Free Printable CPD240 FINAL S/64

1.

In straight and level flight at a constant IAS if flap is selected, it will increase the:

a)

(a) lift and the drag

b)

(b) Clmax and the drag

c)

(c) lift coefficient and the drag

d)

(d) stalling speed

2.

After take-off in an aeroplane fitted with both slats and flaps the reason that it is customary to retract the flaps first is:

a)

(a) Extended flaps decrease the stalling speed by a large amount with relatively little drag.

b)

(b) Extended slats decrease the stalling speed by a large amount with relatively little drag and have no effect on the climb gradient.

c)

(c) Extended slats give the pilot a better view from the cockpit than does extended flaps.

d)

(d) Extended slats enable a more favourable Vmca to be used.

3.

Extension of the Fowler-type trailing-edge flaps will produce:

a)

(a) a force that reduces drag

b)

(b) a nose-down pitching moment

c)

(c) no pitching moment

d)

(d) a nose-up pitching moment

4.

At a constant IAS in straight and level flight, if flaps are deployed the magnitude of the tip vortices will eventually:

a)

(a) increase

b)

(b) remain the same

c)

(c) increase or decrease depending on the initial angle of attack

d)

(d) decrease

5.

The most efficient flap system is the:

a)

(a) plain flap

b)

(b) single-slotted flap

c)

(c) Fowler flap

d)

(d) split flap

6.

The use of a slot at the leading edge of a wing enables the aeroplane to fly at a slower speed because:

a)

(a) it changes the camber of the wing

b)

(b) it delays the stall to a higher angle of attack

c)

(c) the laminar part of the boundary layer gets thicker

d)

(d) it decelerates the upper surface boundary layer

7.

Deploying a Fowler flap will cause it to:

a)

(a) turn down and then move aft

b)

(b) move aft

c)

(c) turn down

d)

(d) move aft and then turn down

8.

Full extension of a Fowler flap will:

a)

(a) increase the wing area only

b)

(b) increase the wing area and increase the camber

c)

(c) increase the camber only

d)

(d) not affect the Cd

9.

At a constant angle of attack, during flap retraction the aeroplane begins to:

a)

(a) climb

b)

(b) yaw

c)

(c) sink

d)

(d) bank

10.

When trailing-edge flaps are extended:

a)

(a) the critical angle of attack decreases and the Clmax increases

b)

(b) Clmax increases and the critical angle of attack increases

c)

(c) Clmax increases and the critical angle of attack remains the same

d)

(d) Vs increases and the critical angle of attack remains constant

11.

If all other factors remain constant the effect of extending trailing-edge flaps whilst maintaining a constant angle of attack is that the aeroplane will:

a)

(a) roll

b)

(b) climb

c)

(c) yaw

d)

(d) suddenly sink

12.

The effect of deploying trailing-edge flaps is:

a)

(a) increased minimum glide angle

b)

(b) decreased minimum glide angle

c)

(c) increased gliding endurance

d)

(d) decreased sink rate

13.

An aeroplane fitted with slats and flaps that have four settings, 0◦, 15◦, 30◦ and 45◦. Which of them when selected will have the greatest negative influence on the L/D ratio?

a)

(a) flaps from 15◦ to 30◦

b)

(b) flaps from 30◦ to 45◦

c)

(c) the slats

d)

(d) flaps from 0◦ to 15◦

14.

If an aeroplane flies in ground effect the result will be:

a)

(a) the lift increases and the drag decreases

b)

(b) the effective angle of attack is decreased

c)

(c) the induced angle of attack is increased

d)

(d) drag and lift decrease

15.

In straight and level flight at a constant mass, parasite drag is directly proportional to:

a)

(a) the square of the speed

b)

(b) speed

c)

(c) angle of attack

d)

(d) the square of the angle of attack

16.

Comparing Cl with Cd at a normal angle of attack:

a)

(a) Cl is much lower than Cd

b)

(b) Cl is much higher than Cd

c)

(c) Cl is approximately equal to Cd

d)

(d) Cl is lower than Cd

17.

The lowest total drag in level flight is when:

a)

(a) induced drag is zero

b)

(b) induced drag is lowest

c)

(c) parasite drag is equal to induced drag

d)

(d) parasite drag is twice the size of induced drag

18.

