(Stability and Control MCQs Aeronautical Engineering

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The term ‘static stability’ refers to:

A) The aircraft’s ability to return to its original position after a disturbance
B) The aircraft’s ability to maintain a constant altitude
C) The ability of an aircraft to maintain its speed
D) The resistance of an aircraft to turbulence
Answer: A) The aircraft’s ability to return to its original position after a disturbance
In aerodynamics, ‘dynamic stability’ involves:

A) The aircraft’s long-term response to disturbances
B) The immediate response to control inputs
C) The resistance of an aircraft to aerodynamic forces
D) The maintenance of constant speed
Answer: A) The aircraft’s long-term response to disturbances
The ‘center of gravity’ (CG) is important for:

A) Determining the aircraft’s stability and control
B) Increasing the aircraft’s lift
C) Reducing the aircraft’s drag
D) Improving fuel efficiency
Answer: A) Determining the aircraft’s stability and control
‘Positive static stability’ means:

A) The aircraft will return to its original position after being displaced
B) The aircraft’s control surfaces will always be effective
C) The aircraft will continue to move in the direction it was originally heading
D) The aircraft’s engine will maintain a constant thrust
Answer: A) The aircraft will return to its original position after being displaced
What does ‘dynamic response’ refer to in an aircraft?

A) The aircraft’s behavior over time after a disturbance
B) The immediate reaction to control surface movements
C) The stability of the aircraft in still air
D) The effect of altitude on aircraft performance
Answer: A) The aircraft’s behavior over time after a disturbance
‘Control authority’ is defined as:

A) The effectiveness of the control surfaces to alter the aircraft’s attitude
B) The aircraft’s ability to maintain a steady speed
C) The rate at which the aircraft can climb
D) The amount of thrust produced by the engines
Answer: A) The effectiveness of the control surfaces to alter the aircraft’s attitude
Which axis is controlled by the ailerons?

A) Longitudinal axis
B) Lateral axis
C) Vertical axis
D) Yaw axis
Answer: A) Longitudinal axis
The ‘vertical stabilizer’ affects:

A) Yaw control
B) Pitch control
C) Roll control
D) Altitude control
Answer: A) Yaw control
In stability analysis, ‘dihedral angle’ helps to:

A) Improve lateral stability
B) Enhance longitudinal stability
C) Increase drag
D) Reduce the aircraft’s speed
Answer: A) Improve lateral stability
A ‘positive static margin’ indicates:

A) The aircraft is statically stable
B) The aircraft is dynamically unstable
C) The aircraft will oscillate uncontrollably
D) The aircraft has excessive drag
Answer: A) The aircraft is statically stable
‘Dutch roll’ is:

A) A type of oscillation involving combined rolling and yawing motions
B) A rapid pitch movement caused by turbulence
C) A sudden loss of altitude during a turn
D) A continuous increase in airspeed
Answer: A) A type of oscillation involving combined rolling and yawing motions
The ‘angle of attack’ (AoA) is critical for:

A) Determining lift and stall characteristics
B) Controlling the aircraft’s yaw
C) Maintaining a steady speed
D) Increasing engine thrust
Answer: A) Determining lift and stall characteristics
‘Static margin’ is defined as:

A) The distance between the center of gravity and the neutral point
B) The distance between the aircraft’s wings
C) The distance between the aircraft’s engine and the fuselage
D) The distance between the aircraft’s center of pressure and center of gravity
Answer: A) The distance between the center of gravity and the neutral point
The ‘neutral point’ in stability refers to:

A) The point where the aircraft’s pitching moments are balanced
B) The point where the aircraft’s speed is maximized
C) The point where the aircraft’s drag is minimized
D) The point where the aircraft’s lift equals weight
Answer: A) The point where the aircraft’s pitching moments are balanced
‘Dynamic stability’ is evaluated by:

A) Observing the aircraft’s response to disturbances over time
B) Measuring the aircraft’s immediate response to control inputs
C) Assessing the aircraft’s fuel efficiency
D) Evaluating the aircraft’s maximum speed
Answer: A) Observing the aircraft’s response to disturbances over time
The ‘rudder’ is used primarily to control:

A) Yaw
B) Pitch
C) Roll
D) Speed
Answer: A) Yaw
The ‘elevator’ is responsible for controlling:

A) Pitch
B) Roll
C) Yaw
D) Speed
Answer: A) Pitch
The ‘roll rate’ of an aircraft is influenced by:

