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Module 11 – Aeroplane Aerodynamics, Structures & Systems
- Question: Asymmetrical deployment of wing spoilers is primarily used in conjunction with which other control surface?
Options:
A) Ailerons
B) Rudder
C) Elevators
Correct Answer: A
Explanation: Wing spoilers, when deployed asymmetrically (one wing’s spoiler extending more than the other), are primarily used to assist or replace ailerons in achieving lateral control (roll) of the aircraft.
- Question: To counteract a left yawing tendency of an aircraft, in which direction should the rudder trim tab be positioned?
Options:
A) Neutral (centre)
B) To the right
C) To the left
Correct Answer: C
Explanation: To trim for a left yaw, you need to create a force that pushes the rudder to the right. A trim tab works by deflecting in the opposite direction to the control surface’s desired movement. Therefore, to move the rudder to the right, the trim tab on the rudder should be deflected to the left. This creates airflow that pushes the rudder to the right, counteracting the left yaw.
- Question: If an aircraft is flying with a left wing low, in which direction would you move the left aileron trim tab?
Options:
A) Down
B) Up
C) Moving the aileron trim tab will not correct the situation.
Correct Answer: B
Explanation: To correct a left wing low condition, we need to raise the left aileron. An aileron trim tab works by deflecting in the opposite direction to the desired control surface movement. Therefore, to move the left aileron up, the left aileron trim tab should be moved upwards. This creates airflow that pushes the aileron up, correcting the low wing.
- Question: When a leading edge flap is fully extended, what is the purpose of the slot in the wing?
Options:
A) To allow the flap to retract into it when it retracts.
B) To re-energise the boundary layer.
C) To increase the lift.
Correct Answer:1 B
Explanation: The slot created when a leading edge flap (or slat) is extended allows high-energy air from below the wing to flow over the top surface. This high-energy air re-energises the boundary layer, helping to delay airflow separation at high angles of attack and thus increasing the stalling angle of the wing.
- Question: Regarding differential aileron control, which statement is accurate?
Options:
A) The upward-moving aileron deflects through a smaller angle than the downward-moving aileron.
B) Both the upward and downward-moving ailerons deflect to the same angle.
C) The downward-moving aileron deflects through a smaller angle than the upward-moving aileron.
Correct Answer: C
Explanation: Differential aileron control is a design feature where the upward-moving aileron deflects more than the downward-moving aileron. This is done to counteract adverse yaw, which is the tendency of the aircraft to yaw in the opposite direction of the roll when ailerons are used. The increased drag on the wing with the upward-moving aileron helps to balance the drag created by the increased lift on the wing with the downward-moving aileron.
- Question: An aeroplane’s fin has a symmetrical aerofoil section. Under what condition will it produce a side-load?
Options:
A) If a suitable angle of attack develops due to either yaw or rudder movement.
B) Only if a suitable angle of attack develops due to yaw.
C) Only when the rudder is moved.
Correct Answer: A
Explanation: A symmetrical aerofoil, such as that of an aeroplane’s fin, will generate a side-load (a force perpendicular to the airflow) whenever it experiences an angle of attack. This angle of attack can be created either by the aircraft yawing (moving its nose to one side relative to the airflow) or by the deflection of the rudder, which changes the airflow’s direction over the fin.
- Question: An aircraft’s left wing is flying lower than the right wing. How would the aileron trimmer control in the cockpit for the left aileron trim tab typically be moved?
Options:
A) Moved up, causing the left aileron to move up.
B) Moved up, causing the left aileron to move down.
C) Moved down, causing the left aileron to move down.
Correct Answer: B
Explanation: If the left wing is low, it means that wing is producing less lift than the right. To correct this, we need to raise the left aileron. An aileron trim tab works by deflecting in the opposite direction to the desired control surface movement. Therefore, to move the left aileron up, the left aileron trim tab control in the cockpit would be moved upwards. This would cause the trim tab itself to deflect downwards, creating airflow that pushes the left aileron down.
- Question: What is the primary function of a slot in an aircraft wing?
Options:
A) To increase the speed of airflow and thereby increase lift.
B) To act as a venturi, accelerating the air and re-energising the boundary layer.
C) To provide a housing or track for the slat to extend into.
Correct Answer: B
Explanation: A slot in a wing, often associated with leading-edge slats or fixed slots, is designed to improve airflow at high angles of attack. It does this by creating a venturi effect, where air flowing through the narrow opening is accelerated. This accelerated, higher-energy air is then directed over the upper surface of the wing, re-energising the boundary layer. By energising the boundary layer, the slot helps to prevent or delay airflow separation, allowing the wing to maintain lift at higher angles of attack, thus increasing the stalling angle.
- Question: What effect does large flap deployment have on spanwise flow on a wing?
Options:
A) It has no effect on spanwise flow.
B) It causes increased spanwise flow towards the tips on the wing’s upper surface.
C) It causes increased spanwise flow towards the tips on the wing’s lower surface.
Correct Answer: C
Explanation: Deploying flaps significantly increases the pressure difference between the lower and upper surfaces of the wing. This increased pressure differential at the wing tips leads to a stronger flow of air from the high-pressure area on the lower surface, around the tip, to the low-pressure area on the upper surface. This is known as spanwise flow, and large flap deployment intensifies this flow towards the wing tips on the lower surface.
- Question: During flight, if an aircraft yaws to the right, what would be its tendency regarding the wings?
Options:
A) The right wing would tend to go low.
B) The aircraft’s nose would tend to pitch up.
C) The left wing would tend to go low.
Correct Answer: A
Explanation: When an aircraft yaws to the right, the left wing moves forward relative to the airflow, and the right wing moves backward. The advancing wing (left wing) experiences a slight increase in relative airspeed and thus generates more lift, causing it to rise. Conversely, the retreating wing (right wing) experiences a slight decrease in relative airspeed and generates less lift, causing it to drop. Therefore, a right yaw typically results in a tendency for the right wing to go low.
