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Ground School - C Middleton > 1 Principles Of Flight > Flashcards

1 Principles Of Flight Flashcards

1
Q

What is the air density in an ISA?

A

1.225 kg/m^3

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2
Q

What is the standard pressure in an ISA?

A

1013.25 hPa

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3
Q

1 hPa = ? ft at low level

A

30 ft

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4
Q

What occurs with temperature at the Tropopause

A

It remains constant

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5
Q

What is the Tropopause height in an ISA?

A

36,090 ft

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6
Q

What is the temp lapse rate in the troposphere?

A

-1.98C / 1000ft

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7
Q

What occurs with density as height increases?

A

It decreases

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8
Q

What factors affect density?

A

Pressure
Temp
Altitude
Water Vapour

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9
Q

How is density affected by temperature?

A

As temperature increases density decreases

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10
Q

What is Newton’s 1st Law?

A

Law of Inertia

A body remains in a state of rest or uniform motion unless acted on by an external force

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11
Q

What is momentum?

A

Mass x Velocity

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12
Q

What is Newton’s 2nd Law?

A

Law of Force

The rate of change of momentum (acceleration) experienced by a body of mass is proportional to the force applied to it

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13
Q

What is Newton’s 3rd Law?

A

Law of Action/Reaction

For every action there is an equal and opposite reaction

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14
Q

A gas in steady motion has what properties? (in term of energies)

A

Potential Energy
Heat Energy
Pressure Energy
Kinetic Energy

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15
Q

Total Pressure = ? + ?

A

Static Pressure + Dynamic Pressure = Total Pressure

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16
Q

Write Bernoulli’s Theorem

A

Total Pressure = P + (1/2 x ρ x V^2)

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17
Q

In Bernoulli’s what is ρ?

A

Density

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18
Q

What happens to pressure with an increase in velocity of a fluid?

A

Pressure decreases

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19
Q

What is an Aerofoil?

A

Surface designed to generate lift from airflow over it’s surface.

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20
Q

What is the Leading Edge Radius?

A

The shape of the leading edge.

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21
Q

What is the Chord Line?

A

Infinite line through the leading and trailing edge of an aerofoil section.

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22
Q

What is the Chord?

A

Distance between the leading and trailing edge of an aerofoil section

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23
Q

What is the Camber?

A

The curvature of the aerofoil. (Upper surface camber/Lower surface camber)

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24
Q

What is the Mean Camber Line?

A

A line equidistant from the upper and lower surfaces of an aerofoil.

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25
Q

What is the Angle of Incidence?

A

Angle between the chord line and the longitudinal fuselage datum.

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26
Q

What is the Relative Airflow (RAF)?

A

Direction of airflow that is remote from the aircraft/ unaffected by its presence. Also known as Freestream flow

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27
Q

What is the Angle of Attack (AoA)?

A

The angle between the chord line and the relative airflow.

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28
Q

Streamline is?

A

The path that a particle of air would/will take

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29
Q

Freestream Flow is?

A

A region of air where P, T and relative vel. are unaffected by the passage of an aerofoil

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30
Q

Define Aspect Ratio

A

AR = Span/Mean Chord or (Span^2)/Mean Chord

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31
Q

Describe a wing with High Aspect Ratio

A

Long and Thin (Glider)

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32
Q

Describe a wing with Low Aspect Ratio

A

Short and Stubby (F35)

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33
Q

What is Laminar Flow (steady flow)?

A

Steady flow lines with no mixing

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34
Q

What is Separated Flow?

A

Halfway between steady and unsteady flow

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35
Q

What is Turbulent Flow (unsteady flow)?

A

Large amount of mixing and not represented with streamlines

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36
Q

What 4 factors impact the pressure distribution on an aerofoil?

A

Shape of the aerofoil
Aerofoil attitude to RAF
Air Density
Velocity

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37
Q

True or False. Changing the AoA changes the Centre of Pressure?

A

True

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38
Q

Centre of Pressure is optimal at what AoA?

A

Normal

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39
Q

At a LOW AoA the Centre of Pressure moves to the …. of the aerofoil

A

Rear

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40
Q

At a HIGH AoA the Centre of Pressure moves to the …. of the aerofoil

A

Front

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41
Q

Lift acts perpendicular to what?

