Engineering Questions with Answers - Multiple Choice Questions
MCQs on Helicopter Rotor and Notations
1 - Question
What would an efficient vertical flight mean?
a) Low power loading
b) High lift
c) Less drag
d) Less pressure difference
Explanation: In a helicopter, rotor provides thrust force in the vertical direction in order to counter its weight. For an efficient vertical flight, the power loading has to be low which means that the ratio of rotor power required to the rotor thrust should be less. This is achieved by low disk loading i.e. The ratio of rotor thrust to the rotor disk area is minimum.
2 - Question
Why does helicopter have huge rotors?
a) Induced power is inversely proportional to rotor radius
b) Induced power is directly proportional to rotor radius
c) Wing loading is inversely proportional to rotor radius
d) Wing loading is directly proportional to rotor radius
Explanation: Induced power loading is proportional to square root of the rotor disk loading and inversely proportional to the rotor radius for a rotary wing in hover. Therefore, it has a large disk region of large diameter rotors for a given gross helicopter weight.
3 - Question
Which of these has the lowest disk loading?
Explanation: The use of high disk loading rotors for lifting compromises vertical flight capability, both in terms of power and reduced hover endurance. Of all the VTOL aircraft, helicopter has the lowest disk loading and thus has the most powerful vertical flight capability.
4 - Question
What kind of motion is produced by the hinged blade which is lying in the plane of rotor disk?
a) Flap motion
b) Lag motion
c) Yaw motion
d) Roll motion
Explanation: The hinged blade allows rigid body rotation about the hinge point which is acted upon by restoring moment due to centrifugal force acting on the rotating blade. For the hinge that lies in the plane of the rotor disk, there’s an out-of-plane deflection of the blades produced. This is known as flap motion. When the deflection of blade along vertical hinge arises, it is known as lag motion.
5 - Question
How are the aerodynamic forces of the rotor controlled?
a) Feathering motion
b) Lag motion
c) Flap motion
d) Yaw motion
Explanation: The aerodynamic forces of the rotor is controlled using the pitch motion which helps in altering the angle of attack of the rotor blade. The change of blade pitch angle is known as feathering motion. This is achieved using hinge or bearing but for rotors without hinge, it is accomplished by the pitch moment about the torsional rigidity region at the rotor blade root.
6 - Question
What is the rotor whose blades are attached to the hub with hinges called?
a) Teetering rotor
b) Articulated rotor
c) Hinge rotor
d) Flap and lag rotor
Explanation: There are various arrangements of rotor based on how the blades are arranged to the hub for flap and lag motion. In case of articulated rotor, the rotor blades are attached to the hub with flap and lag hinges. This allows the blade to move independently with each blade that can either flap, lag, feather or lead.
7 - Question
What values of aspect ratio is generally used for helicopter rotor blades?
Explanation: The ratio of its span to its mean chord is the aspect ratio of a wing. It is equal to the square of the wingspan divided by the area of the wing. Higher is the aspect ratio, more narrow is the wing and vice versa. A higher aspect ratio wing is generally preferred for helicopters as it reduces the tip vortices thus reducing drag.
8 - Question
Teetering rotors have blade attached to hub without hinges which is attached to the shaft by the gimbal.
Explanation: Teetering rotor is one of the rotor classifications where the blades form one continuous structure in the teetering or seesaw configuration that is connected to the shaft with a single flap hinge. It doesn’t have any hinge lag. If the blades without any hinges is attached to the hub which is further attached to the shaft using gimbal, it is known as gimbal rotor.
9 - Question
Why are twin rotor configuration used?
a) To generate more lift
b) To counter torques
c) To generate pitching motion
d) To generate yaw motion
Explanation: A twin rotor configuration is used in a helicopter to counter the torque generated by the main rotor. The rotors are counterrotating with equal size and loading. This leads to no net yaw motion which can be detrimental.
10 - Question
What are the components of rotor?
Explanation: The helicopter is an essential component that provides the vertical lift. The main rotor generates the lift whereas the tail rotor counteracts the torque thus eliminating yaw-motion. The rotor system consists of the hub on which all the blades are attached, it also has the mast. Together these three components make up the entire rotor system. The rotor system in turn is attached to the shaft through which the power is delivered.
11 - Question
What is the azimuth angle of the rotor blade for a constant rotational speed?
Explanation: The azimuth angle for a rotor blade is given by the angle between the downstream direction and the blade span axis. This angle is measured in the direction of the rotation of the blade. It is zero in the downstream direction and Ωt for a constant rotational speed.
12 - Question
What is the formula to compute the moment of inertia of the rotor blade about center of rotation?
Explanation: Moment of inertia or rotational inertia of the rotor blade about the center of rotation is given by: Ib=∫R0mr2dr Where, m is the blade’s mass per unit length which is a function of r r is radial location of the blade measured from center (r=0) to the tip (r=R)
13 - Question
What is the value of linear twist rate in general?
Explanation: The rotor blade of the helicopter is twisted along the length of the blade. The linear twist rate θtw is given by the difference between tip pitch and the root pitch, where the pitch is the angle of the blade. This value is mostly negative.
14 - Question
What is blade lock number?
a) Ratio of inertial and aerodynamic force
b) Ratio of aerodynamic and inertial force
c) Ratio of viscous force and aerodynamic force
d) Ratio of inertial force and viscous force
Explanation: The rotor blade’s lock number is given as the ratio of the aerodynamic and inertial force. The formula is: γ=ρacR4Ib Where, γ is the blade lock number a is blade section two-dimensional lift curve slope c is the chord length R is the radial location to the blade tip Ib is the moment of inertia of the blade