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PPL (A) > Aerodynamics 1 > Flashcards

Aerodynamics 1 Flashcards

1
Q

What are the three types of motion an aircraft is capable of?

A

Pitch

Roll

Yaw

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2
Q

What are three axis of motion that an aircraft move about?

A

Lateral axis - pitch

Longitudinal axis - roll

Normal axis (vertical axis) - yaw

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3
Q

What are the 3 primary flight controls of an aircraft?

A

Elevator - lateral axis - pitch

Ailerons - longitudinal axis - roll

Rudder - normal axis - yaw

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4
Q

What is the common point on an aircraft where all three axis intersect?

A

Centre of Gravity (CoG)

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5
Q

The elevator(s) initiates or prevents which motion/ action?

A

Pitching - nose up/ nose down attitude

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6
Q

The aileron(s) initiate or prevent which motion (action)?

A

Rolling

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7
Q

Changes in aircraft attitude are assessed from where?

A

The top of the instrument panel

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8
Q

What is the outcome of pulling back on the control column?

A

Pitch Up / Nose Up / Climb

Elevators deflect upward and consequently the airflow is deflected upward which imposes a downward force on the tail.

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9
Q

What is the outcome of pushing forward on the control column?

A

Pitch Down / Nose Down / Descend

Elevators deflect downward and consequently the airflow is deflected downward which imposes an upwards force on the tail

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10
Q

What is the outcome of turning the control column right?

A

Turn right / bank right

The right aileron deflects upward whilst the left aileron deflects downward

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11
Q

If an aileron is deflected downward, which direction will the aircraft turn/ bank?

A

Turn/ bank toward the opposite wing side

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12
Q

What is the outcome of turning the control column to the left?

A

Turn left / bank left

The left aileron deflects upward whilst the right aileron deflects downward

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13
Q

The rudders are connected to which control instruments?

A

The pedals

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14
Q

What is the outcome of pressing the left pedal forward/ in?

A

Yaw to the left

The rudder is deflected to the left, airflow passing over the rudder deflects to the left which pushes the tail to the right

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15
Q

What is the outcome of pressing the right pedal forward/ in?

A

Yaw to the right

The rudder is deflected to the right, airflow passing over the rudder deflects to the right which pushes the tail to the left

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16
Q

What is a secondary/ further effect of a roll?

A

Yaw in the direction of the turn/ bank

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17
Q

What is a secondary / further effect of a yaw?

A

A roll in the direction of the yaw

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18
Q

What is a dangerous consequence of the roll-yaw relationship?

A

A spiral dive

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19
Q

How can you recover from a spiral dive?

A
  1. Reduce power
  2. Gently level the wings
  3. Gently nose up the attitude
  4. Reapply power
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20
Q

When rolling and yawing to the left, which wing will cover a greater distance and at greater speed?

A

The right wing (outside wing)

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21
Q

When rolling and yawing to the right, which wing will cover a greater distance and at greater speed?

A

The left wing (outside wing)

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22
Q

What 3 factors determine the strength and effectiveness of a control input?

A
  1. Area of control surface
  2. The angle at which the control surface is deflected
  3. The speed of the passing airflow
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23
Q

What are the only 2 factors/ variables that a pilot has control over with regards to a control input?

A
  1. Deflection of the control surface
  2. Speed of the aircraft - speed of airflow passing over the control surface

A pilot can obviously not change the area of the control surface

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24
Q

What is the special effect produced when climbing with high engine power and low forward speed?

A

A propeller slipstream

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25
Q

Which 2 controls become more effective when exposed to a propeller slipstream?

A

The elevators and the rudder

The ailerons are outside the influence of the propeller slipstream

26
Q

When operating at lower speed, will the pilot feel greater or lesser resistance on the controls?

A

Greater resistance

27
Q

When operating at higher speed, will the pilot feel greater or lesser resistance on the controls?

A

Lesser

28
Q

Is a larger or smaller degree of deflection of the control surface(s) required when operating at low air speeds to achieve a particular pitch, roll or yaw?

A

Larger

29
Q

Is a larger or smaller degree of deflection of the control surface(s) required when operating at high air speeds to achieve a particular pitch, roll or yaw?

A

Smaller

30
Q

In aviation, what unit of measurement to express speed?