Induced drag:

a)

(a) increases as the aspect ratio increases

b)

(b) is not related to the lift coefficient

c)

(c) increases in direct proportion to the size of the wing-tip vortices

d)

(d) increases as the lift coefficient increases

19.

The part of an aeroplane that affects the induced drag the most is:

a)

(a) wing tip

b)

(b) engine cowling

c)

(c) wing root

d)

(d) landing gear

20.

The maximum L/D ratio is used to obtain:

a)

(a) the distance taken to climb to a specified altitude

b)

(b) the maximum distance taken to glide from a specified altitude in still air

c)

(c) the glide distance from a specified altitude

d)

(d) the minimum distance for the cruise

21.

A high aspect ratio wing produces:

a)

(a) an increased stalling speed

b)

(b) increased induced drag

c)

(c) decreased induced drag

d)

(d) less sensitivity to gust effects

22.

The relationship between the induced drag and the aspect ratio is:

a)

(a) a decrease in aspect ratio increases the induced drag

b)

(b) there is no relationship

c)

(c) induced drag = 1.3 times the aspect ratio

d)

(d) increased aspect ratio increases the induced drag

23.

Induced drag is created by the:

a)

(a) downwash across the wing

b)

(b) spanwise flow pattern resulting in wing-tip vortices

c)

(c) interference of the airstream between the wing and the fuselage

d)

(d) separation of the boundary layer

24.

If all other factors remain constant the effect that increased dynamic pressure has on total drag is:

a)

(a) none

b)

(b) that it decreases

c)

(c) that it is only affected by the groundspeed

d)

(d) that it increases

25.

Which of the following reduces induced drag?

a)

(a) flap extension

b)

(b) elliptical lift distribution

c)

(c) low aspect ratio

d)

(d) high angles of attack

26.

A high aspect ratio wing:

a)

(a) increases induced drag

b)

(b) decreases induced drag

c)

(c) has greater structural strength than a low aspect ratio wing

d)

(d) stalls at a higher angle than a low aspect ratio wing

27.

In straight and level flight at a constant IAS, when flaps are lowered the induced drag:

a)

(a) is unchanged

b)

(b) decreases

c)

(c) increases

d)

(d) increases or decreases depending on aeroplane type

28.

The effect that winglets have is that they:

a)

(a) decrease the stalling speed

b)

(b) increase static longitudinal stability

c)

(c) reduce induced drag

d)

(d) increase the value of Vmd

29.

Ground effect could begin to be felt during the approach to land:

a)

(a) at a height equal to twice the wingspan above the ground

b)

(b) at a height equal to one wingspan above the ground

c)

(c) when the angle of attack is increased

d)

(d) at a height equal to half the wingspan above the ground

30.

When an aeroplane enters ground effect the lift vector is inclined (i) . . . . . . . . ., which (ii) . . . . . . . . . . . the thrust required.

a)

(a) (i) forward (ii) reduces

b)

(b) (i) forward (ii) increases

c)

(c) (i) rearward (ii) reduces

d)

(d) (i) rearward (ii) increases

31.

On entering ground effect:

a)

(a) more power is required

b)

(b) the power required is not affected

c)

(c) less power is required

d)

(d) lift decreases

32.

Deploying spoiler surfaces results in drag (i) . . . . . . . . . . and lift (ii) . . . . . . . . . .

a)

(a) (i) increasing; (ii) increasing

b)

(b) (i) increasing; (ii) decreasing

c)

(c) (i) decreasing; (ii) increasing

d)

(d) (i) decreasing; (ii) decreasing

33.

Which of the following statements is correct regarding Vmd?

a)

(a) Parasite drag is greater than induced drag.

b)

(b) The ratio of lift to drag is maximum.

c)

(c) The best glide range is achieved at this speed.

d)

(d) It is the best endurance speed for a piston-engined aeroplane.

34.

Which of the following statements regarding the stalling speed is correct?

a)

(a) The stalling speed is decreased with a smaller angle of sweep.

b)

(b) The stalling speed is increased with a smaller angle of sweep

c)

(c) The stalling speed is decreased with T-tail.

d)

(d) The stalling speed is decreased with increased anhedral.

