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when thrust > drag
climb
Thrust and drag
A project supported by AIRBUS and the CAAC
Date of the module
1 - International standard atmosphere
2 - Altimetry principle
3 - Operating speeds
4 - Flight mechanics
Table of Contents
A project supported by AIRBUS and the CAAC
Date of the module
Balance of forces for steady level flight at
constant speed
lift
thrust
weight = mg
drag
lift = weight
thrust = drag
A project supported by AIRBUS and the CAAC
Date of the module
Lift equation :
Weight = ½ S (TAS)2 CL
Drag equation :
Thrust = ½ S (TAS)2 CD
Power equation :
Power = Thrust × TAS = ½ S (TAS)3 CD
A project supported by AIRBUS and the CAAC
Date of the module
As a function of Mach number :
Weight = 0.7 S PS M2 CL
Thrust = 0.7 S PS M2 CD
As a function of P0 :
the pressure ratio = PS/P0 is introduced
(P0 pressure at ZP = 0) :
Weight / = 0.7 S P0 M2 CL
Thrust / = 0.7 S P0 M2 CD
A project supported by AIRBUS and the CAAC
Date of the module
Balance of forces in climb Gza
TAS
Gx
Gxa
W= mg
Gz
L
T D
ground
datum line
aerodynamics
datum line
aircraft
datum line
: climb angle
: angle of attack
flight attitude
A project supported by AIRBUS and the CAAC
Date of the module
angle of attack
climb angle
climb
Thrust
climb angle
TAS
flight attitude
TAS
TAS
Rate of
climb
(RC)
Climb Angle and Rate of Climb
Angle of attack
Thrust
0
climb angle
RC = TAS sin
A project supported by AIRBUS and the CAAC
Date of the module
Longitudinal axis :
Thrust = Drag + weight sin
Vertical axis :
Lift = Weight cos
if is small sin tan cos 1
Thrust = Drag + Weight
Lift = Weight
= Thrust - Drag
Weight
A project supported by AIRBUS and the CAAC
Date of the module
Thrust as a function of speed
D,T
Speed
thrust
drag
Given
m, t°C, Zp,
thrust lever position
A project supported by AIRBUS and the CAAC
Date of the module
Expression of the climb angle :
Expression of the rate of climb
RC = TAS .
= 100 Thrust
Weight
1
L/D
RC (ft/mn) TAS (kt) . (%)
A project supported by AIRBUS and the CAAC
Date of the module
Balance of forces in descent
TAS
Gx
Gxa
Gza Gz
L
W= mg
T D
ground
datum line
aerodynamics
datum line
aircraft
datum line
: descent angle
: angle of attack
flight attitude
A project supported by AIRBUS and the CAAC
Date of the module
Gradient of descent :
if Thrust 0 (Idle)
Rate of descent :
= Thrust - Drag
Weight
< 0
= - 100 1
L/D
RC (ft/mn) TAS (kt) . (%)
A project supported by AIRBUS and the CAAC
Date of the module
D/
M
increasing W/
D/as a function of Mach number
A project supported by AIRBUS and the CAAC
Date of the module
gradient
D,T
Speed
thrust
drag
climb
Speed
max
L/Dmax
Given
m, t°C, Zp
cruise speed
climb speeds
Climb gradient
versus speed
Climb gradient is maximum
when the Drag is minimum
or L/D maximum
A project supported by AIRBUS and the CAAC
Date of the module
• Table of contents
• Flight operations duties
• European Applicable Regulation
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