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Notations Flashcards

1
Q

a

A

1/rad

Lift curve slope (dCL/d⍺, dCL/dδ)

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2
Q

AR

A

-

Lifting Surface Aspect Ratio

AR = b^2/S

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3
Q

b

A

m

Lifting surface span

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4
Q

c

A

m

Chord length

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5
Q

cs

A

m/s

Speed of sound

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6
Q

c’/c

A

-

High-lift device chord extension ratio

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7
Q

_
c

A

m

Mean Aerodynamic Chord length

_
c = 2 (integrate(c^2 dy/S) between b/2 and 0)

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8
Q

CD

A

-

Drag Coefficient

CD = CD0 + CDi

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9
Q

CD0

A

-

Drag Coefficient at zero lift

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10
Q

CDi

A

-

Lift dependent/induced Drag Coefficient

CDi = CL^2/piARe

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11
Q

CH

A

-

Hinge Moment Coefficient

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12
Q

CL

A

-

Lift Coefficient

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13
Q

CL0

A

-

Lift Coefficient at zero aircraft angle of attack

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14
Q

CM

A

-

Pitching Moment Coefficient

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15
Q

CM0

A

-

Pitching Moment Coefficient at zero lift (constant when taken about surface aerodynamic centre)

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16
Q

CT

A

-

Thrust Coefficient

CT = T/0.5ρV∞^2*S

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17
Q

D

A

N

Drag Force

D = 0.5ρV∞^2SCD

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18
Q

e

A

-

Oswald/span efficiency factor

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19
Q

g

A

m/s^2

Gravitational acceleration

g0 = 9.81 m/s^2

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20
Q

H

A

N m

Hinge moment

                                      _ H = 0.5*ρ*V∞^2*Ssurf*csurf*CH
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21
Q

Hm

A

-

Stick-fixed manoeuvre margin

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22
Q

Ixx

A

kg m^2

Roll second moment of inertia

Ixx = integrate(y^2 + z^2)dm

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23
Q

Iyy

A

kg m^2

Pitch second moment of inertia

Iyy = integrate(x^2 + z^2)dm

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24
Q

Izz

A

kg m^2

Yaw second moment of inertia

Izz = integrate(y^2 + x^2)dm

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25
Q

Ixz

A

kg m^2

Cross second moment of inertia

Ixz = integrate(xz)dm

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26
Q

i

A

rad

Lifting surface setting angle - defined between mean aerodynamic chord and aircraft z-datum

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27
Q

Kn

A

-

Stick-fixed static margin

_ _
xnp - xCG

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28
Q

K’n

A

-

Stick-free static margin

_ _
x’np - xCG

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29
Q

L (N)

A

N

Lift

L = 0.5ρV∞^2SCL

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30
Q

L (N m)

A

N m

Rolling Moment (positive port wing up)

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31
Q

lH

A

m

Horizontal separation between wing and tailplane aerodynamic centres

xH - xW

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32
Q

l’H

A

m

Horizontal tailplane lift moment arm

xH - xCG

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33
Q

m

A

kg

Aircraft mass

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34
Q

M

A

N m

Pitching Moment (positive nose up)

                               _ M = 0.5*ρ*V∞^2*S*c*CM
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35
Q

M∞

A

-

Freestream Mach number

M∞ = V∞/cs

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36
Q

n

A

-

Load factor

n = Lift/Weight

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37
Q

N

A

N m

Yawing moment (positive port wing forward)

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38
Q

p (Pa)

A

Pa

Pressure

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39
Q

p0

A

Pa

Total/Pitot pressure

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40
Q

ps

A

Pa

Static pressure

41
Q

p (rad/s)

A

rad/s

Roll rate (positive port wing up)

42
Q

q

A

rad/s

Pitch rate (positive nose up)

43
Q

q∞

A

Pa

Dynamic head/pressure

q∞ = 0.5ρV∞^2

44
Q

r

A

rad/s

Yaw rate (positive port wing forward)

45
Q

S

A

m^2

Lifting Surface Planform Area

46
Q

T

47
Q

Td

A

s

Damped Period of Oscillation

Td = 2pi/ωd

48
Q

Tn

A

s

Undamped Period of Oscillation

Td = 2pi/ωn

49
Q

U

A

m/s

Velocity along x wind axis (positive moving forward)

50
Q

V

A

Velocity along y wind axis (positive moving starboard)

