flight operation 飞行运行概述(25)

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versus Mach number, at given altitude
Mach number optimization
versus altitude, at given Mach number
optimum altitude
A project supported by AIRBUS and the CAAC
Date of the module
1 - Direct operating cost
2 - Specific range
3 - All engines operating cruise speeds
4 - Altitude optimisation
5 - Maximum cruise altitude
6 - Buffet limit
7 – ATC requirment
8 - Cruise optimisation
Table of Contents
A project supported by AIRBUS and the CAAC
Date of the module
2 - Specific Range
SR = 1
Distance consumption
Unit : nm / ton or nm / 1000 lbs
Example : A320-200 SR = 200 nm / ton
(58 tons at FL 350 M.78)
A project supported by AIRBUS and the CAAC
Date of the module
 2 - Specific Range
SR =
SR =
1
Distance consumption
Ground speed
Hourly consumption
A project supported by AIRBUS and the CAAC
Date of the module
 2 - Specific Range
SR =
SR =
With no wind SR =
1
Distance consumption
Ground speed
Hourly consumption
TAS
Ch
A project supported by AIRBUS and the CAAC
Date of the module
T
To
speed of sound
temperature
2 - Specific Range
 TAS = a.M and a = ao
A project supported by AIRBUS and the CAAC
Date of the module
2 - Specific Range
 TAS = a.M and a = ao T
To
661 kt
288 °K
A project supported by AIRBUS and the CAAC
Date of the module
 TAS= a.M and a = ao
 Ch = Csp. Ta and Ta =
T
To
Specific consumption
Engine thrust available
Lift to Drag ratio
mg
L/D
A project supported by AIRBUS and the CAAC
Date of the module
 TAS= a.M and a = ao
 Ch = Csp. Ta and Ta =
T
To
mg
L/D
mg
L/D
T
To
ao M
Csp
SR =
A project supported by AIRBUS and the CAAC
Date of the module
SR =
ao M L/D
Csp
T To
mg
2 - Specific Range
Aerodynamics
Engine Weight
A project supported by AIRBUS and the CAAC
Date of the module
 SR variations with Mach
number
M.L/D
Csp
T To
.70 .80 .90 Mach
0,075
Csp
T
To
0,085
(kg/h.N)
10
15
M.L/D Given :
- weight
- altitude
2 - Specific Range
A project supported by AIRBUS and the CAAC
Date of the module
 SR variations with Mach
number
Mach
SR
.70 .80 .90
100
150
200
250 (nm/t)
Given :
- weight
- altitude
SR max
Maxi-range Mach
SR reaches a maximum
2 - Specific Range
A project supported by AIRBUS and the CAAC
Date of the module
1 - Direct operating cost
2 - Specific range
3 - All engines operating cruise speeds
4 - Altitude optimisation
5 - Maximum cruise altitude
6 - Buffet limit
7 – ATC requirment
8 - Cruise optimisation
Table of Contents
A project supported by AIRBUS and the CAAC
Date of the module
Mach
SR
All along the flight,
the fuel consumption
makes the aeroplane
weight decrease
 Maxi-Range
 influence of weight Given :
- altitude
3 - All engines operating cruise speeds
A project supported by AIRBUS and the CAAC
Date of the module
Mach
SR
burn off
 Maxi-Range
Given :
- altitude
3 - All engines operating cruise speeds
A project supported by AIRBUS and the CAAC
Date of the module
Mach
SR
burn off
 Maxi-Range
Given :
- altitude
3 - All engines operating cruise speeds
As weight decreases,
- the specific range increases
- the Maxi-Range Mach decreases too
A project supported by AIRBUS and the CAAC
Date of the module
Mach
SR
burn off
 Maxi-Range
 Cd minimum : trip fuel is
minimum
 but low speed : trip time is
quite long !
Given :
- altitude
3 - All engines operating cruise speeds
A project supported by AIRBUS and the CAAC
Date of the module
Mach
SR
burn off
 Maxi-Range
 Cd minimum : trip fuel is
minimum
 but low speed : trip time is
quite long !
 Alternative :
 Increasing cruise speed without
too much increasing of fuel
consumption
Given :
- altitude
　
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