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EASA Principle of Flight > Lecture notes > Flashcards

Lecture notes Flashcards

1
Q

Transition point

A

The point at which the laminar boundary layers changes to trubulent boundary layer (NOT SPERATING FROM SURFACE)

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2
Q

IAS
CAS
EAS
TAS

A

EAS = CAS corrected for compressibility error

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3
Q

Drag foruma

A

Cd * 1/2 * p * V^2 * S

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4
Q

Doubling the speed will:
1. double
2. quadruple
the lift and drag

A

Quadruple. Because it is v^2

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5
Q

What is D0

A

Zero lift drag

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6
Q

What is Di

A

Induced drag

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7
Q

Trim drag

A

Drag coming from other control surfaces such the elevators

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8
Q

More lift = ____ Drag

A

More induced

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9
Q

The airflow above the wing (low pressure) will move towards
1. Wing root
2. Wing tip

A

Wing root

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10
Q

THe airflow below the wing will move towards
1. Wing root
2. Wing tip

A

Wing tip

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11
Q

As angle of attack increases, the induced drag

A

Increases.
Because angle of attack increase = lift increase.
Lift icnrease = Di increase

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12
Q

Low airspeed = ____ induced drag

A

High.
Low airspeed = high angle of attack
High angle of attack = high induced drag

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13
Q

Induced drag is _____ porportional to V^2
1. Directly
2. Inversly

A

Inversly

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14
Q

Washout

A

The wing is twisted. AoA at the wing tip is lower than root.

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15
Q

Washout has: _______ vortices, _____ induced drag

A

Less, lower

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16
Q

Total drag = ____ + ____

A

Zero lift drag (parasite) + induced drag

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17
Q

More weight means _____ total drag

A

More.
More weight = More lift
More lfit = More induced drag

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18
Q

Vmd

A

Minimum drag speed (Di = D0)

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19
Q

When on ground effect, the upwash ___ and downwash _____

A

increases, descreases.

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20
Q

When on ground effect, the upwash ___ and downwash _____ creating ___ lift and ____ drag

A

More lift, more drag

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21
Q

Since on ground effect more lift is created, we can lift at ______ AoA

A

lower

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22
Q

Remember

A

graph

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23
Q

More weight / more load factor, ____ wing tip vortices

A

More

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24
Q

As flaps lowered, CP moves

A

aft

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25
Q

As flaps lowered ,the stalling AoA

A

decreases

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26
Q

Taper wing _____ vortices, with _____ induced drag

A

reduce, less

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27
Q

More weight & load factor, ______ vortex

A

More

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28
Q

More weight will require _____ lift,
So that means vortex is _____ with _____ AoA

A

More, increased, more

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29
Q

Vortex intensity _______ with higher TAS

A

Reduces

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30
Q

Buffet

A

The disturbed wake flow from the wing hits the tailplane and causes it to shake

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31
Q

As flaps lowered, the stalling angle of attack

A

Decreases

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32
Q

3 Modifications to avoid wing tip stall (wing root stall is preferable)

A
  • Washout (lower angle of attack at the tip)
  • Vortex generators
  • Stalling strip (Forces stall to begin at root)
33
Q

More weight will ______ stall speed

A

Increase

34
Q

Stall speed foruma by changing wieghts:
(Old V) * SQAUREROOT(New weight / old weight)

A

remember for test in cats

35
Q

Lower weight / lower load factor will _______ stall speed

A

decrease

36
Q

Manouevres will ______ load factor

A

increase

37
Q

When weight increases, wing loading ____

A

increases

38
Q

Slipping turn is the nose turns _____ of the turn,
Skidding turn is the nose turns _____ of the turn

A

outside,
inside

39
Q

On climb, the _____ wing stalls first

A

Outer

40
Q

On descent, the _____ wing stalls first

A

Inner

41
Q

Swept wing

A

A swept wing is a wing that angles either backward or occasionally forward from its root rather than in a straight sideways direction.

42
Q

Autorotation

A

autorotation is the tendency of an aircraft in or near a stall to roll spontaneously to the right or left, leading to a spin

43
Q

Spin recovery

A

Reduce power
Ailerons neutral
Full opoosite rudder

44
Q

Slots and slats task

A

Allowing air from under the wing to flow over upper surface and delay separation

45
Q

Using flaps on take off ______ ground roll and lift-off speed,
also _______ climb gradient

A

Reduces reduces

46
Q

More moment arm, ______ actual force in _____ applied force

A

more, less

47
Q

Since longer moment arm is more effective, the controls are _____

A

hinged

48
Q

With a fwd CG, stick force is _____

A

high

49
Q

When stick force is _____ the aircraft is _____ to manoeuvre

A

High, harder

50
Q

If flight control is hinged at its leading edge, ____ stick force required

A

more

51
Q

Horn balance

A

Portion of the control surface acts ahead of the hinge line

52
Q

Inset hinge

A

Hinge is a bit more into the control surface, reducing the moment

53
Q

Balance tab

A

Deflects in the direciton opposite to the eleavtor deflection

54
Q

Anti-balance taab

A

Can be found on all-flying tailplane, since the tail is more sensistive

55
Q

Control flutter

A

A vibraiton caused by pressure distribution over a control surface

56
Q

To prevent control flutter, the CG of the control surface should be

A

On and or ahead the hingle line

57
Q

Adverse yaw

A

Tendenacy of the aircraft to yaw to the opposite direction because of differential aileron drag

58
Q

Differantial ailerons and frise ailerons cause _____ drag on the ______ wing to reduce adverse yaw

A

increased, desceding

59
Q

Rudder coupled ailerons

A

When the aircraft is banked, the rudder automatically deflects the yaw into the turn

60
Q

Static stability

A

The capability of the body to return to its original position

61
Q

Dynamic stability

A

Describes the subsequent reaction

62
Q

Positive dynamic stability

A

When a body returns to its original position through oscillations of decreasing amplitude

63
Q

Neutral dyamic stability

A

When oscillations continue without a change in amplitude

64
Q

Negative dynamic stability

A

When oscillations increase in amplitude

65
Q

Positive static stability

A

A body returns to its previous condition after disturbance

66
Q

Neutral static stability

A

A body maintains its new positions after a disturbance

67
Q

Negative static stability

A

A body continues to move aay from its previous condition after a disturbance

68
Q

Keel surface behind the CG have a stable/unstable influence

A

stable

69
Q

Swept wings _____ direcitonal stability as the wing with more of its span exposed to the airflow has _______ drag

A

Increase, more

70
Q

Dihedral helps ______ stability

A

Lateral

71
Q

A high wing ____ lateral stability

A

increases

72
Q

Propeller slipstream will have a ______ effect during a sideslip

A

Destabilising

73
Q

Flaps will have _____ lateral stability

A

Less

74
Q

Spiral instability occurs when the _____ stability is greater than _____ stability

A

Directional stability, lateral stability

75
Q

Vertical component of gust hits the airplane, causing ____ AoA, and in other words:

A

More AoA, more lift, more load factor

76
Q

Torque

A

Resistance to rotation

77
Q

Angle of advance (helix)

A

The angle between the relative airflow and rotational velocity, relates to TAS

78
Q

Blade angle is changed throughout the blade to

A

Have an equal amount of “lift” generated at each blade section

EASA Principle of Flight (6 decks)

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