A

Relative Airflow

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42
Q

Drag acts perpendicular to what upwards force?

A

Lift

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43
Q

Combining Lift and Drag gives what?

A

Total Aerodynamic Reaction

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44
Q

What is the Lift equation and define each term?

A

L = C(L) 0.5 rho V^2 S

L=Lift
C(L)= Coefficient of Lift
rho=density
V=Free Stream Velocity
S= Wing Area
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45
Q

What is the Critical Angle of Attack?

A

15 or 16 deg

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46
Q

Coefficient of lift is made up of what 3 components?

A

AoA
Wing Planform
Wing Surface Condition

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47
Q

What happens to the critical AoA as the camber of the aerofoil increases?

A

Critical AoA reduces with increasing camber

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48
Q

Describe the C(L) vs AoA graph with changing cambers

A

The steepness of the performance line does not change but shifts to the left as camber is increased, with the max C(L) increasing slightly.

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49
Q

How does Aspect Ratio (AR) affect the C(L) vs AoA graph?

A

AR alters the gradient of the performance line. High AR steeper gradient, lower AR shallower gradient.

Lower AR tend to have higher critical AoA.

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50
Q

How does the planform affect the C(L) vs AoA graph?

A

Straight wing has a more gentle change of C(L) around critical angle.

Swept wing has a more abrupt change to the C(L) around the critical angle.

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51
Q

How does wing surface condition affect the C(L) vs AoA graph?

A

Smoother surface gives max performance.

As the surface roughens, the gradient of the performance curve remains the same but the critical angle is lower.

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52
Q

What factors affect lift?

A

RAF
AoA
Downwash. Increasing AoA will increase downwash Increase downwash will reduce the effective AoA. Reduced AoA tilts the lift component backwards therefore reducing lift.

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53
Q

What vector opposes thrust?

A

Drag

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54
Q

What are the 2 types of drag?

A

Zero Lift Drag (ZLD)

Lift Dependant Drag (LDD)

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55
Q

What is the Drag equation?

A

D =C(D) x 0.5 x rho x V^2 x S

D=Drag
C(D)= Coefficient of Drag
rho=density
V=Free Stream Velocity
S= Wing Area
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56
Q

Zero Lift Drag is made up of what 3 components?

A

Surface Friction - Aero resistance from contact of RAF with surface of aircraft.
Form drag - The shape ‘shown’ to the airflow.
Interference - Caused by external tanks, pods, weapons etc

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57
Q

How can we reduce interference drag?

A

Better aero shapes, internal stowage

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58
Q

Lift dependant drag comprises of

A

Induced Drag

Elements of Zero Lift Drag (ZLD)

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59
Q

Induced drag predominantly comes from what behaviour associated with spanwise flow?

A

Vortex formation

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60
Q

5 factors that effect vortex formation are:

A 
Wing Planform
Aspect Ratio
Lift and Weight
Speed
AoA
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61
Q

How can we minimise Induced Drag?

A 
Winglet
Tip Tank/Missile
Taper
High AR
Washout
Change of Aerofoil Section
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62
Q

What is the ‘Taper’ of a wing?

A

The changing of the chord between the base to the tip of the wing

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63
Q

What is washout?

A

The ‘twist’ of the wing along its length?

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64
Q

Zero Lift Drag (ZLD) …… as speed increases.

A

increases

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65
Q

Zero Lift Drag (ZLD) is dominant at ….. speeds

A

higher

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66
Q

Lift Dependant Drag (LDD) …… as speed increases.

A

decreases

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67
Q

Lift Dependant Drag (LDD) is dominant at …… speeds

A

lower

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68
Q

Total drag is the combination of …… + ……

A

Zero Lift Drag (ZLD)
+
Lift Dependant Drag (LDD)

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69
Q

What does V(IMD) stand for?

A

Velocity (Indicated Minimum Drag)

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70
Q

With respect to fuel, why is V(IMD) of interest?

A

Lowest fuel consumption required to overcome drag of aircraft.

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71
Q

Optimal lift/drag ratio occurs at about what velocity? (name of velocity)

A

V(IMD)

72
Q

Max lift occurs at AoA of ….

A

16 deg

73
Q

Min drag occurs at AoA of ….

