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sfc - satm > Ch 2: Straight and Level > Flashcards

Ch 2: Straight and Level Flashcards

1
Q

Ch 1 Rev: RAF acts …… to aeroplane’s flight path (Pg 9)

A

Parallel and opposite

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2
Q

Ch 1 Rev: Curvature of aerofoil is called … (Pg 9)

A

Camber

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3
Q

Ch 1 Rev: Difference between Chord line and RAF is… (Pg 9)

A

Angle of Attack (AoA)

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4
Q

Ch 1 Rev: Centre of Gravity is point at which … acts through (Pg 9)

A

Gravity

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5
Q

Chord Line (Pg 21)

A

Direct line from leading edge to trailing edge of wing

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6
Q

Mean Camber (Pg 21)

A

Line running from leading to trailing edge equally between upper and lower surfaces

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7
Q

Centre of Pressure (CoP)

A

Point where lift is considered to act through

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8
Q

Aeroplane is straight and level when… (Pg 21)

A

Maintains constant heading (direction), Constant Altitude, at Constant Airspeed whilst in balance
/ State of Equilibrium

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9
Q

4 Forces acting in aeroplane in flight… (Pg 21)

A

Lift, Weight, Thrust, Drag

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10
Q

Lift… (Pg 21)

A

Acting through Centre of Pressure (CoP) perpendicular to RAF

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11
Q

Weight… (Pg 21)

A

Acts through Centre of Gravity (CoG) towards centre of Earth

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12
Q

Thrust… (Pg 21)

A

Acts parallel to engine crankshaft, counteracts drag

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13
Q

Drag… (Pg 21)

A

Acts opposite to direction of motion

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14
Q

Lift balances… (Pg 21)

A

Weight

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15
Q

Thrust balances… (Pg 21)

A

Drag

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16
Q

Couples of opposing forces are… (Pg 21)

A

Pair of parallel opposing forces that do not act through the same point, –> causing tendency to rotate

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17
Q

Thrust/Drag couple causes… (Pg 21)

A

Nose-up tendency

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18
Q

Lift/Weight couple causes… (Pg 21)

A

Nose-down tendency

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19
Q

Bernoulli’s Principle (Pg 22)

A

Airflow below has reduced velocity = increased static pressure, airflow above has increased velocity = decreased static pressure

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20
Q

Engineer’s Lift form. (Pg 23)

A

Mathematical eqn for how lift is achieved

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21
Q

Lift = (CL)(1/2)(P)(V∧2)(S) (Pg 23)

A

CL = Coefficient of Lift, made of Camber and AoA
P = Greek letter for Air Density
V = Velocity/True Airspeed (TAS)
S = SA of wing

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22
Q

Pilot’s Lift form. (Pg 23)

A

2 options for altering lift; AoA and (Indicated Airspeed) IAS

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23
Q

Lift = AoA ∝ IAS (Pg 23)

A

Relationship is inversely proportional

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24
Q

Weight: CoG is… (Pg 23)

A

Point at which all weight of aeroplane is concentrated

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25
Q

Lift = Weight in… (Pg 23)

A

Stabilised Level flight

26
Q

Thrust must be greater than … to continue accelerating (Pg 24)

A

Drag

27
Q

In balanced, level flight at constant airspeed, …. must be equal (Pg 24)

A

Thrust and Drag

28
Q

Total drag is made of… (Pg 24)

A

Induced Drag, Parasite Drag

29
Q

Induced drag: (Pg 24)

A

Result of production of lift, prominent at low airspeeds

30
Q

Parasite drag: (Pg 24)

A

Caused by moving solid object through fluid medium

31
Q

Parasite drag = further broken into… (Pg 24)

A

Form Drag, Skin Friction Drag, Interference Drag

32
Q

Form drag… (Pg 24)

A

Caused by air having to move out of way as aeroplane moves forward

33
Q

Skin Friction drag is… (Pg 24)

A

Caused by air sticking to surface of aeroplane as it moves,
Rough surfaces cause boundary layer to thicken and stops air from flowing smoothly (reduced laminar flow)

34
Q

Define Laminar Flow (Pg 24)

A

Movement of particles in smooth path

35
Q

Interference drag is… (Pg 24)

A

When 2 moving airflows meet from different directions or at an angle.

