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pof sf charlie Flashcards

1
Q

please select whether the following statements are correct or incorrect.

Considering the air passing through a divergent duct:

  1. the static pressure increases.
  2. the total pressure reduces.

a. 1. correct, 2. incorrect
b. 1. incorrect, 2. incorrect
c. 1. correct, 2. correct
d. 1. incorrect, 2. correct

A

a. 1. correct, 2. incorrect

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1
Q

what are the SI units for the following?

  1. wing loading [ ]
  2. power [ ]
  3. energy [ ]

[kg/m2]
[kg]
[kg/m3]
[watts]
[joules]
[kelvin]
[newtons]

A
  1. [kg/m2]
  2. [watts]
  3. [joules]
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2
Q

‘an imaginary straight line drawn between the centre of the leading edge and the trailing edge’ is the:

a. chord line
b. mean aerodynamic chord
c. chord
d. camber line

A

a. chord line

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3
Q

which of the following wing designs reduce induced drag?

pick all correct answers

a. increasing the length of the wing tip chord
b. winglets
c. increasing the aspect ratio.
d. increasing the angle of incidence towards the wingtip.
e. reducing the camber towards the wingtip.

A

a. increasing the length of the wing tip chord
c. increasing the aspect ratio.
d. increasing the angle of incidence towards the wingtip.
e. reducing the camber towards the wingtip.

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4
Q

which of the following can be read off a drag polar graph?

pick all correct answers

a. CLMAX
b. critical Angle of Attack
c. the parasite drag at zero CL.
d. CDP
e. CL/CD ratio at any CL
f. the numerical speed for minimum drag.

A

a. CLMAX
e. CL/CD ratio at any CL

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5
Q

Skin friction drag is:

a. parasite drag minus form drag.

b. a product of surface interaction slowing the molecules in the boundary layer due to viscosity.

c. a product of friction between the molecules in a large volume of air affected by the passage of the object.

d. a product of vortices whenever lift is created.

A

b. a product of surface interaction slowing the molecules in the boundary layer due to viscosity.

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6
Q

An aircraft increases the speed by 70% whilst maintaining straight and level flight. The Parasite Drag will:

a. increase by 289%

b. increase by 189%

c. increase by 49%

d. increase by 70%

A

a. increase by 289%

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7
Q

An altitude increases the total drag curve drawn against the iAS will:

a. move up

b. move to the right

c. remain in the same location

d. move up and to the right

A

d. move up and to the right

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8
Q

Upon leaving ground effect the wing vortices will [ ], the EAF will become [ ] and the effective alpha will [ ].

A

Upon leaving ground effect the wing vortices will [ increase ], the EAF will become [ steeper ] and the effective alpha will [ ].

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9
Q

Regarding the CL - alpha graph, for an aeroplane with a low aspect ratio wing compared to an aeroplane with a high aspect ratio wing:

a. the gradient is shallower, which reduces the threat of excessive load factor in vertical gusts.

b. the gradient will be steeper and the critical angle of attack smaller.

c. the gradient is the same, but CLmax would increase, resulting in a larger gust load factor.

d. for symmetrical wings of different aspect ratio only, the graphs would be identical.

A

a. the gradient is shallower, which reduces the threat of excessive load factor in vertical gusts.

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10
Q

For a given aircraft if the weight is decreased, VMD will (i) and drag will (ii).

a. (i) remain the same (ii) increase

b. (i) remain the same (ii) decrease

c. (i) increase (ii) increase

d. (i) decrease (ii) decrease

A

d. (i) decrease (ii) decrease

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11
Q

If a pilot increases the flap setting in a climb, the stall speed will (i) and the climb angle will (ii).

a. (i) decrease (ii) increase

b. (i) decrease (ii) decrease

c. (i) increase (ii) decrease

d. (i) increase (ii) increase

A

d. (i) increase (ii) increase

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12
Q

Considering different configurations/ flap designs, which of the following would represent an order of increasing CD?

a. Plain, Slotted, Split, Clean

b. Plain, Clean, Slotted, Split

c. Clean, Split, Plain, Slotted

d. Clean, Slotted, Plain, Split

A

c. Clean, Split, Plain, Slotted

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13
Q

In the descent, speed brakes will
[ ] CL/CD ratio and
[ ] angle of descent.