35.

Which of the following design features is most likely to cause an aeroplane to superstall?

a)

(a) A T-tail.

b)

(b) A canard wing.

c)

(c) Swept wings.

d)

(d) A low horizontal tail.

36.

All other factors remaining constant, the stalling speed increases when:

a)

(a) spoilers are retracted

b)

(b) pulling out of a dive

c)

(c) the mass decreases

d)

(d) altitude is increased

37.

Which of the following statements regarding the spin is correct?

a)

(a) in a spin the airspeed continually increases

b)

(b) all aeroplanes are designed so that they can never spin

c)

(c) during spin recovery the ailerons should be in the neutral position

d)

(d) an aeroplane is most likely to spin when the stall starts at the wing root

38.

The effect on the stall that the downwash from a swept wing contacting a horizontal tail has is that it causes:

a)

(a) a nose-up tendency and/or lack of elevator response

b)

(b) nose-down tendency

c)

(c) increased sensitivity of elevator inputs

d)

(d) a tendency to accelerate after the stall

39.

The vane of a stall-warning system with a flapper switch is activated by the movement of the:

a)

(a) point of lowest pressure

b)

(b) stagnation point

c)

(c) centre of pressure

d)

(d) centre of gravity

40.

The pitch-up effect of an aeroplane with swept wings in a stall is due to:

a)

(a) aft movement of the CG

b)

(b) forward movement of the CG

c)

(c) the wing root stalling first

d)

(d) the wing tip stalling first

41.

During an erect spin recovery:

a)

(a) the control column is moved to the most aft position

b)

(b) the ailerons are held in the neutral position

c)

(c) the control column is moved sideways in the opposite direction to the bank

d)

(d) the control column is moved sideways in the same direction as the bank

42.

The type of stall that has the largest associated angle of attack is:

a)

(a) accelerated

b)

(b) low speed

c)

(c) deep

d)

(d) shock

43.

Vortex generators on the upper surface of a wing will:

a)

(a) increase the magnitude of the shockwave

b)

(b) decrease the intensity of the shockwave induced air separation

c)

(c) increase the critical Mach number

d)

(d) decrease the spanwise flow at high Mach numbers

44.

When an aerofoil stalls the lift (i) . . . . . . . . and the drag (ii). . . . . . . . . . .

a)

(a) (i) decreases; (ii) decreases

b)

(b) (i) remains constant; (ii) decreases

c)

(c) (i) decreases; (ii) remains constant

d)

(d) (i) decreases; (ii) increases

45.

The recovery procedure from a stall in a light single-engined aeroplane is:

a)

(a) maximum power; stick forward roll neutral; correct for bank with rudder

b)

(b) maximum power; stick neutral and forward, correct for bank with stick

c)

(c) idle power; stick neutral; wait for normal nose-down tendency

d)

(d) idle power; stick-roll neutral and forward

46.

Where does flow separation commence at high angles of attack?

a)

(a) upper surface towards the trailing edge

b)

(b) upper surface towards the leading edge

c)

(c) lower surface towards the trailing edge

d)

(d) lower surface towards the leading edge

47.

Which of the following increases the stalling angle?

a)

(a) flaps

b)

(b) slats

c)

(c) spoilers

d)

(d) ailerons

48.

At high altitude an aeroplane encounters severe turbulence but no high-speed buffet. In these conditions if the aeroplane decelerates the type of stall most likely to be experienced first is:

a)

(a) low-speed

b)

(b) accelerated

c)

(c) deep

d)

(d) shock

49.

Vortex generators on the upper surface of the wing will:

a)

(a) decrease the stalling speed by increasing the tangential velocity of the swept wing

b)

(b) increase the effectiveness of the spoiler due to the increase of parasite drag

c)

(c) decrease the shock-wave-induced separation

d)

(d) decrease the interference drag of the trailing-edge flaps

50.

The reason that swept-wing aeroplanes are more likely to deep stall is:

a)

(a) the CP moves aft

b)

(b) the CP moves forward

c)

(c) the wing root stalls first

d)

(d) The upper surface spanwise flow is from tip to root

CPD240 FINAL S/64

Total questions: 50

Worksheet time: 55mins

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