A

Kts/ hr

knots per hour = nautical miles per hours

31
Q

For the purpose of expressing runway dimensions and meteorological visibility, what unit of measurement is used?

A

m or kms

Metres of kilometres

32
Q

1 nautical mile (1nm) is equivalent to what?

A

1 knot

1 minute of latitude

1.85km / 1852m

6080ft

33
Q

What is the atmospheric pressure at sea level?

A
  1. 2 Hpa
  2. 92 inch/hg
  3. 00 mm/Hg
  4. 7 lbs/ inch^2
34
Q

What is the conversion for Temp degrees C and Temp degrees F?

A

Celsius = Subtract 32 and multiply by 0.555

F = Multiply by 1.8 and add 32

35
Q

What is the conversion for weight/ mass?

A 
Kgs = Lbs divide 2.2
Lbs = kgs multiply 2.2
36
Q

What is the conversion for volume?

A

Litres = US Gallons x 3.8

US Gallons = Litres divide 3.8

37
Q

Sustained level flight is possible due to a force that is equal and opposite to the weight of the aircraft. What is this force referred to as?

A

Lift

38
Q

If the force of lift changes to become less that than weight of the aircraft, will the aircraft climb, descend or remain in level flight?

A

The aircraft will descend

39
Q

Is the direction of the relative airflow always equal to or opposite to the direction of the motion?

A

Relative airflow is always opposite to the motion of the aircraft

40
Q

Is relative airflow equal to the IAS, GAS or TAS?

A

Relative airflow is always equal to the aircraft’s True Airspeed (TAS)

41
Q

On an aerofoil, the straight line joining the leading and trailing edge is called what?

A

The Chord Line

42
Q

The angle formed between the chord line of an aerofoil (wing) and the relative airflow is referred to as what?

A

The Angle of Attack (AoA)

43
Q

True or False - The mean camber line is an equidistant line drawn from the leading edge to the trailing edge of an aerofoil (wing)?

A

True

44
Q

Does the maximum camber on an aerofoil (wing) occur at the point of greatest or least separation between the mean camber line and the chord line?

A

The point of greatest separation

45
Q

How does lift and drag act in relation to relative airflow?

A

Lift acts at a right angle to the direction of the relative airflow.

Drag acts parallel to the direction of the relative airflow.

46
Q

What is the force that is a resultant of lift and drag?

A

Total Reaction

47
Q

What is the name of the point on the aerofoil (wing) where all forces are evenly distributed?

A

The Centre of Pressure (CoP)

48
Q

Is the CoP a fixed or moving point on the aerofoil?

A

The CoP moves in response to a changing AoA

49
Q

During normal flight, does the CoP move toward the leading edge or toward the trailing edge as AoA is increased?

A

The CoP moves toward the leading edge as AoA is increased

50
Q

What is the name of the angle produced on an aerofoil (wing) whereby the maximum possible lift is produced for a given airspeed?

A

The Critical or Stalling Angle

51
Q

What happens to the airflow at angles beyond the critical or stalling angle?

A

The airflow is no longer smooth. More drag and less lift is produced.

52
Q

To maintain level flight at high speed, can the required lift be produced with a high or low AoA?

A

A low AoA

53
Q

To maintain level flight at low speed, can the required lift be produced with a high or low AoA?

A

A high AoA

54
Q

With increasing air speed, will both lift and drag increase?

A

Yes, both lift and drag will increase.

55
Q

What is the name given to the speed when a pilot has no option but to apply the critical/ stalling AoA to maintain a given amount of lift at low airspeeds?

A

The Stalling Speed

56
Q

What will occur if a pilot applies an AoA greater than the Critical/ Stalling Angle at a given airspeed?

A

The aircraft will stall

57
Q

How do you recover from a stall?

A
  1. Apply forward control column to pitch nose down / reduce AoA
  2. Level the wings
  3. Increase power as required
  4. Return to safe flight path
58
Q

The magnitude of the total reaction on an aerofoil depends upon what?

A
  1. The AoA

2. The speed of the relative airflow

59
Q

Once the stalling angle has been reached, any increase in the AoA will result in what?

A

Less lift and more drag

60
Q

For any given airspeed, the stalling angle is the angle at which what occurs to lift?

A

Lift reaches its maximum

PPL (A) (2 decks)

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