ANNEX
Symbols
Quantities are dimensionless unless otherwise stated. Symbols and abbreviations not listed below are used only locally and defined in the text. Subscripts 1 and 2 denote conditions at the start and end of a segment respectively. Overbars denote segment mean values, i.e. average of start and end values.
- a
Average acceleration, ft/s2
- amax
Maximum acceleration available, ft/s2
- A, B, C, D
Flap coefficients
- E, F, GA,B, H
Engine thrust coefficients
- Fn
Net thrust per engine, lbf
- Fn/δ
Corrected net thrust per engine, lbf
- G
Climb gradient
- G′
Engine-out climb gradient
- GR
Mean runway gradient, positive uphill
- g
Gravitational acceleration, ft/s2
- ISA
International Standard Atmosphere
- N *
No of engines supplying thrust
- R
Drag-to-lift ratio CD/CL
- ROC
Segment rate of climb (ft/min)
- s
Ground distance covered along ground track, ft
- sTO8
Take-off distance into an 8 kt headwind, ft
- sTOG
Take-off distance corrected for w and GR, ft
- sTOw
Take-off distance into headwind w, ft
- T
Air temperature, °C
- TB
Breakpoint temperature, °C
- V
Groundspeed, kt
- VC
Calibrated airpeed, kt
- VT
True airspeed, kt
- W
Aeroplane weight, lb
- w
Headwind speed, kt
- Δs
Still air segment length projected onto ground track, ft
- Δsw
Segment length ground projection corrected for headwind, ft
- δ
p/po, the ratio of the ambient air pressure at the aeroplane to the standard air pressure at mean sea level: po = 101,325 kPa (or 1 013,25 mb)
- ε
Bank angle, radians
- γ
Climb/descent angle, radians
- θ
(T + 273,15)/(T0 + 273,15) the ratio of the air temperature at altitude to the standard air temperature at mean sea level: T0 = 15,0 °C
- σ *
ρ/ρ0 = Ratio of air density at altitude to mean sea level value (also, σ = δ/θ)