[increase] [decrease]

A

In the descent, speed brakes will
[ decrease ] CL/CD ratio and
[ increase ] angle of descent.

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14
Q

Which statements is correct regarding a shockwave on a lift on a lift generating wing?

a. it is located at the position of the wing’s greatest thickness when the aeroplane reaches the speed of sound.

b. it reaches its highest intensity when flying at the critical Mach number.

c.it moves AFT and intensifies when an aileron is deflected downward.

d. it moves forward as the Mach number increases.

A

d. it moves forward as the Mach number increases.

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15
Q

In front of a normal shockwave compared to behind, the temperature is (i), the dynamic pressure is (ii) and the LSS is (iii):

a. (i) higher, (ii) higher, (iii) higher

b. (i) lower, (ii) lower, (iii) lower

c. (i) higher, (ii) lower, (iii) higher

d. (i) lower, (ii) higher, (iii) lower

A

c. (i) higher, (ii) lower, (iii) higher

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16
Q

The Critical Mach number:

a. is the lowest Mfs at which some of the flow is sonic.

b. is slower when the aircraft is lighter.

c. is faster when the wing is thicker.

d. occurs just past Mfs 1.0

A

a. is the lowest Mfs at which some of the flow is sonic.

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17
Q

A commercial jet transport is nearing its top of decent for its UK destination on a short haul flight from Central Europe.

During the initial decent the pilot will hold a constant (ii), the pitch angle will (ii), and the CL will (iii).

a. (i) CAS, (ii) remain the same, (iii) remain the same.

b. (i) Mach number (ii) decrease, (iii) increase.

c. (i) Mach number (ii) decrease, (iii) increase.

d. (i) Mach number (ii) decrease, (iii) decrease

A

d. (i) Mach number (ii) decrease, (iii) decrease

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18
Q

If VS1g is 78 knots, what is the stall speed in a 50 degrees Angle of Bank turn?

write the numerical number (in knots) to 2 significant figures

Answer [_____________]

A

97knots

1/cos(50) = 1.55
78 x √ 1.55/1
=97.10

19
Q

Considering stall speed, which of the following statements are correct/incorrect?

(i) the stall speed increases with increase in load factor and with forward movement of CG.

(ii) the stall speed decreases when flaps are retracted and aircraft mass decreases.

a. (i) incorrect, (ii) incorrect

b. (i) incorrect, (ii) correct

c. (i) correct, (ii) incorrect

d. (i) correct, (ii) correct

A

c. (i) correct, (ii) incorrect

20
Q

Considering the buffet free range, which of the following statements are correct or incorrect?

(i) the buffet range reduces as the CG moves AFT.

(ii) the buffet range increases as load factor reduces

(iii) the buffet range decreases as the pressure altitude increases.

a. (i) correct, (ii) correct, (iii) incorrect
b. (i) correct, (ii) incorrect, (iii) correct
c. (i) incorrect, (ii) correct, (iii) incorrect
d. (i) incorrect, (ii) correct, (iii) correct

A

d. (i) incorrect, (ii) correct, (iii) correct

21
Q

If VS for an aircraft in straight and level flight is 85knots, what is the percentage change in CL when the aircraft is at
147knots?

a. an increase of 77%
b. an increase of 32%
c. a decrease of 67%
d. a decrease of 33%

A

c. a decrease of 67%

22
Q

Which 3 factors listed below will cause an increase in stall speed?

a. a decrease in weight.
b. underslung engines compared to centreline engines.
c. extending slats
d. forward CG
e. turning
f. an AFT CG
g. ice on the wing
h. an increase in thrust

