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IL-76MD-yasim.xml
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IL-76MD-yasim.xml
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<?xml version="1.0" encoding="ISO-8859-1"?>
<!--
Copyright (C) Herbert Wagner Nov2016
see Read-Me.txt for all copyrights in the base folder of this aircraft
-->
<!-- Ilyushin Il-76 : BARANGER Emmanuel (2016) / update to version MD by Herbert Wagner 10/2016
Sources : https://en.wikipedia.org/wiki/Ilyushin_Il-76
Wingspan : 50.50 m ( 165 ft 8 in )
Lenght : 46.59 m ( 152 ft 10 in )
Height : 14.76 m ( 48 ft 5 in )
Empty weight : 92500 kg ( 203962 lb )
Engines : 4 x Aviadvigatel PS-90-76 turbofans (32000 lbf each )
Max speed : 900 km/h (490 ) Mach 0.82 depending on altitude
YASim solution results: Orig
Iterations: 1490
Drag Coefficient: 31.0667
Lift Ratio: 553.429
Cruise AoA: 0.898545
Tail Incidence: -1.32107
Approach Elevator: -0.299533
CG: 5.245, 0.010, -1.521 orig
YASim solution results: HerbyW
Iterations: 1215
Drag Coefficient: 24.2235
Lift Ratio: 170.611
Cruise AoA: 1.43628
Tail Incidence: -2.37312
Approach Elevator: -0.277629
CG: 5.205, 0.010, -1.556
YASim solution results: speed +30
Iterations: 1176
Drag Coefficient: 21.7203
Lift Ratio: 190.207
Cruise AoA: 1.216
Tail Incidence: -2.00719
Approach Elevator: -0.298373
CG: 5.205, 0.010, -1.556
YASim solution results:
Iterations: 1108
Drag Coefficient: 22.2106
Lift Ratio: 169.587
Cruise AoA: 0.815191
Tail Incidence: -1.57191
Approach Elevator: -0.33555
CG: 5.205, 0.010, -1.556
YASim solution results: new fuselage elements camber 0.02
Iterations: 1208
Drag Coefficient: 20.0481
Lift Ratio: 207.347
Cruise AoA: 1.2069
Tail Incidence: -2.02059
Approach Elevator: -0.31807
CG: 5.399, 0.047, -1.644
YASim solution results: camber 0.05
Iterations: 1138
Drag Coefficient: 20.4983
Lift Ratio: 184.873
Cruise AoA: 0.807334
Tail Incidence: -1.58822
Approach Elevator: -0.357786
CG: 5.399, 0.047, -1.644
YASim solution results: camber 0.06
Iterations: 1115
Drag Coefficient: 20.6482
Lift Ratio: 178.28
Cruise AoA: 0.674526
Tail Incidence: -1.44449
Approach Elevator: -0.371045
CG: 5.399, 0.047, -1.644
YASim solution results: camber 0.07
Iterations: 1087
Drag Coefficient: 20.7982
Lift Ratio: 172.07
Cruise AoA: 0.54193
Tail Incidence: -1.301
Approach Elevator: -0.384265
CG: 5.399, 0.047, -1.644
YASim solution results: camber 0.1
Iterations: 998
Drag Coefficient: 21.1748
Lift Ratio: 156.079
Cruise AoA: 0.144233
Tail Incidence: -0.870633
Approach Elevator: -0.425335
CG: 5.399, 0.047, -1.644
YASim solution results:
Iterations: 997
Drag Coefficient: 21.1748
Lift Ratio: 156.078
Cruise AoA: 0.144253
Tail Incidence: -0.870665
Approach Elevator: -0.425295
CG: 5.399, 0.047, -1.644
YASim solution results: flaps lift 1.3 < 1.4 drag 1.9
Iterations: 1105
Drag Coefficient: 20.82
Lift Ratio: 137.179
Cruise AoA: 0.451578
Tail Incidence: -1.35391
Approach Elevator: -0.47121
CG: 5.399, 0.047, -1.644
YASim solution results: flaps lift 1.5 drag 1.9
Iterations: 1191
Drag Coefficient: 20.4707
Lift Ratio: 122.828
Cruise AoA: 0.756452
Tail Incidence: -1.83402
Approach Elevator: -0.516155
CG: 5.399, 0.047, -1.644
Specifications (Il-76TD-90)
General characteristics
Crew: 5
Payload: 42 tonnes (Il-76M), 48 tonnes (Il-76MD), 60 tonnes (Il-76MD-90A) ()
Length: 46.59 m (152 ft 10 in)
Wingspan: 50.5 m (165 ft 8 in)
Height: 14.76 m (48 ft 5 in)
Wing area: 300.0 m² (3,229.2 ft²)