- Question: How will an aircraft’s service ceiling be affected by a drop in ambient temperature?
Options:
A) It will not be affected.
B) It will decrease.
C) It will increase.
Correct Answer: C
Explanation: Service ceiling is the maximum altitude an aircraft can maintain a specified rate of climb. When the ambient temperature drops, the air density increases. Denser air allows the engine to produce more power and the wings to generate more lift at a given true airspeed, thus enabling the aircraft to achieve a higher service ceiling.
- Question: What effect does extending a leading edge slat typically have on the angle of attack of a wing at which stall occurs?
Options:
A) It increases the angle of attack.
B) It decreases the angle of attack.
C) It has no effect on the angle of attack.
Correct Answer: A
Explanation: Extending a leading edge slat creates a slot between the slat and the main wing. This slot allows high-energy air from the lower surface to flow over the top surface, re-energizing the boundary layer. By delaying boundary layer separation, the wing can achieve a higher maximum angle of attack before stalling.
- Question: With reference to differential aileron control, which of the following is a consequence?
Options:
A) Drag increases on the inner wing (the wing with the down-going aileron).
B) Drag decreases on the outer wing (the wing with the up-going aileron).
C) Drag increases on the outer wing (the wing with the up-going aileron).
Correct Answer: A
Explanation: Differential aileron control involves the upward-moving aileron deflecting more than the downward-moving aileron. The downward deflection of an aileron increases the lift and also induces more drag on that wing (the inner wing in a turn). The smaller downward deflection helps to balance the drag produced by the increased lift, reducing adverse yaw.
- Question: If an aircraft is aerodynamically stable, what will happen if it is momentarily disturbed from its trimmed attitude?
Options:
A) The aircraft will become excessively sensitive to control inputs.
B) The aircraft will naturally return to its original trimmed attitude.
C) The aircraft’s Centre of Pressure will shift rearwards.
Correct Answer: B
Explanation: Aerodynamic stability refers to an aircraft’s inherent tendency to return to its original equilibrium state after being disturbed. If a stable aircraft is nudged away from its trimmed attitude (e.g., by a gust of wind), it will generate forces and moments that act to restore it to its previous balanced state without any pilot input.
- Question: What is the primary function of slats on an aircraft wing?
Options:
A) To act as an air brake, increasing drag.
B) To prevent the boundary layer from separating from the upper surface for a longer duration at high angles of attack.
C) To increase the overall surface area and lift capability of the wing.
Correct Answer: B
Explanation: Slats are leading-edge devices that, when extended, create a slot between the slat and the main wing. This slot directs high-energy air from the lower surface over the upper surface, re-energizing the boundary layer. By preventing or delaying boundary layer separation, slats allow the wing to maintain lift at higher angles of attack, increasing the maximum lift coefficient and the stalling angle.
- Question: Due to the change in lift forces resulting from the extension of flaps during flight, what is the typical pilot action required to maintain altitude?
Options:
A) The pilot should lower the nose, reducing the angle of attack.
B) The pilot should maintain the same nose position, keeping the angle of attack constant.
C) The pilot should raise the nose, increasing the angle of attack.
Correct Answer: A
Explanation: Extending flaps increases the lift coefficient of the wing at a given angle of attack and airspeed. To maintain the same amount of lift (and thus altitude) at the same airspeed after extending flaps, the angle of attack needs to be reduced. This is typically achieved by lowering the aircraft’s nose.
- Question: If an aircraft is flying with a nose-heavy tendency, in which direction would you typically move the elevator trim tab?
Options:
A) Up, to move the elevator up.
B) Down, to move the elevator up.
C) Up, to move the elevator down.
Correct Answer: B
Explanation: A nose-heavy condition means the aircraft’s nose is tending to pitch down. To counteract this, we need to create a downward force on the tailplane, which effectively raises the nose. This is achieved by deflecting the elevator upwards. An elevator trim tab moves in the opposite direction to the desired elevator movement. Therefore, to move the elevator up, the elevator trim tab should be moved downwards.
- Question: What is the primary function of a balance tab on a control surface?
Options:
A) It assists the pilot in moving the controls by providing a mechanical advantage.
B) It is used to trim the aircraft about the appropriate axis.
C) It effectively increases the surface area of the control surface.
Correct Answer: A
Explanation: A balance tab is a small hinged surface on the trailing edge of a control surface. It is linked to the aircraft’s structure in such a way that when the pilot moves the main control surface, the balance tab deflects in the opposite direction. This creates an aerodynamic force that helps to move the main control surface, reducing the effort required by the pilot.
- Question: When the ailerons are moved to initiate a roll, which wing typically experiences a greater increase in drag?
Options:
A) Both wings have an equal increase in drag.
B) Both wings increase drag, but the wing with the down-going aileron increases more.
C) Both wings increase drag, but the wing with the up-going aileron increases more.3
Correct Answer: B
Explanation: When the ailerons are deflected, the down-going aileron increases the lift on that wing, which also results in an increase in induced drag. The up-going aileron decreases lift and drag, but the overall effect is that the wing with the down-going aileron experiences a greater increase in drag. This difference in drag can lead to adverse yaw.
- Question: Under what condition will an automatic slat typically extend on its own?
Options:
A) When the angle of attack is low.
B) When the angle of attack is either high or low.
C) When the angle of attack is high.
Correct Answer: C
Explanation: Automatic slats are designed to deploy when the aircraft approaches its critical angle of attack. At high angles of attack, there is a greater risk of airflow separation over the wing. The slats extend to re-energize the boundary layer and increase the stalling angle, thus providing a safety margin.