A

e. turning
d. forward CG
g. ice on the wing

23
Q

In a fully developed errect spin, an aircraft yawing (i) will roll (ii) and pitch (iii).

a. (i) left, (ii) left, (iii) up
b. (i) left, (ii) right, (iii) up
c. (i) right, (ii) left, (iii) down
d. (i) right, (ii) right (iii) down

A

a. (i) left, (ii) left, (iii) up

24
Q

graph pic

A
25
Q

What are the characteristics of a laminar boundary layer?

a. has high energy at its base.
b. shallow velocity gradient
c. 2-3mm deep
d. has low energy at its base
e. steep velocity gradient
f. a few centimetres deep

A

b. shallow velocity gradient
c. 2-3mm deep
d. has low energy at its base

26
Q

A stall warning system which uses a flapper switch will active when:

a. the stagnation point moves below it.
b. the separation point moves in front of it.
c. the separation point moves behind it.
d. the stagnation point moves above it.

A

b. the separation point moves in front of it.

27
Q

Which of the following options would reduce the tendency of the aircraft to suffer from Dutch Roll?

a. increase the wing sweep angle.

b. increase the wing dihedral angle.

c. fly at higher altitude

d. move the CG forward

A

b. increase the wing dihedral angle.

28
Q

For acceptable longitudinal stability the CG must be:

a. forward of the neutral point by at least the static margin.

b. AFT of the neutral point by at least the static margin.

c. forward of the neutral point by less than the static margin.

d. AFT of the neutral point by no more than the static margin.

A

a. forward of the neutral point by at least the static margin.

29
Q

An aeroplane has static directional and lateral stability. if due to sideslip the airflow approaches from the left of the nose, the aeroplane will:

a. roll right and yaw right.
b. roll right and yaw left.
c. roll left and yaw right.
d. roll left and yaw left.

A

b. roll right and yaw left.

30
Q

If dynamic stability of an aircraft was neutral, the static stability:

a. could have been neutral or positive.
b. must be neutral.
c. must be positive.
d. could have been neutral, positive or negative.

A

a. could have been neutral or positive.

31
Q

To trim an aircraft for a slower speed in straight and level flight, the trim wheel should be rotated [ ] causing the trim tab to move [ ] which will hold the elevator [ ].

[up] [down] [forward] [backward?]

A

To trim an aircraft for a slower speed in straight and level flight, the trim wheel should be rotated [ backwards? ] causing the trim tab to move [ down ] which will hold the elevator [ up ].

32
Q

For a CAT swept wing aircraft, which of the following statements is correct regarding spoilers and ailerons?

a. flying on the approach with first stage of flaps extended, the outboard ailerons will be active and the spoilers could be used as speed brakes.

b. in the climb at mid latitudes both the inboard and outboard ailerons will be active.

c. following a decompression at hight altitude, flaps and spoilers should be used to increase the drag.

d. turning in the cruise, the spoiler yaws the aircraft with no effect on lift.

A

a. flying on the approach with first stage of flaps extended, the outboard ailerons will be active and the spoilers could be used as speed brakes.

33
Q

Which of the following devices ALL reduce the load on the pilot during a control surface deflection?

a. a spring tab, an anti-balance tab and a servo tab.

b. a inset hinge, a mass balance and an internal balance.

c. a trim tab, a balance tab and an inset hinge.

d.a balance tab, a servo tab and a horn balance.

A

d.a balance tab, a servo tab and a horn balance.

34
Q

Which of these statements about the gust load factor on an aeroplane are correct or incorrect?

  1. when wing sweepback increases the gust load factor decreases.
  2. when IAS increases, the gust load factor increases.

a. (1) is incorrect, (2) is correct
b. (1) is correct, (2) is incorrect
c. (1) is incorrect, (2) is incorrect
d. (1) is correct, (2) is correct.

A

a. (1) is incorrect, (2) is correct

35
Q

Which of the following statements about Vc is correct?

a. it must be no greater than 0.6VD and provide a minimum specified speed margin between VC and VD.

b. it must be no greater than 0.6B and provide a minimum specified speed margin between VC and VB.

c. it must be no greater than 0.8VD and provide a minimum specified speed margin between VC and VD.

d. it must be no greater than 0.7VB and provide a mimic specified speed margin between VC and VA.