Empty weight: 92,500 kg (Il-76TD-90)[nb 1] (203,962 lb)
Max. takeoff weight: 195,000 kg (Il-76)[nb 2] (429,975 lb (Il-76TD-90))
Powerplant: 4 × Aviadvigatel PS-90-76 turbofans, 142 kN (32,000 lbf) or 14,500 kgf[66] each
Performance
Maximum speed: 900 km/h (490 kt, 560 mph) Mach 0.82 depending on altitude
Range: 5,000 km (2,700 nmi) for (Il-76MD-90A/TD-90VD) with 52 tonne payload; 4,000 km (Il-76M/T); 4,400 km (Il-76MD/TD), 4,200 km (Il-76MF/TF)
Service ceiling: 13,000 m (42,700 ft)
Wing loading: 566.7 kg/m² (Il-76M/T)[nb 3] (116.05 lb/ft² (Il-76M/T), 129.72 lb/ft² (Il-76MD/TD))
Thrust/weight: (Il-76)[nb 4]
minimal landing run: 450 m with thrust reversal
92,000 kg (Il-76MD/TD), 104,000 kg (Il-76MF/TF)
for other models: 170,000 kg (Il-76M/T), 190,000 kg Il-76MD/TD), 210,000 kg (Il-76MF/TF)
633.3 kg/m² (Il-76MD/TD)
0.282 (Il-76M/T), 0.252 (Il-76MD/TD), 0.228 (Il-76MF/TF)
Armament
Guns: 2× 23 mm cannon in radar-directed manned turret at base of tail
Bombs: Some military models have 2 hardpoints under each outer wing capable of supporting 500 kg bombs.
Il-76MD
Improved military transport version, (modifitseerovannyy Dahl'ny - modified, long-range).
Il-76MD Skal'pel-MT
- Mobile Hospital
Il-76M / Il-76MD
Built without military equipment but designated as Ms and MDs (Gordon - 'Falsies')
Il-76MD-90
An Il-76MD with quieter and more economical Aviadvigatel PS-90 high-bypass turbofan engines.
Il-76MDM
modernized Il-76MD for the Russian Air Force.
Il-76MD-90A
An updated version with a new glass cockpit, updated avionics,
new internal wing structure and Aviadvigatel PS-90 engines. It was also known as Il-476 while in development.
Il-76MD tanker
Iraqi Air Force tanker conversions.
http://www.airvectors.net/avil76.html
Il-76MD
Performance
General Data
Il-76MD military transport aircraftis based on the Il-76M serial productionmilitary transport aircraft.
The aircraft is meant for parachute operations and landing of military personnel, military equipment,
cargoes, fuel and containers. By reinforcing its main structural elements (airframe and landing gear),
the maximum takeoff weight and commercial load have been increased.
Show more
Top thrust (SI system, H=0)
4х12000kgf
Another figure
Main technical characteristics
Dimensional characteristics
Length, m 46,6
Height, m 14,76
Wingspan, m 50,5
Wing area, sq. m. 300
Fuselage diameter, m 4,8
Power plant parameters
Number x engine type 4 x turbojet engine
Engine model D-30KP series 2
Top thrust (SI system, H=0), kgf 12 000
Weight parameters
Maximum takeoff weight, tons 190 (210 t = 462970 lbs)
Maximum payload, tons 48
Fuel tank capacity, l 109 500
Aircraft performance
Cruising speed, km/h 750–780
Flight altitude, m 9 100–12 100
Flight range with payload of 40 tons, km 4 200
Takeoff distance, m 1 700
Landing distance, m 930
Number of seats
Crew, persons 7 (6)
Passengers, persons single-deck version:
126 paratroopers
145 military personnel
114 wounded
Double-deck version:
225 military personnel
Freight compartment parameters
Length x Width x Height, m 24,54x3,45x3,4
Volume, cubic meters 321
Specified life
Calendar operating life, years 45
Number of flights 8 000
Number of flight hours, hr. 12 000
Il-76MD-90
Performance
General Data
Il-76MD-90 military transport aircraftis based on the Il-76MD series productionmilitary transport aircraftand is designed for landing and parachuting of military personnel, equipment and various cargos.
