Module 8 Set 5 AST
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1
The lift produced by an aero foil
- Varies with the area of the aero foil
- Depends primarily on the thrust that each engine produces
- Varies directly with the area of the aero foil
2
The coefficient of lift
- Decreases with an increase in airspeed
- Increases as the centre of pressure move rearwards
- Increases with an increase in angle of attack
3
Lift coefficient may be increased by
- Increasing the wing angle of attack
- Increasing forward speed
- Gaining height
4
A typical aero foil at zero degrees angle of attack will produce
- No lift
- No drag
- Some lift and drag
5
The centre of pressure will move, over a cambered aero foil, in a normal working range aft of the leading edge by
- 5% - 10%
- 25% - 30%
- 35% - 45%
6
If the weight of an aircraft is increased, the profile drag at a given speed will
- Increase
- Decrease
- Remains the same
7
Airflows mixing at airframe junctions will normally lead to
- Interference drag
- Induced drag
- Form drag
8
The induced drag of an aircraft is the drag due to the
- Lift being produced
- Surface roughness
- Frontal area
9
One of the benefits of a ‘High Aspect Ratio’ wing is to reduce the
- “Zero Lift” aircraft drag
- Parasite drag
- Induced drag
10
Zero lift drag will only occur when the aircraft is in
- Steep dive
- Shallow glide
- Truly vertical flight
11
At the transition point the boundary layer becomes
- Thinner with turbulent flow
- Thicker with laminar flow
- Thicker with turbulent flow
12
The airflow over an aircraft wing of finite length is considered to be
- Steady
- Two dimensional
- Three dimensional
13
Airflow around a cylindrical body becomes turbulent at the
- Transition point
- Stagnation point
- Terminal velocity
14
The stagnation point on an aero foil is the point where the
- Suction pressure reaches a maximum
- Airflow is brought completely to rest
- Boundary layer changes from laminar to turbulent
15
Downstream from the leading edge of an aero foil, the boundary layer will
- Thicken
- Thin out
- Become laminar
16
The layer of air extending from the surface of an object to the point where no dragging occurs is known as
- Stagnation layer
- Turbulent layer
- Boundary layer
17
The angle of attack of an aero foil is the angle that the
- Chord line makes with the longitudinal axis
- Chord line makes with the relative airflow
- Airframe makes with the horizontal when the aircraft is in a rigging position
18
The chord line of an aero foil is
- A line, each point of which is equal distant from the upper and lower surfaces of an aero foil section
- A straight line drawn through the centers of curvature at the leading and trailing edges of an aero foil section
- A straight line tangential to the top surface at the leading edge
19
Wash out will ensure
- Tip of the wing stalls first giving a greater warning to the pilot of a complete stall
- Root of the wing stalls first maintaining control over the ailerons
- Complete wing stalls at once reducing the risk of structural failure
20
Washout on a wing refers to
- A greater angle of incidence at the wing root than at the wing tip
- An increase in angle of incidence from the wing root to the wing tip
- The distance between the leading and and trailing edge of a wing
21
An aero foil with zero camber will
- Have a reflex trailing edge
- Be symmetrical in section
- Have a concave lower section
22
A common feature designed to prevent wing tip stall is
- A reduction in incidence at the tips, called washout
- The use of slats to increase the stalling angle
- Root spoilers to cause airflow breakaway
23
As the angle of attack increases
- Induced drag decreases
- Induced drag increases
- Wingtip vortices decrease
24
On an aero foil section, as the angle of attack is increased, the
- Transition point moves towards the trailing edge
- Stagnation point moves away from the leading edge underneath the wing
- Stagnation point moves round the leading edge to towards the transition point
25
When the angle of attack of an aero foil is increased
- The lift coefficient increases as the centre point of pressure moves rearwards
- A forward movement of the centre of pressure coincides with an increase of the lift coefficient
- The coefficient of lift reduces with an increase in drag
26
As an airflow approaches an aero foil at an angle of attack it experiences
- Upwash
- Downwash
- A vortex
27
On a rectangular wing platform a small stall strip is installed on the inboard section of the wings leading edge to ensure
- The outboard section of the wing stalls first
- Elevator control is not lost at the beginning of a stall condition
- The wing root area stalls first allowing the aileron control to continue throughout the stall
28
If two identical aeroplane with a large difference in their weight are stalled
- The heavier will have a higher stalling speed than the lighter
- The lighter will have a higher stalling speed than the heavier
- They will both stall at the same speed
29
An aircraft wing is designed to stall
- Along the whole length simultaneously
- Progressively from root to tip
- Progressively from tip to root
30
If the throttle is opened and the angle of attack is held constant, the airspeed and altitude are
- Increased continuously at a constant rate
- Increased initially then stabilized at new values
- Unchanged
31
When viewed from the rear, wingtip vortices rotate
- Clockwise on the port wing, anti clockwise on the starboard wing
- Anti clockwise on the port wing, clockwise on the starboard wing
- Anti clockwise on both wings
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