A

c. it must be no greater than 0.8VD and provide a minimum specified speed margin between VC and VD.

36
Q

VA for a crop duster (utility category) is published as 153knots. What is the 1g stall speed?

write the numerical answer (in knots) to the nearest whole number.

[_____________]

A

73 knots

153x √ 1/4.4
=7.3​

37
Q

Propeller efficiency:

a. increases and then decreases as flight speed increases from slow to fast flight for an aeroplane with a fixed pitch propeller.

b. is constant over a wide range of speeds for a fixed pitch propeller.

c. is the ratio of propeller blade frontal area to the area of the propeller disc.

d. is the ratio of the shaft power to the output propeller power.

A

a. increases and then decreases as flight speed increases from slow to fast flight for an aeroplane with a fixed pitch propeller.

38
Q

Which of the following statements are true for a fixed pitch propeller?

pick all correct answers

a. the blade angle of attack increases as the propeller RPM decreases.

b. the blade angle of attack reduces as the aircraft’s TAS increases.

c. they preserve propeller efficiency over a wide range of airspeeds.

d. they are mechanically simple.

A

b. the blade angle of attack reduces as the aircraft’s TAS increases.

39
Q

The effective pitch is:

a. is the pitch that perseveres an optimum angle of attack by altering the blade pitch angle.

b. the distance a propeller would travel in one revolution if it was moving through the air at the blade angle.

c. the distance the propeller actually moves forward in one revolution.

d. is the same as fine pitch.

A

c. the distance the propeller actually moves forward in one revolution.

40
Q

A tailwind aeroplane which has an anticlockwise rotating propeller (when viewed from the cockpit). During the takeoff roll when the pilot pushes forward on the controls to lift the tailwheel, the aeroplane will:

a. yaw right due to gyroscopic effect.

b. yaw right due to increasing asymmetric blade effect.

c. yaw left due to asymmetric blade effect and torque reaction.

d. yaw left due to slipstream and torque reaction effects.

A

d. yaw left due to slipstream and torque reaction effects.

41
Q

An aeroplane is taking off from a high elevation airport. What would be the effect on VMCG and VMCA?

a. both VMCG and VMCA will decrease.

b. VMCG will decrease as this is based on ground speed and VMCA will increase.

c. Both VMCG and VMCA will increase.

d. VMCG and VMCA will not be affected, because these V speeds are IAS which is not affected by changes in air density.

A

b. VMCG will decrease as this is based on ground speed and VMCA will increase.

42
Q

A twin engined aeroplane has a lift:drag ratio of 19:1. If the mass is 52,700kg and the thrust per engine is 43,800N. What is the one-engine inoperative percentage climb gradient?

(assume g=10m/s2)

a. 3.0%
b. 11.4%
c. 7.9%
d. 16.9%

A

a. 3.0%

43
Q

A single engine piston aircraft is flying a navigation exercise at 4,500ft AMSL.
The lift/drag ratio is 11:1. The glide TAS is 75knots and the elevation is 800ft. What is the glide range over the ground given a 10knots headwind?

write the numerical answer (in NGM) to one decimal place.

[_________________]

A

715?

44
Q

Regarding aircraft performance in a glade, an increase in headwind will
[ ] the maximum endurance and a decrease in madd will [ ] the maximum endurance.

A

[decrease]

[increase]

maybe

45
Q

An aircraft with a mass of 65,000kg is flying a turn at a TAS of 215knots, with a 37 degrees angle of bank.

What is the load factor experienced and the rate of turn (in degrees per second) respectively? assume g=10m/s2

a. 1.33 and 7.4

b. 1.33 and 0.065

c. 1.25 and 4.7

d. 1.25 and 3.9

A

d. 1.25 and 3.9

sf final (4 decks)

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