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ATPLs > PoF > Flashcards

PoF Flashcards

1
Q

Parasite drag =

A

Skin friction drag + form drag + interference drag

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2
Q

Profile drag =

A

Skin friction drag + form drag

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3
Q

Skin friction drag =

A

Airflow causing friction over the wing

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4
Q

What worsens skin friction drag

A

Wing contamination

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5
Q

Form drag =

A

Pressure differential between leading & trailing edge (pressure at leading edge higher than trailing)
Aerodynamic force of high to low PG acts against direction of flight

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6
Q

Is Q (IAS) proportional to form drag

A

Yes

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7
Q

What happens to form drag when:
1) AOA increases?
2) Vortex generators are installed?

A

1) form drag increases
2) form drag decreases

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8
Q

How to minimise parasite drag? (4)

A
  • Streamlining
  • Incorporating fillets & fairings
  • Using laminar flow wing sections
  • Minimising frontal area
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9
Q

Induced drag =

A

Span-wise flow causing wing tip vortices

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10
Q

Higher CL or lower IAS affects Induced drag how?

A

Stronger wing tip vortices

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11
Q

What do wing tip vortices cause?

A

Stronger downwash = rearward inclined wing lift = greater induced drag

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12
Q

What happens to induced drag when:
1) lift increases?
2) weight increases?
3) load factor (g) increases?
4) speed increases?
5) aspect ratio increases?

A

1) induced drag increases
2) induced drag increases
3) induced drag increases
4) induced drag decreases
5) induced drag decreases

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13
Q

What is the CDi equation?

A

CDi = CL² ÷ AR

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14
Q

How to minimise induced drag? (3)

A
  • High AR
  • Tapered wing Planform with wing twist & span-wise camber variation
  • Using end plates, tip-tanks, winglets or tip shaping
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15
Q

Gravity =

A

9.81 m/s²

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16
Q

Is air density proportional to TAS?

A

No (inversely proportional)

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17
Q

What happens to air density when:
1) Temp. increases?
2) Static pressure increases?
3) Humidity increases?
4) Alt. increases?

A

1) air density decreases
2) air density increases
3) air density decreases
4) air density decreases

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18
Q

A plane is rolling right, which aileron is down?

A

Left aileron down

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19
Q

What camber does the horizontal stabiliser have?

A

Negative

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20
Q

1 metre = how many ft?

A

3.28ft

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21
Q

How many ft in a statue mile?

A

5280ft

22
Q

How many ft in a NM?

A

6080ft

23
Q

How many kts per m/s?

A

2

24
Q

How to calculate °Kelvin?

A

°C + 273

25
Q

How to calculate °F?

A

(⁹/⁵ × °C) + 32

26
Q

How many lbs in a kg?

A

2.205

27
Q

What is the sweep angle?

A

Angle between the 25% chord line & the line perpendicular to the root chord

28
Q

What happens when entering ground effect?

A
  • Lift increases
  • Induced drag decreases
  • Tailplane æ modified so that less downforce is created = pitch down moment
  • ASI & altimeter under-read
29
Q

Where is the AC on a wing?

A

¼ chord position at < Mach 0.4

30
Q

Taper ratio =

A

Tip chord ÷ root chord

31
Q

Mean geometric chord =

A

Wing area ÷ wing span

32
Q

Aspect ratio =

A

Wing span ² ÷ wing area

33
Q

Lift equation?

A

L = ½ p V² S CL

34
Q

Lift equation where CL is sought?

A

CL = L ÷ (½ p V² S)

35
Q

Dynamic pressure=

A

½ p V²

36
Q

What is the relationship between IAS & dynamic pressure?

A

IAS is proportional to √dynamic pressure

37
Q

CLMAX =

A

1 ÷ Vs²

38
Q

VS1g (new) =

A

VS1g (old) × √(new weight ÷ old weight)

39
Q

New VA ÷ old VA =

A

√CL old ÷ CL new

40
Q

What’s the relationship between new and old load factors (n) and old and new speeds (V)

A

N(new) ÷ n(old) proportional to V²new ÷ V²old

41
Q

Load factor (n) =

A

Lift ÷ Weight

42
Q

n∆ =

A

Vnew² ÷ Vold²

43
Q

Bernoulli’s theorem =

A

P + ½ p V² = K

Pressure + kinetic energy (dynamic pressure) = constant

44
Q

Pressure (Pa) =

A

Force (N) ÷ Area (m²)

45
Q

Lift & drag depend on? (4)

A
  • AoA
  • Aerofoil thickness & camber
  • Air density
  • Velocity
46
Q

What is the best L/D ratio known as?

A

Optimum AoA

47
Q

Will a change of weight in a given config. change L/D max?

A

No

48
Q

An AoA other than optimum AoA will cause what with regards to the L/D ratio?

A

More drag for lift required

49
Q

Mach No. =

A

TAS ÷ LSS

50
Q

LSS =

A

38.96 × √absokute temp. (K)

51
Q

Thrust =

A

T = D + W sin(gamma)

D = drag, W = weight, Gamma = angle between weight & opposite to lift in a climb

52
Q

Limit load factors:
1) CS-25?
2) Normal CS-23?
3) Utility CS-23?
4) Aerobatic CS-23?

A

1) -1g to +2.5g
2) -1.52g to +3.8g
3) -1.76g to +4.4g
4) -3g to +6g

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