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Date of the module
A project supported by AIRBUS and the CAAC
Date of the module
2 - Climb in operation
Example: A320
climb at constant speed
250 kt (ATC limitation)
climb at constant speed
A320 : 300 kt
climb at constant Mach
A320 : M 0.78
Top Of Climb (TOC)
Start of
climb
10000 ft
29500 ft
acceleration
Change over
altitude
A project supported by AIRBUS and the CAAC
Date of the module
2 - Climb in operation
Energy conservation
Three sources of energy are available to generate aerodynamic forces :
- kinetic energy, which increases with increasing speed
- potential energy, which is proportional to altitude
- chemical energy, from the fuel
A project supported by AIRBUS and the CAAC
Date of the module
altitude
True Air Speed Rate of Climb
constant CAS
constant Mach
constant Mach
TROPOPAUSE
climb at constant TAS
2 - Climb in operation
Energy conservation
A project supported by AIRBUS and the CAAC
Date of the module
   
maximum
air climb
gradient
climb at
RC max
minimum consumptiondistance
climb
high speed climb
Cruise FL
MAXI
CLIMB
THRUST
CRUISE THRUST
distance
2 - Climb in operation
A project supported by AIRBUS and the CAAC
Date of the module
 Climb at Maximum Rate
Climbing at the maximum rate of climb speed enables a
given altitude to bereached in the shortest time.
Climb at Maximum Gradient
 The climb gradient at green dot speed is at its maximum.
Climbing at green dot speed enables a given altitude to be
achieved over the shortest distance.
 Climb at Minimum Cost
Minimum Cost
Between CI=0 and CImax
CI=0=IASECON=maximum rate of climb speed
CI=CImax=IASECON=VMO-10kt
A project supported by AIRBUS and the CAAC
Date of the module
 Influencing Parameters
1. Altitude Effect
PA↑ ⇒ climb gradient ↓
rate of climb ↓
2. Temperature Effect
Temperature ↑ ⇒ climb gradient ↓
rate of climb↓
 3. Weight Effect
Weight ↑ ⇒ climb gradient ↑
rate of climb ↑
A project supported by AIRBUS and the CAAC
Date of the module
 Influencing Parameters
4. Wind Effect
Headwind ↑ ⇒ Rate of climb
Fuel and time to T/C →
Flight path angle (γg) ↑
Ground distance to T/C↓
Tailwind↑ ⇒ Rate of climb →
Fuel and time to T/C→
Flight path angle (γg) ↑
Ground distance to T/C ↑
A project supported by AIRBUS and the CAAC
Date of the module
1 - Climb angle and rate of climb
2 - Climb in operation
3 - Cabin climb
Table of Contents
A project supported by AIRBUS and the CAAC
Date of the module
aircraft
cabin
time
cabin rate of climb  500 ft/mn
pressure
Zp
Zp > 30000 ft
Zp = 8000 ft
3 - Cabin climb
A project supported by AIRBUS and the CAAC
Date of the module
Table of Contents
1 - Cruise
2 - Climb
3 - Descent
4 - Holding
A project supported by AIRBUS and the CAAC
Date of the module
1 - Descent angle and rate of descent
2 - Descent in operation
3 - Cabin descent
Table of Contents
A project supported by AIRBUS and the CAAC
Date of the module
1 - Descent angle and rate of descent
2 - Descent in operation
3 - Cabin descent
Table of Contents
A project supported by AIRBUS and the CAAC
Date of the module
TAS
rate of climb
rate of descent
TASRDmin TASmin
minimum rate
of descent
maximum rate
of descent
Given
engine thrust, m
speed limit VMO / MMO
1 - Descent angle and rate of descent
A project supported by AIRBUS and the CAAC
Date of the module
True Air Speed
rate of
descent
min
speed limit VMO / MMO
light gross weight
heavy gross weight
1 - Descent angle and rate of descent
Influence of weight
RD  when w 
A project supported by AIRBUS and the CAAC
Date of the module
 air angle of descent
ground angle of descent
flight path
TAS
HEADWIND
1 - Descent angle and rate of descent
A project supported by AIRBUS and the CAAC
Date of the module
no wind
FL 350
　
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