A) Ailerons
B) Elevators
C) Rudder
D) Flaps
Answer: A) Ailerons
The ‘control authority’ of an aircraft is maximized by:

A) Properly designing the control surfaces and their effectiveness
B) Increasing the aircraft’s weight
C) Decreasing the aircraft’s speed
D) Reducing the aircraft’s altitude
Answer: A) Properly designing the control surfaces and their effectiveness
A ‘statically unstable’ aircraft:

A) Will not return to its original position after being disturbed
B) Will return to its original position after being disturbed
C) Will have increased control surface effectiveness
D) Will have reduced drag
Answer: A) Will not return to its original position after being disturbed
In stability terms, ‘neutral stability’ means:

A) The aircraft will neither return to nor diverge from its original position after a disturbance
B) The aircraft will return to its original position after a disturbance
C) The aircraft will diverge further from its original position after a disturbance
D) The aircraft’s speed will be affected
Answer: A) The aircraft will neither return to nor diverge from its original position after a disturbance
The ‘mean aerodynamic chord’ (MAC) is important for:

A) Calculating the aircraft’s stability characteristics
B) Measuring the aircraft’s drag
C) Determining the aircraft’s thrust requirements
D) Assessing the aircraft’s engine performance
Answer: A) Calculating the aircraft’s stability characteristics
The ‘aircraft’s center of pressure’ moves:

A) Forward with increasing angle of attack
B) Backward with increasing angle of attack
C) Remains constant with changing angle of attack
D) Varies with the aircraft’s speed
Answer: B) Backward with increasing angle of attack
‘Longitudinal stability’ is influenced by:

A) The position of the center of gravity relative to the center of lift
B) The position of the vertical stabilizer
C) The aircraft’s wing configuration
D) The amount of thrust produced by the engines
Answer: A) The position of the center of gravity relative to the center of lift
The ‘dihedral effect’ refers to:

A) The improvement in roll stability due to the angle of the wings
B) The reduction in drag due to the aircraft’s design
C) The increase in lift due to wing camber
D) The change in pitch due to control surface adjustments
Answer: A) The improvement in roll stability due to the angle of the wings
‘Yawing moment’ is controlled by:

A) The rudder
B) The ailerons
C) The elevators
D) The flaps
Answer: A) The rudder
In terms of stability, a ‘high center of gravity’ tends to:

A) Reduce lateral stability
B) Increase longitudinal stability
C) Improve yaw control
D) Enhance roll stability
Answer: A) Reduce lateral stability
The ‘neutral point’ is:

A) The location where the pitching moments balance
B) The point where the aircraft’s drag is minimized
C) The point where the aircraft’s speed is maximized
D) The point where the aircraft’s weight is evenly distributed
Answer: A) The location where the pitching moments balance
‘Static margin’ can be increased by:

A) Moving the center of gravity forward
B) Moving the center of gravity backward
C) Reducing the aircraft’s speed
D) Increasing the aircraft’s weight
Answer: A) Moving the center of gravity forward
The ‘power-off stall’ is:

A) A stall occurring when the engines are not producing thrust
B) A stall occurring during a high-speed dive
C) A stall occurring during a climb
D) A stall occurring with full engine power
Answer: A) A stall occurring when the engines are not producing thrust
The ‘trim’ control in an aircraft is used to:

A) Maintain a desired attitude without constant control input
B) Change the aircraft’s speed
C) Alter the aircraft’s altitude
D) Control the aircraft’s roll rate
Answer: A) Maintain a desired attitude without constant control input
‘Static stability’ is a measure of:

A) The aircraft’s immediate response to a disturbance
B) The aircraft’s long-term response to a disturbance
C) The aircraft’s ability to return to its original position after a disturbance
D) The aircraft’s resistance to aerodynamic forces
Answer: C) The aircraft’s ability to return to its original position after a disturbance
In a stable aircraft, the center of gravity is typically:

A) Ahead of the center of lift
B) Behind the center of lift
C) Directly above the center of lift
D) Directly below the center of lift
Answer: A) Ahead of the center of lift
The ‘aerodynamic center’ is:

A) The point where the pitching moment is constant regardless of the angle of attack
B) The point where the center of gravity is located
C) The point where the lift is maximized
D) The point where the drag is minimized
Answer: A) The point where the pitching moment is constant regardless of the angle of attack
A ‘negative static margin’ indicates:

A) The aircraft is statically unstable
B) The aircraft has excessive drag
C) The aircraft will have improved roll stability
D) The aircraft will be more fuel-efficient
Answer: A) The aircraft is statically unstable
‘Yaw stability’ is primarily controlled by:

A) The vertical stabilizer and rudder
B) The ailerons and elevators
C) The flaps and slats
D) The wing configuration
Answer: A) The vertical stabilizer and rudder
‘Roll stability’ is influenced by:

A) The dihedral angle of the wings
B) The position of the center of gravity
C) The aircraft’s engine thrust
D) The shape of the fuselage
Answer: A) The dihedral angle of the wings
The ‘stick-free’ mode in aircraft stability:

A) Allows for automatic adjustment of the control surfaces without pilot input
B) Requires manual adjustment of all control surfaces
C) Provides increased resistance to turbulence
D) Improves fuel efficiency
Answer: A) Allows for automatic adjustment of the control surfaces without pilot input
The ‘roll axis’ is controlled by:

A) Ailerons
B) Elevators
C) Rudder
D) Trim tabs
Answer: A) Ailerons
‘Longitudinal stability’ is achieved by:

A) Ensuring the center of gravity is forward of the center of lift
B) Aligning the vertical stabilizer with the aircraft’s longitudinal axis
C) Adjusting the aircraft’s speed and altitude
D) Increasing the size of the control surfaces
Answer: A) Ensuring the center of gravity is forward of the center of lift
‘Lateral stability’ in an aircraft is affected by:

A) The dihedral angle and sweepback of the wings
B) The position of the horizontal stabilizer
C) The engine thrust and configuration
D) The aircraft’s landing gear design
Answer: A) The dihedral angle and sweepback of the wings
The ‘stick-pusher’ system is designed to:

A) Prevent the aircraft from exceeding critical angles of attack
B) Increase the aircraft’s roll rate
C) Improve the aircraft’s yaw control
D) Enhance the aircraft’s pitch stability
Answer: A) Prevent the aircraft from exceeding critical angles of attack
‘Directional stability’ refers to:

A) The aircraft’s ability to maintain a straight flight path without yawing
B) The aircraft’s ability to maintain a steady climb rate
C) The aircraft’s ability to remain level in turbulent conditions
D) The aircraft’s ability to increase speed rapidly
Answer: A) The aircraft’s ability to maintain a straight flight path without yawing
The ‘yaw damper’ is used to:

A) Reduce oscillations and improve directional stability
B) Increase the aircraft’s roll rate
C) Maintain a constant altitude
D) Enhance pitch stability
Answer: A) Reduce oscillations and improve directional stability
The ‘moment coefficient’ is used to:

A) Determine the pitching moment relative to the center of gravity
B) Calculate the aircraft’s lift-to-drag ratio
C) Measure the aircraft’s fuel efficiency
D) Assess the aircraft’s maximum speed
Answer: A) Determine the pitching moment relative to the center of gravity
In ‘static stability,’ a positive restoring force means:

A) The aircraft will return to its original position after being disturbed
B) The aircraft will continue to move away from its original position
C) The aircraft will maintain a constant speed
D) The aircraft will increase its altitude
Answer: A) The aircraft will return to its original position after being disturbed
The ‘aircraft’s trim tab’ helps in:

A) Adjusting the control surfaces to maintain a desired flight attitude
B) Increasing the aircraft’s maximum speed
C) Reducing drag and increasing lift
D) Improving fuel efficiency
Answer: A) Adjusting the control surfaces to maintain a desired flight attitude
‘Yawing moment’ is affected by:

A) The rudder deflection and the aircraft’s speed
B) The aileron deflection and the aircraft’s weight
C) The elevator deflection and the altitude
D) The flap position and the aircraft’s climb rate
Answer: A) The rudder deflection and the aircraft’s speed
The ‘critical engine-out minimum control speed’ (Vmc) is:

A) The minimum speed at which the aircraft can maintain controlled flight with one engine inoperative
B) The maximum speed at which the aircraft can safely climb
C) The minimum speed required for takeoff
D) The maximum speed at which the aircraft can operate safely
Answer: A) The minimum speed at which the aircraft can maintain controlled flight with one engine inoperative
The ‘aircraft’s load factor’ is:

A) The ratio of the total aerodynamic force to the aircraft’s weight
B) The total weight of the aircraft
C) The ratio of the aircraft’s lift to its drag
D) The difference between the aircraft’s maximum and minimum speeds
Answer: A) The ratio of the total aerodynamic force to the aircraft’s weight

 

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