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EASA Principle of Flight > Lecture notes > Flashcards

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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
As flaps lowered ,the stalling AoA
decreases
26
Taper wing _____ vortices, with _____ induced drag
reduce, less
27
More weight & load factor, ______ vortex
More
28
More weight will require _____ lift, So that means vortex is _____ with _____ AoA
More, increased, more
29
Vortex intensity _______ with higher TAS
Reduces
30
Buffet
The disturbed wake flow from the wing hits the tailplane and causes it to shake
31
As flaps lowered, the stalling angle of attack
Decreases
32
3 Modifications to avoid wing tip stall (wing root stall is preferable)
- Washout (lower angle of attack at the tip) - Vortex generators - Stalling strip (Forces stall to begin at root)
33
More weight will ______ stall speed
Increase
34
Stall speed foruma by changing wieghts: (Old V) * SQAUREROOT(New weight / old weight)
remember for test in cats
35
Lower weight / lower load factor will _______ stall speed
decrease
36
Manouevres will ______ load factor
increase
37
When weight increases, wing loading ____
increases
38
Slipping turn is the nose turns _____ of the turn, Skidding turn is the nose turns _____ of the turn
outside, inside
39
On climb, the _____ wing stalls first
Outer
40
On descent, the _____ wing stalls first
Inner
41
Swept wing
A swept wing is a wing that angles either backward or occasionally forward from its root rather than in a straight sideways direction.
42
Autorotation
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
Spin recovery
Reduce power Ailerons neutral Full opoosite rudder
44
Slots and slats task
Allowing air from under the wing to flow over upper surface and delay separation
45
Using flaps on take off ______ ground roll and lift-off speed, also _______ climb gradient
Reduces reduces
46
More moment arm, ______ actual force in _____ applied force
more, less
47
Since longer moment arm is more effective, the controls are _____
hinged
48
With a fwd CG, stick force is _____
high
49
When stick force is _____ the aircraft is _____ to manoeuvre
High, harder
50
If flight control is hinged at its leading edge, ____ stick force required
more
51
Horn balance
Portion of the control surface acts ahead of the hinge line
52
Inset hinge
Hinge is a bit more into the control surface, reducing the moment
53
Balance tab
Deflects in the direciton opposite to the eleavtor deflection
54
Anti-balance taab
Can be found on all-flying tailplane, since the tail is more sensistive
55
Control flutter
A vibraiton caused by pressure distribution over a control surface
56
To prevent control flutter, the CG of the control surface should be
On and or ahead the hingle line
57
Adverse yaw
Tendenacy of the aircraft to yaw to the opposite direction because of differential aileron drag
58
Differantial ailerons and frise ailerons cause _____ drag on the ______ wing to reduce adverse yaw
increased, desceding
59
Rudder coupled ailerons
When the aircraft is banked, the rudder automatically deflects the yaw into the turn
60
Static stability
The capability of the body to return to its original position
61
Dynamic stability
Describes the subsequent reaction
62
Positive dynamic stability
When a body returns to its original position through oscillations of decreasing amplitude
63
Neutral dyamic stability
When oscillations continue without a change in amplitude
64
Negative dynamic stability
When oscillations increase in amplitude
65
Positive static stability
A body returns to its previous condition after disturbance
66
Neutral static stability
A body maintains its new positions after a disturbance
67
Negative static stability
A body continues to move aay from its previous condition after a disturbance
68
Keel surface behind the CG have a stable/unstable influence
stable
69
Swept wings _____ direcitonal stability as the wing with more of its span exposed to the airflow has _______ drag
Increase, more
70
Dihedral helps ______ stability
Lateral
71
A high wing ____ lateral stability
increases
72
Propeller slipstream will have a ______ effect during a sideslip
Destabilising
73
Flaps will have _____ lateral stability
Less
74
Spiral instability occurs when the _____ stability is greater than _____ stability
Directional stability, lateral stability
75
Vertical component of gust hits the airplane, causing ____ AoA, and in other words:
More AoA, more lift, more load factor
76
Torque
Resistance to rotation
77
Angle of advance (helix)
The angle between the relative airflow and rotational velocity, relates to TAS
78
Blade angle is changed throughout the blade to
Have an equal amount of "lift" generated at each blade section

EASA Principle of Flight (6 decks)

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