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M11 Resit > 11.1 Theory Of Flight > Flashcards

11.1 Theory Of Flight Flashcards

1
Q

What movement occurs around the lateral axis

A

Pitch

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2
Q

Where’s the lateral axis located

A

Wing tip to wing tip

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3
Q

What control surface is responsible for pitch

A

Elevators on horiz stab

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4
Q

What type of movement acts on the longitudinal axis

A

Roll

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5
Q

What type of movement acts on the longitudinal axis

A

Roll

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6
Q

What control surface is responsible for roll

A

Aileron

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7
Q

What control surface is responsible for roll

A

Aileron

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8
Q

What axis is responsible for yaw

A

Vertical

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9
Q

What axis is responsible for yaw

A

Vertical

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10
Q

What control surface allows yaw movement

A

Rudder

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11
Q

What control surface allows yaw movement

A

Rudder

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12
Q

What are the primate flight controls

A

Rudder
Elevator
Ailerons
(Sometimes roll spoilers too)

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13
Q

What axis do ailerons assist to affect control around

A

Longitudinal

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14
Q

When the left aileron is deflected up and the right is deflected down which was does the aircraft roll

A

Left

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15
Q

What tends to occur when the aircraft is rolled

A

Sideslip

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16
Q

What’s the force acting on the control surface in flight a product of

A

Kinetic energy and surface area

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17
Q

How is dynamic energy calculated

A

1/2pV shared or 1/2 density x airspeed squared

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18
Q

What’s the energy in the air proportional to

A

The square of the airspeed

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19
Q

What may happen to the ailerons being moved at high speeds when being moved and why
What’s done to combat this

A

Can go outside it’s structural limit loads due to the forces on the surface due to high speeds

Having inboard and outboard ailerons

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20
Q

When are both sets of ailerons used

A

Take off and landing

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21
Q

What aileron is locked out as aircraft speeds increase

A

Outboard

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22
Q

What’s used for roll control at high speeds

A

Inbrd ailerons and roll spoilers

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23
Q

What axis does the elevators affect and what type of control on what axis

A

Longitudinal
Pitch control on lateral

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24
Q

What’s a stabilator

A

Controls both elevator and horizontal stab

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25
Q

What axis do stabilators rotate around and what movement do they affect

A

Vertical and affect pitch

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26
Q

What’s usually installed in conjunction with a stabilator

A

Anti balance tab

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27
Q

What are stabilators used for

A

Enhanced speed and rapid manoeuvrability

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28
Q

What problem can occur with stabilators at high speed transonic flight

A

Surface can be rendered In effective due to a shockwave for,ed at the hinge line

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29
Q

What are variable incidence stabiles/ THS used for

A

Pitch trimming

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30
Q

What advantage does the variable incidence stabiliser/THS have

A

Reduced requirement for elevator deflection due to less drag

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31
Q

What direction does the nose go when the angle of attack of the THS increases

A

Nose down

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32
Q

Where are the horizontal control surfaces of canards located

A

Front of aircraft ahead of the main wings

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33
Q

How can canards fwd position improve the aircraft’s natural stability

A

By providing a nose down force

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34
Q

What are benifits of canards

A

Enhance aircraft’s stall resistance

Increase manoeuvrability ( as canard will stall first and cause a nose down pitching moment to help recover the stall )

Control redundancy (fallback/back up)

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35
Q

What’s the rudder used for

A

Directional or Yaw control

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36
Q

What direction does the aircraft go if the left rudder pedals pressed down

A

Left

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37
Q

What does the rudder limiter do

A

Restricts the amount of rudder deflection with increasing airspeed

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38
Q

What’s used to assist ailerons in a roll movement

A

Rudder

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39
Q

What are Frise ailerons

A

Differential ailerons

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40
Q

What are methods of the uneven drag on wings caused by aileron deflection

A

Frise ailerons
Differential ailerons
Spoilers

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41
Q

What affects can happen as a result of a high vertical stabiliser

A

Adverse roll

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42
Q

What systems in place r help overcome adverse roll

A

Aileron-rudder interconnect system

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43
Q

What system is used correct osicillations of Dutch roll

A

Yaw damping system

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44
Q

What aircraft dome have horizontal stabilisers

A

Delta-wing

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45
Q

What movement do you get on a elevon when they are moved in opposing directions

A

Aileron/roll

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46
Q

What way do the rudder gator control surfaces move to pitch the aircraft down

A

Ruddervator down together

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47
Q

Where are slots primarily located on the wing

A

Outboard leading edge

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48
Q

What’s the purpose of slots

A

Allows high energy air to accelerate through to the top of the wing and reenergise the boundary layer to prevent flow seperation