51
Q

V∞

A

m/s

True Freestream Velocity

V∞ = sqrt(U^2 + V^2 + W^2)

52
Q

Vi

A

m/s

Equivalent Freestream Velocity

Vi = sqrt(σ)*V∞

53
Q

_
V

A

-

Non-dimensional Velocity

Vi/VimD

54
Q

_
VH

A

-

Horizontal tailplane volume coefficient

_ _
(xH - xW) * SH/Sref

55
Q

_
V’H

A

-

Modified Horizontal tailplane volume coefficient

_ _
(xH - xCG) * SH/Sref

56
Q

_
VV

A

-

Vertical tailplane volume coefficient

_ _
(xV - xCG) * SV/Sref

57
Q

W (m/s)

A

m/s

Velocity along z wind axis (positive moving downwards)

58
Q

W (N)

A

N

Aircraft Weight

59
Q

x

A

m

Distance aft of aircraft datum, parallel to freestream velocity vector

60
Q

xac

A

m

Chordwise position about which surface dCM/dCL = 0

61
Q

xnp

A

m

Distance of stick-fixed neutral point aft of aircraft datum, parallel to freestream velocity vector

62
Q

x’np

A

m

Distance of stick-free neutral point aft of aircraft datum, parallel to freestream velocity vector

63
Q

xW

A

m

Distance of wing aerodynamic centre aft of aircraft datum, parallel to freestream velocity vector

64
Q

X

A

N

Force along x wind axis (positive forward)

65
Q

y

A

m

Spanwise distance port of aircraft datum, normal to the x - z plane

66
Q

Y

A

N

Force along y wind axis (positive to starboard)

67
Q

z

A

m

Distance above aircraft datum, normal to the freestream velocity vector

68
Q

Z

A

N

Force along z wind axis (positive downwards)

69
Q

⍺

A

rad

Angle of attack, defined between freestream velocity and aircraft z-datum

70
Q

⍺0

A

rad

Lifting surface zero-lift angle of attack

71
Q

β

A

rad

Sideslip angle, defined between freestream velocity and aircraft centreline

72
Q

γ

A

rad

Climb angle, defined between freestream velocity and the earth frame (positive in a climb)

73
Q

Γ

A

deg

Dihedral angle

74
Q

δ

A

rad

Control surface deflection

75
Q

ε

A

rad

Downwash/upwash angle

76
Q

ε0

A

rad

Downwash/upwash angle at zero aircraft angle of attack

77
Q

є

A

rad

Thrust setting angle - defined between thrust line and aircraft z-datum

78
Q

ζ

A

-

Damping ratio

79
Q

η

A

-

Lifting surface aerodynamic efficiency factor

η = (Vlocal / V∞)^2

80
Q

Θ

A

rad

Pitch angle - defined between wind body-fixed axes and the earth frame (positive in the climb)

81
Q

λ

A

-

Eigenvalue

82
Q

Λ

A

rad

Lifting surface sweep angle (typically at quarter-chord line)

83
Q

ρ

A

kg/m^3

Density of air

84
Q

Φ

A

rad

Roll angle - defined between wind body-fixed axes and the earth frame (positive in the right roll)

85
Q

Ψ

A

rad

Yaw angle - defined between wind body - fixed axes and the earth frame (positive in the right turn)

86
Q

ω

A

rad/s

Angular velocity

87
Q

ωd

A

rad/s

Damped natural angular frequency of oscillation

88
Q

ωn

A

rad/s

Undamped natural angular frequency of oscillation

ωd = ωn * sqrt(1 - ζ^2)

89
Q

(⋅)A

A

Property relating to aileron

90
Q

(⋅)C

A

Property relating to canard

91
Q

(⋅)CG

A

Centre of Gravity

92
Q

(⋅)e

A

Property at equilibrium value

93
Q

(⋅)E

A

Property relating to elevator

94
Q

(⋅)H

A

Property relating to horizontal tailplane

95
Q

(⋅)R

A

Property relating to rudder

96
Q

(⋅)ref

A

Aircraft reference value

                               _         _ typically Sref = SW, cref = cW
97
Q

(⋅)T

A

Property relating to trim-tab

98
Q

(⋅)V

A

Property relating to vertical tailplane

99
Q

(⋅)W

A

Property relating to main lifting surface (wing)

2 (8 decks)

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