Engineering Questions with Answers - Multiple Choice Questions

# Aerodynamics – Blade Element Theory

1 - Question

What is the blade element theory used for?
a) Predict performance of airscrew airfoil
b) Predict performance of wind turbine
c) Predict performance of supersonic airfoil
d) Predict performance of flat plate
Explanation: The blade element theory is used to predict the performance of an airscrew blade which is a type of lifting airfoil used in helicopters. It can be replaced by a single hypothetical bound vortex which sheds vortex from the tip of the blade.

2 - Question

Which shape is traced by the trailing vortex at the tip of the airscrew blade?
a) Helix
b) Solenoid
c) Circle
d) Sine curve
Explanation: On examining the vortex system of the airscrew blade, we see that the trailing vortex which is formed at the tip of the blade traces out helix as the airscrew advances and rotates, the trailing vortex takes a helical form.

3 - Question

The bound and trailing vortex cancel out each other in the plane of the airscrew blade.
a) True
b) False
Explanation: There are three planes that can be considered- One immediately ahead of the plane, in plane of the blade and one immediately behind the blade. In case of the plane which is immediately ahead of the blade, the angular velocity is zero resulting in bound and trailing vortices canceling out each other.

4 - Question

How many times is the angular velocity of flow behind airscrew compared to that of angular velocity in plane of airscrew?
a) Same
b) Twice
c) Thrice
d) Four times
Explanation: If we consider the angular velocity of flow in plane of the airscrew blade as bΩ, and the angular velocity behind the blade as indicated by the bound vortices as +βΩ, then the angular velocity of the flow behind the airscrew is given by: ω=(b+β)Ω=2bΩ This value is twice that of the angular velocity in plane of the airscrew.

5 - Question

When is the blade element theory applicable?
a) When solidity is much greater than 1
b) When solidity is much lesser than 1
c) When solidity is equal to 1
d) When solidity is equal to 0
Explanation: In order to make sure that the blade element theory is applicable, there are certain conditions that have to be met. First being that the spacing to the chord ratio should be high. sc >> ! And solidity should be much lesser than 1. Solidity is defined by: σ=Bcπr Where, B is number of blades C is the chord length R is the radius

6 - Question

How does the blade element theory treat the airfoil as?
a) One-dimensional
b) Two-dimensional
c) Three-dimensional
d) One complete body
Explanation: The essence of blade element theory is to divide the blade into numerous segments known as blade elements. These are considered to be independent and not influencing the flow over other elements. Thus, it is treated as a two-dimensional airfoil whose aerodynamic forces are computed based on local flow conditions at that particular element instead of the entire airfoil.

7 - Question

Why is blade element theory preferred over momentum theory for designing a propeller?
a) Assumes flow inside stream tube as constant
b) Neglects span wise flow
c) Model thrust lag
d) Account for varying blade geometry
Explanation: There are several reasons why blade element theory is preferred over momentum theory. It can account for varying blade geometry, allows torque estimation, allows non-linearities for example lift curve to be modelled. The other points are some of the disadvantages.

8 - Question

What is the formula for the helix angle?
a) Φ=tan-1V0VE
b) Φ=sin-1V0VE
c) Φ=cos-1V0VE
d) Φ=tan-1VEV0
Explanation: According to blade element theory, When the propeller rotates and advances, the tip traces out helix. Along with this the trailing vortex also traces helix. This angle is measured between the direction of the flow and plane of rotation and is computed using the formula: Φ=tan-1V0VE Where, V0 is the forward airspeed of the aircraft VE is the effective resultant velocity.

9 - Question

What is the inflow ratio for hovering?
a) 1-1.5
b) 0.05-0.07
c) 0.6-1
d) 0.01-0.05
Explanation: Inflow ratio is a nondimensional quantity that is used to compare the results from different rotor blades. The formula for inflow ratio is given by: λ=V+vΩR Where, V is the climb velocity which is zero for hovering v is the induced velocity Ω is the rate of rotation of the blade R is the radius The value of inflow ratio ranges between 0.05 and 0.07 for hovering.

10 - Question

What is rotor polar?
a) Plot of power coefficient as a function of thrust coefficient
b) Plot of thrust coefficient as a function of power coefficient
c) Plot of power coefficient as a function of lift coefficient
d) Plot of power coefficient as a function of drag coefficient