A

2 deg

74
Q

Most efficient lift/drag performance our aerofoil of interest occurs at …. (AoA)

A

4 deg

75
Q

What is the lift/drag ratio defined as?

A

C(L) / C(D)

76
Q

The LATERAL axis passes….

A

through the wings

77
Q

The LONGITUDINAL axis passes….

A

along the length of the fuselage

78
Q

The NORMAL axis passes…

A

vertically through the a/c

79
Q

What action is performed around the LONG, LAT and NORMAL axis’

A

LONG - Roll
LAT - Pitch
NORMAL - Yaw

80
Q

Name the 3 PRIMARY flight control surfaces

A

Elevator
Aileron
Rudder

81
Q

What action do each of the the Primary Flight Control Surfaces control?

A

Elevator - Pitch
Aileron - Roll
Rudder - Yaw

82
Q

A ‘heavy’ stick can make the a/c …. to control

A

Difficult

83
Q

A ‘light’ stick may cause the a/c to be ….. easily.

A

Overstressed

84
Q

Control movements should be …… to the given a/c

A

Proportional

85
Q

What PFCS is most responsive?

A

Aileron

86
Q

What are the PRIMARY and further effects of the PFCS?

A

Elevator - (P) Pitch + (Furth) Height/Speed Interchange
Aileron - (P) Roll + (Furth) Yaw
Rudder - (P) Yaw + (Furth) Roll

87
Q

Name the SECONDARY flight control surfaces

A

Flaps
Spoilers
Air Brakes
Trim Tabs

88
Q

Flaps provide extra l… and d…

A

Lift and drag

89
Q

What happens to the Lift vs Drag ratio when the form drag is increased?

A

The Lift vs Drag ratio will decrease.

90
Q

With flaps extended. What happens to the critical angle?

A

Critical angle will decrease

91
Q

Flaps have 3 effects. 2 increasing, 1 decreasing. What are these?

A

Increase Lift
Increase Drag
Decrease Lift/Drag ratio

92
Q

What are the 2 types of trim surfaces?

A

Fixed Trim

Trim Tabs

93
Q

If you want to trim the nose up. What direction should the trim tabs in the elevator be pointing?

A

Upwards

94
Q

Rate of climb is determined by what?

A

Airspeed

Angle of Climb

95
Q

If we want to climb and maintain the same speed. We need to add ….

A

POWER

96
Q

To maintain a climb at a given airspeed (more accurately EAS) ____ power is required than in level flight.

A

MORE

97
Q

The angle of climb is determined by the amount of _____ left after ______ drag.

A

THRUST

OPPOSING

98
Q

For a piston a/c, the max angle of climb speed will be just above what speed? Denoted as V(MU)

A

Unstick speed

99
Q

The lowest calibrated airspeed at and above an a/c can safely lift off and continue take-off is …..

A

Unstick speed

V(MU)

100
Q

At higher altitudes the “power available” curve of the engine is _____

A

LOWER

101
Q

Glide descent is defined as ______ travel per altitude ____.

A

FORWARD travel per altitude LOST

102
Q

When descending. To maintain airspeed, energy must be _____ to overcome drag.

A

EXPENDED

103
Q

Endurance gliding is about ….

A

flying for as LONG (time) as possible.

104
Q

Range gliding is about ….

A

flying as FAR as possible.

105
Q

Max glide distance is achieved at …. lift/drag ratio.

A

OPTIMUM

106
Q

A tailwind will ____ ground distance travelled while gliding.

A

DECREASE

107
Q

A headwind will ____ ground distance travelled while gliding.

A

INCREASE

108
Q

Weight does what to glide angle? (also impact on range vs endurance gliding)

A
  • Not effect the gliding angle.
  • Range gliding is unchanged in still air.
  • Endurance gliding decreases with increased weight.
109
Q

What control surface do we use to ROLL the aircraft?

A

Aileron

110
Q

T or F? When turning, without other inputs you will lose altitude.

A

TRUE

The vertical lift component will be reduced in a turn.

111
Q

To maintain altitude when turning you are required to increase lift by increasing what?

And what is the secondary effect of this?

A

Angle of Attack

Therefore will begin to introduce a centripetal force and therefore g.

