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at higher altitude
5 - Maximum cruise altitude
A project supported by AIRBUS and the CAAC
Date of the module
SR
M
m3
m2
m1
ISA + 20
ISA or
below
Cruise Mach
Engine limitation Maximum Cruise Thrust
Flying at Zp2, with the same weight
would require a thrust higher than MCrT
Zp2 > Zp1
5 - Maximum cruise altitude
A project supported by AIRBUS and the CAAC
Date of the module
SR
M
m3
m2
m1
ISA + 20
ISA or
below
Cruise Mach
Engine limitation Maximum Cruise Thrust
Only lighter weights can be flown at higher
altitude with the same cruise Mach
Zp2 > Zp1
5 - Maximum cruise altitude
A project supported by AIRBUS and the CAAC
Date of the module
SR
M
m3
m2
m1
ISA + 20
ISA or
below
Cruise Mach
Engine limitation Maximum Cruise Thrust
Zp2 is the maximum cruise altitude for m3
in ISA condition, at this cruise Mach number
Zp2 > Zp1
5 - Maximum cruise altitude
A project supported by AIRBUS and the CAAC
Date of the module
Definition :
For a given aircraft weight, it is the maximum
altitude at maximum cruise thrust in level flight with a
given Mach number .
5 - Maximum cruise altitude
= f(temp.)
A project supported by AIRBUS and the CAAC
Date of the module
ISA or below
ISA + 20
Maximum cruise altitude
decreases when :
- weight increases
- temperature increases
- Mach increases
Zp
weights
Max cruise altitude
M
5 - Maximum cruise altitude
A project supported by AIRBUS and the CAAC
Date of the module
Zp
weights
ISA or below
ISA + 20
Max cruise altitude
engine-limited area
M
5 - Maximum cruise altitude
A project supported by AIRBUS and the CAAC
Date of the module
Cruise at ECON MACH Zp
weights
ISA or below
ISA + 20
Max cruise altitude
Optimum altitude
ECON Mach
iso-Mach curves
M
5 - Maximum cruise altitude
Mach depends on :
altitude
weight
iso-Mach curves are
parallel to optimum
altitude
A project supported by AIRBUS and the CAAC
Date of the module
Effect of wind on optimum
altitude :
if wind is more
favourable at lower
altitude, it may be worth
flying at this altitude to
increase the ground
specific range.
Zp
weights
ISA or below
ISA + 20
Max cruise altitude
Optimum altitude
wind deviation for constant ground SR
20
40
60
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
LIFT RANGE :
On level flight mg = 0.7 S P CL M2
When CL = CLmax lift limit
(if increases, stall occurs)
Lift range is associated with CLmax M2 curve
6 - Buffet limit
A project supported by AIRBUS and the CAAC
Date of the module
1
CL max M2
M
1
CL max
M
Compressibility effect
6 - Buffet limit
A project supported by AIRBUS and the CAAC
Date of the module
CL max M2
M
1
mg = 0.7 S P CLmaxM2
given weight
Zp
lift range
Mmin Mmax
Zp max Lift ceiling
Level flight (no load factor)
6 - Buffet limit
At given weight,
to each CLmax M2
corresponds one altitude
(static Pressure)
When Zp increases, the lift
range decreases.
lift ceiling
A project supported by AIRBUS and the CAAC
Date of the module
While maneuvering, the aeroplane suffers load factors
mg n mg
buffet limit : n mg = 0.7 S P CLmaxM2
buffet = severe vibrations just before stall occurs
6 - Buffet limit
At given altitude, and given weight, to each CLmaxM2
corresponds one load factor
A project supported by AIRBUS and the CAAC
Date of the module
Mach
n
Zp1
given weight
6 - Buffet limit
Mmin Mmax
n1
At given weight and altitude, the aeroplane can suffer a load
factor equal to n1 before buffeting at Mmin (or Mmax).
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