36
Q

Power is… (Pg 25)

A

Rate of doing work, the product of force applied and the resultant velocity

37
Q

Work done is … (Pg 25)

A

Work is done by applying force over a distance

38
Q

Forces to use for power are… (Pg 25)

A

Thrust and Drag

39
Q

Thrust to power… (Pg 25)

A

Power available or ability to do work

40
Q

Drag to power… (Pg 25)

A

Power required or work to be done

41
Q

Power available eqn… (Pg 25)

A

Power Available = Thrust x TAS (True Aispeed)

42
Q

Power required eqn… (Pg 25)

A

Power Required = Drag x TAS (True Airspeed)

43
Q

Static Stability is… (Pg 25)

A

Describes aeroplane’s tendency to return to its original condition

44
Q

Dynamic Stability is… (Pg 25)

A

Concerned with motion of aeroplane after the disturbing force has been removed, and its ability to dampen out any oscillations over time

45
Q

Lateral Stability is… (Pg 26)

A

Displayed along the longitudinal axis, wings tend to return to wings-level attitude after being displaced

46
Q

Longitudinal Stability is… (Pg 26)

A

Displayed along the Lateral axis …….

47
Q

Directional Stability is… (Pg 26)

A

Displayed along Normal axis, when yaws will act to restore aeroplane to original flight path & realign with RAF

48
Q

To achieve Straight and Level flight use… (Pg 27)

A

Power + Attitude = Performance

49
Q

PA28-161 Warrior; PAST NORMAL cruise (Pg 27):

A

P - 2400-2450RPM, A - 1/3 Ground, S - 105Kts, Trim and Balance

50
Q

PA28-161 Warrior; PAST FAST cruise (Pg 27):

A

P - 2500RPM, A - Slightly lower than NC, S - 110Kts, Trim and Balance, All power below 2000RPM = Carby Heat FULL ON

51
Q

PA28-161 Warrior; PAST SLOW cruise (Pg 27):

A

P - 1900RPM, A - Nose on horizon, S - 75Kts, Trim and Balance, All power below 2000RPM = Carby Heat FULL ON

52
Q

PA28-161 Warrior; PAST SAFE Slow cruise (Pg 27):

A

P - 2100RPM, A - 1/3 Ground, S - 70Kts (+ 2 stages flaps), Trim and Balance, All power below 2000RPM = Carby Heat FULL ON

53
Q

PA28-161 Warrior; PAST FAST cruise (Pg 27):

A

P - 2500RPM, A - Slightly lower than NC, S - 110Kts, Trim and Balance, All power below 2000RPM = Carby Heat FULL ON

54
Q

PA28-181 Archer; PAST NORMAL cruise (Pg 27):

A

P - 2350-2400RPM, A - 1/3 Ground, S - 110Kts, Trim and Balance, All power below 2000RPM = Carby Heat FULL ON AS REQUIRED

55
Q

PA28-181 Archer; PAST FAST cruise (Pg 27):

A

P - 2500RPM, A - Slightly lower the NC, S - 115Kts, Trim and Balance, All power below 2000RPM = Carby Heat FULL ON AS REQUIRED

56
Q

PA28-181 Archer; PAST SLOW cruise (Pg 27):

A

P - 1900RPM, A - Nose on Horizon, S - 80Kts, Trim and Balance, All power below 2000RPM = Carby Heat FULL ON AS REQUIRED

57
Q

PA28-181 Archer; PAST SAFE Slow cruise (Pg 27):

A

P - 2100RPM, A - 1/3 Ground, S - 75Kts (+ 2 stages flaps), Trim and Balance, All power below 2000RPM = Carby Heat FULL ON AS REQUIRED

58
Q

Entry use… (Pg 27)

A

PAST procedure

59
Q

Work cycle use… (Pg 28)

A

ALAP Cycle, Attitude-Lookout-Attitude-Performance

60
Q

Correction Cycle use… (Pg 28)

A

CCHAT Cycle, Change-Check-Hold-Adjust-Trim

61
Q

Transition/Exit use… (Pg 29)

A

PAST Procedure

sfc - satm (12 decks)

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