112
Q

Progressive increase in lift and loading in a turn can be continued until:

A

A/c stall when AoA reaches critical angle

g threshold of pilot is reached

g threshold of the a/c is reached

113
Q

When making a level turn the _____ component of ____ must be equal to the ____ to maintain altitude.

A

VERTICAL component of LIFT

equal to

WEIGHT

114
Q

When an a/c turns, lift acts towards the ____ of the turn as well as _____.

A

CENTRE of the turn as well as UPWARDS

115
Q

In a level turn, if weight increases;
What is also required to increase?
What else will increase to maintain the same radius turn?

A

Vertical component of lift required to increase.

Therefore, the centripetal force will also increase (‘g’)

116
Q

To achieve a max rate turn, the following should be satisfied…

A
  • Wing loading (weight of a/c) to be as low as possible.
  • Air as dense as possible.
  • Max value of the product of C(L) and Angle of Bank.
117
Q

In a minimum radius or max rate turn, thrust _____ the lift needed from the wing and can help ____ turn radius.

A

thrust REDUCES the lift needed

help IMPROVE/MINIMISE

118
Q

Describe a standard rate turn

A

3 deg per second

180 in a minute

119
Q

A clean a/c will always stall at the ____ AoA, regardless of weight

A

SAME AoA

120
Q

Basic stall speed is denoted by ….

A

V(B)

121
Q

In level flight and at low speeds, the AoA will be _____

A

HIGH

As the wing works ‘hard’ to maintain lift in the reduced airflow.

122
Q

During the stalling process, describe what happens to the centre of pressure.

A

As the AoA increases towards the critical angle the CoP will move towards the leading edge.

When it passes the critical angle it will quickly move back towards the trailing edge.

123
Q

At what point does the air over the wing become turbulent?

A

Transition Point

124
Q

As speed reduces, what must the AoA do to keep lift constant?

A

The AoA must INCREASE.

125
Q

Key factors that change stalling speed are:

A
  • Changing weight
  • Manoeuvring (Load factor(n))
  • Configuration (changes in C(L)max)
  • Power and slipstream
126
Q

Changing the weight of the a/c impacts; the stall SPEED or stall ANGLE?

A

SPEED

127
Q

If the weight is increased, the AoA required to maintain level flight ______ for the same speed.

A

INCREASES

128
Q

Stability describes the motion of a body after __________________________

A

after AN EXTERNAL FORCE HAS BEEN REMOVED/APPLIED.

129
Q

The two types of stability are:

A

Static - Immediate Reaction

Dynamic - Subsequent Reaction

130
Q

What happens to a POSITIVELY Stable body?

A

A body returns to original position

131
Q

What happens to a NEUTRALLY Stable body?

A

A body that takes up a new position

132
Q

What happens to a NEGATIVELY Stable body?

A

A body continues to move away from original position

133
Q

STATIC stability describes …

A

The immediate reaction of the body after disturbance.

134
Q

DYNAMIC stability describes …

A

The subsequent reaction of the body after disturbance.

135
Q

Factors that will affect the long term response of an a/c are:

A 
Momentum (Vel x Mass)
Static stabilities (pitch, roll, yaw)
Angular velocities about the 3 axes
Angular momentum
Aerodynamic damping methods
136
Q

Dynamic stability can be described in 5 ways. These are:

A 
Negative Dynamic Stability
Negative Dynamic Stability (Divergence)
Neutral Dynamic Stability
Positive Dynamic Stability (Damped Phugoid)
Positive Dynamic Stability (Convergence)
137
Q

What design features will enhance

DIRECTIONAL STABILITY?

A
  • Large Fin
  • Long Moment Arm

Example: TORNADO

138
Q

What design features will enhance

LONGITUDINAL STABILITY?

A
  • Long Horizontal Tailplane
  • Long Moment Arm

Example: A400

139
Q

What design features will enhance

LATERAL STABILITY?

A
  • Large Fin
  • Dihedral
  • Sweep Back
  • High Wing

Example: C17

140
Q

The range of an a/c is determined by

A 
Airframe Consideration - Flaps, Gear etc
Temperature - Colder=More Dens + Increase engine efficiency
High Altitude
IAS vs Drag
IAS vs TAS
141
Q

Considering range, V(IMD) is important because …

A

It is the speed that provides the least amount of drag on the airframe.