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49
Q

What’s the purpose of slots

A

Allows high energy air to accelerate through to the top of the wing and reenergise the boundary layer to prevent flow separation and stalls

Allowing aircraft to fly at slower speeds and higher aofa

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50
Q

Do slots give lift

A

No just re energise boundary layer

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51
Q

What’s a disadvantage of slots

A

Give drag

52
Q

How do slats increase lift

A

By increasing the camber

53
Q

What control surface can be used as a stall prevention in flight

A

Slats

54
Q

What’s a downside of flaps

A

Increased drag

55
Q

What can happen as flaps are deployed (negatives)

A

Aerodynamic force moves the wings centre of pressure rearwards causing a nose down pitch tendency

56
Q

What way will the nose pitch when the flaps are being PUT IN

A

Nose up

57
Q

How much % lift do the plain flaps provide

A

50-55

58
Q

What’s a benifit of split edge flaps

A

Avoids boundary layer separation ivermectin the upper surface

59
Q

What % lift does the split flap provide

A

60-65

60
Q

What percentage of lift does the slotted flap provide

A

70-75

61
Q

What does the fowler flap design do the chord of the wing

A

Increases

62
Q

What does the fowler flap design do the chord of the wing

A

Increases

63
Q

What percentage of lift does the fowler flap provide

A

Up to 95

64
Q

What do Krueger flaps help to do

A

Carry out low speed handling

65
Q

What are the two functions on spoilers

A

Assist ailerons in a roll
And to increase drag

66
Q

When can full deflection of spoilers be achueved

A

On ground

67
Q

What’s the main point of ground spoilers

A

To improve efficiency of the landing gear brakes by dumping the lift generated by the wing so forcing that weight into the landing gear

68
Q

What’s the main point of ground spoilers

A

To improve efficiency of the landing gear brakes by dumping the lift generated by the wing so forcing that weight into the landing gear

69
Q

What effect does spa wise flow have on the boundary layer

A

Thicken it

70
Q

What happens to the distance between the c of g ans the c of p when both wing tips stall at the same time,

A

They get closer

71
Q

How do sawtooth leading edges work

A

Creates a small vortex that limits the boundary layer outflow and redirects spanwise flow

72
Q

How are vortex generators installed

A

In pairs so the vortices mix

73
Q

What are stall strips made of

A

Alluminium

74
Q

What are trim tabs used for

A

Compensate for imbalances of aircraft

75
Q

Where are trim tabs usually positioned on light aircraft

A

Rudder

76
Q

What way do trim tabs deflect in relation to the flight control surface

A

Opposite direction to the direction the flight control has been deflected to

This assists to keep the flight control in the desired position

77
Q

What direction does the balance tab move in relation to the control surface and why

A

Opposite

Creates a force on the flight surface which assists the movement

78
Q

Disadvantage of the balance tab

A

Reduces efficiency of surface

79
Q

What direction does the anti-balance tab move in relation to the flight surface

A

Same direction but deflects to a greater angle than control surface

80
Q

What’s a disadvantage of an anti balance tab

A

More effort required to deflect these

81
Q

What direction does the servo tab move in relation to the Scot roll surface

A

Opposite

82
Q

What way does a spring tab deflect in with the control surface

A

Opposite

83
Q

What can happen if the c of g of a control surface is aft of the hinge line

A

Can cause an inertia to be felt and an ossicillation/flutter to follow

84
Q

How can torsional aileron flutter be prevented

A

Mass balancing so that the c of g is on or slightly ahead of the hinge line

85
Q

What’s the speed of sound at sea level

A

340 m/s

86
Q

How’s the Mach number calculate

A

The velocity of object (v) / speed of sound (a)

87
Q

Where are the sound waves if the objects travelling at low speeds

A

Ahead of the object

88
Q

What speeds does subsonic flight occur in

A

0-0.8 mach

89
Q

What speeds does transonic flight occur at

A

0.8-1.2 Mach

90
Q

What issue can occur with stability of flight in transonic region

A

Airflow separation due to shockwave

91
Q

What speeds are supersonic

A

1.2-5

92
Q

What happens to density and pressure at supersonic flight

A

Slight changes in pressure and no changes in density

93
Q

At what stage of flight is air compressible

A

Supersonic

94
Q

What happens to the coefficient of lift and coefficient of drag in the supersonic range

