pressure distribution is responsible for creating lift.

3 - Question

What is responsible for creating the aerodynamic drag on the airfoil?
a) Pressure distribution
b) Friction
c) Thrust
d) Gravity
Explanation: Viscosity causes drag on the airfoil. For an airfoil, friction is responsible for causing viscosity and hence, causes drag.

4 - Question

Select the unmatched pair.
a) Pressure distribution: lift
b) Shear stress: skin-friction drag
c) Flow separation: form drag
d) Air pressure: pressure drag
Explanation: Lift is caused by the pressure distribution on the airfoil. The two ways drag is exerted is due to shear stress on the surface of the airfoil (skin – friction drag) and due to the flow separation (form drag, also called pressure drag).

5 - Question

The component of viscosity that creates skin-friction drag is_____

a) i
b) iii
c) ii
d) iv

Explanation: The component that creates skin- friction drag is shear stress acting on the surface of the airfoil. This is denoted by iii in the figure.

6 - Question

Which of the following is responsible for causing form drag?

a) i
b) iv
c) ii
d) iii

Explanation: Form drag is also known as pressure drag. The mechanism behind it is flow separation in a viscous flow which occurs near the trailing end. This is denoted by iv in the figure given.

7 - Question

The pressure drag in a fully attached flow over an airfoil is zero.
a) True
b) False
Explanation: For the attached flow, the pressure acting at the rear end of the airfoil counteracts the pressure acting on the front edge. But once flow separation occurs, the rear pressure reduces causing a net backward pressure – pressure drag.

8 - Question

A state with flow separation and reducing lift at a high angle of attack is___
a) Climbing
b) Take off
c) Landing
d) Stall
Explanation: Stall is characterized by a reduction in the lift at high angles of attack, i.e. when the angle of attack increases more than the critical angle of attack. The flow is no more attached and flow separation occurs.

9 - Question

Which of the following is not related to flow separation?
a) Reduction of lift
b) Increased drag
d) Attached flow