142
Q

In a turboprop maximum range is achieved at:

A
  • Cruise Climb
  • Max Continuous RPM
  • IAS at V(IMD)
143
Q

Lift Dependent Drag curves moves to the _____ when you lose weight

A

LEFT

144
Q

In a turbojet a/c when flying for range we should:

A
  • Fly at Max TAS/drag
  • At low altitudes at 1.32xV(IMD)
  • As weight reduces (burning fuel) a/c should cruise climb at constant mach
145
Q

What RPM do we want to operate at in a TURBOPROP and TURBOJET?

A

TURBOPROP - Max CONTINUOUS

TURBOJET - OPTIMUM

146
Q

TURBOJET engines are designed to operate in the _____ rpm band.

A

OPTIMUM rpm band

147
Q

What speeds do we want to operate at in a TURBOPROP and TURBOJET?

A

TURBOPROP - V(IMD)

TURBOJET - 1.32xV(IMD)

148
Q

What is a C of A?

A

Certificate of Airworthiness

149
Q

The maximum permissible T/O weight is the least after considering:

A
  • C of A limit
  • WAT (Weight-Alt-Temp) limit for T/O and LANDING
  • Field Length
  • T/O net flight path
  • En-route terrain clearance
150
Q

Define Wing Loading

A

Weight/Area

151
Q

Name 3 lift augmentation devices

A

Slats - delay stall until higher angle of attack
Flaps - increase lift by increasing the camber
Boundary layer control

152
Q

Lift augmentation devices are used to increase ______ ______ ____________

A

MAX LIFT COEFFICIENT

153
Q

The airflow caused by slats does what to the boundary layer?

A

RE-ENERGISES it

154
Q

The use of slats does provides what?

A
  • Improved control at low speeds

- Augments lift

155
Q

Flaps vary the ______ ____ of the wing section

A

CAMBER LINE

156
Q

The GREATER the mean camber the _____ the lift capability of the wing.

A

GREATER

157
Q

Name the 3 types of propeller

A
  • Fixed Pitch
  • Variable Pitch - Piston
  • Variable Pitch - Gas turbine
158
Q

TRUE or FALSE? - Propellers have washout?

A

TRUE - Propellers do have washout (twist) along their length

159
Q

At what speed does drag increase significantly?

A

Near the speed of sound

160
Q

The PREFECT propeller rotates _____ from the pilots perspective

A

CLOCKWISE

161
Q

Propeller blade washout is used to _____ an ______ angle of attack along its length

A

MAINTAIN an EFFICIENT

162
Q

____ Pitch is used to maintain maximum efficiency at LOW AIRSPEEDS

A

FINE Pitch

163
Q

____ Pitch is used to maintain maximum efficiency at HIGHER AIRSPEEDS

A

COARSE Pitch

164
Q

Define Windmilling

A

Loss of positive torque on the propellers

Propellers will spin due to air movement over their surface. Spinning the drive shaft and the gearbox

165
Q

Propellers are _________ following engine failure, to prevent them inducing significant drag

A

FEATHERED

166
Q

How can you increase the ‘SOLIDITY’ of the propeller

A
  • Increase the number of blades

- Increase the chord of each blade

167
Q

Swing on take-off can be caused by:

A
  • Slipstream effect

- Torque Reaction

168
Q

The slipstream effect of a CLOCKWISE rotating propeller (pilot’s view) will induced asymmetric flow over the fin and rudder.

Resulting in the a/c yawing to the ____

A

LEFT

169
Q

The torque reaction of a CLOCKWISE rotating propeller (pilot’s view) will induce a counter torque on the a/c frame.

There will be an increased load on the ____ side undercarriage causing the a/c to swing ____ on travel down the runway during takeoff.

A

Increased load on LEFT undercarriage

Swing to the LEFT on travel

170
Q

What does Vx represent?

A

Max angle climb speed

171
Q

What does Vy represent?

A

Max rate climb

172
Q

V(mu) is known as the ______ speed.

A

UNSTICK

173
Q

What a/c will try and operate at OPTIMUM RPM?

A

Jet Engine A/C

174
Q

What a/c will try and operate at MAX CONTINUOUS RPM?

A

TurboProp

175
Q

Lowering slats does what to the critical angle?

A

INCREASES CRITICAL ANGLE

Ground School - C Middleton (12 decks)

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