A

Reduction in coefficient of lift

Increased coefficient of drag

95
Q

What Mach number is airspeed considered compressible

A

0.4 Mach

96
Q

When does a normal shockwave formation take place

A

In transonic range at the Mcrit and will form at right angles to the path of the airflow

97
Q

What happens to the position of the shockwave as the mach number increases

A

Grows ans moves rearwards

98
Q

What happens to the speed of the airflow after it’s passed through the shockwave

A

Decelerates to a subsonic speed

99
Q

What happens to kinetic energy as it goes through a shockwave

A

Coverts to heat energy and temp rises

100
Q

What’s wave drag

A

Wave drag is the proportion of total drag which is due to shockwaves

101
Q

What’s the two ways to reduce wave drag

A

Using vortex generators

Area rule

102
Q

Generally what’s the position of the centre of lift on a circular arc wing type if the airflow on the wing is supersonic

A

50% of the chord

103
Q

Why’s it important that the aircraft is arranged so that the cross sectional area is as smooth as possible from nose to tail

A

To ensure volume distribution which minimises wave drag

104
Q

Why’s it important that the aircraft is arranged so that the cross sectional area is as smooth as possible from nose to tail

A

To ensure volume distribution which minimises wave drag

105
Q

What’s the sear hack body shape

A

The body with the lowest theoretical wave drag in supersonic flow

106
Q

What can be done to the shape of the aircraft to get volume distributions

A

Flattening the sides of the fuselage below a bubble canopy and at the tail surfaces to compensate for their presence.

107
Q

When’s an expansion wave formed

A

When supersonic airflow changes direction around a curve or corner away from the proceeding flow direction

108
Q

What happens to the static pressure, Density, temp, useful energy and total pressure when a expansion wave occurs

A

Stat pres,dens, temp decrease

Useful energy and total press stay same

109
Q

When’s aerodynamic heating significant

A

At supersonic speeds

110
Q

What happens to velocity and temp as if flows over an aerodynamic surface

A

Velocity decrease
Temp increase

111
Q

What’s Areodynamic heating also known as

A

Friction heating

112
Q

What percentage of strength does aluminium alloy lose as 250 degrees celsius

A

80%

113
Q

Why’s alluminium commonly used in some military aircraft (heat)

A

Lightweight and low coefficient of thermal expansion

114
Q

What’s the limit that gte compressors take axial velocities

A

Not much more than 0.4 Mach regardless of aircraft speed

115
Q

What does a normal shock diffuser inlet do

A

Employs a single normal shock wave at the inlet to slow the air to subsonic velocity

116
Q

What does a normal shock diffuser inlet do

A

Employs a single normal shock wave at the inlet to slow the air to subsonic velocity

117
Q

Why’s a normal shock diffuser inlet not used at higher-supersonic speeds

A

Bc the normal shockwave is strong and will cause a great reduction in total pressure recovered by the inlet

118
Q

Why’s a normal shock diffuser inlet not used at higher-supersonic speeds

A

Bc the normal shockwave is strong and will cause a great reduction in total pressure recovered by the inlet

119
Q

What’s the single and multiple oblique shock inlet do

A

Uses a series of very weak oblique shockwaves to gradually slow to the flow before a normal shock wave can occur. Slowing it before reduces the strength of a normal shockwave

Leads to a least waste in energy and highest pressure recovery

120
Q

How does the variable supersonic inlet work

A

When below Mach 1 - Inlet fully open and ac fly at high aofa
When just above Mach 1 - inlet closes slightly to employ single shockwave
When at high Mach numbers - close more so 3 oblique shockwave occur then 1 normal shock wave

121
Q

What’s a way to reduce profile thickness of the wing and it’s critical Mach number

A

Aero Swept wings

122
Q

How’s profile thickness calculate

A

Actual thickness / chord length

123
Q

What sweep angle do most modern jet ac have

A

30 degrees

Bc ur reduces prof thickness and increases crit mach number

124
Q

What disadvantage do swept wings have

A

Increased spanwise flow

This can cause stagnation in boundary layer and wing tip stall

125
Q

What disadvantage do swept wings have

A

Increased spanwise flow

This can cause stagnation in boundary layer and wing tip stall

126
Q

What’s bigger inbrd or outbrd ailerons

A

Outbrd

127
Q

When can fixed trim tabs be adjusted

A

Only on the ground

M11 Resit (13 decks)

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