The aircraft has more powerful and economic PS-90A-76 engines, which meet ICAO requirements for noise and harmful emissions. Installation of new engines allowed for increasing cost efficiency of the aircraft significantly, due to reduced average fuel consumption in cruise flight, increasingflying range and commercial load, and reducing direct operational costs.
Top thrust (SI system, H=0)
4х16000kgf
Another figure
Main technical characteristics
Dimensional characteristics
Length, m 46,6
Height, m 14,76
Wingspan, m 50,5
Wing area, sq. m. 300
Fuselage diameter, m 4,8
Power plant parameters
Number x engine type 4 x turbojet engine
Engine
PS-90A-76
Top thrust (SI system, H=0), kgf 16 000
Weight parameters
Maximum takeoff weight, tons 195
Maximum payload, tons 50
Fuel tank capacity, l 109 500
Aircraft performance
Cruising speed, km/h 750–800
Flight altitude, m 9 100–12 100
Flight range with payload of 40 tons, km 5 400
Takeoff distance, m 1 300
Landing distance, m 930
Number of seats
Crew, persons 6
Passengers, persons single-deck version:
126 paratroopers
145 military personnel
114 wounded
Double-deck version:
225 military personnel
Freight compartment parameters
Length x Width x Height, m 24,54x3,45x3,4
Volume, cubic meters 321
Specified life
Calendar operating life, years 30
Number of flights 4 000
Number of flight hours, hr. 6 000
Il-76MD-90A
Performance
Media
3D tour
General Data
Il-76MD-90A is created on the basis of mass production Il-76MD aircraftfor the purposes of further improvement of this type of aircraft and extension of its transportation capacity by way of modernizing the wingand installing more powerful, economical and quiet PS-90A-76engines, instead of D-30KP-2 engines.
Il-76MD-90A is meant for parachuting and landing of military personnel, military equipment, cargoes, fuel and containers.
Modified Il-76MD-90A aircraft complies with standards for noise level determined by requirements of Appendix 16 Chapter 4 of ICAO standards, and for emission of harmful substances into the atmosphere. All this, along with the opportunities for aircraft navigation by RNP-1 requirements allowed for expanding the flight geography of Il-76MD-90A both in local and international airlines.
Show more
Top thrust (SI system, H=0)
4х16000kgf
Another figure
Main technical characteristics
Dimensional characteristics
Length, m 46,6
Height, m 14,76
Wingspan, m 50,5
Wing area, sq. m. 300
Fuselage diameter, m 4,8
Power plant parameters
Number x engine type 4 x turbojet engine
Engine
PS-90A-76 ,142 kN (32,000 lbf) or 14,500 kgf
Top thrust (SI system, H=0), kgf 16 000
Weight parameters
Maximum takeoff weight, tons 210
Maximum payload, tons 52 (with extension to 60)
Fuel tank capacity, l 109 500
Aircraft performance
Cruising speed, km/h 750–800
Flight altitude, m 9 100–12 100
Flight range with payload of 52 tons, km 5 000
Takeoff distance, m 1 540
Landing distance, m 1050
Number of seats
Crew, persons 6
Passengers, persons single-deck version:
126 paratroopers
145 military personnel
114 wounded
Double-deck version:
225 military personnel
Freight compartment parameters
Length x Width x Height, m 24,54x3,45x3,4
Volume, cubic meters 321
Specified life
Calendar operating life, years 30
Number of flights 8 000
Number of flight hours, hr. 10 000
-->
<airplane mass="203962" version="YASIM_VERSION_CURRENT">
<approach speed="110" aoa="2" fuel="0.2">
<control-setting axis="/controls/engines/engine[0]/throttle-lever" value="0.5"/>
<control-setting axis="/controls/engines/engine[1]/throttle-lever" value="0.5"/>
<control-setting axis="/controls/engines/engine[2]/throttle-lever" value="0.5"/>
<control-setting axis="/controls/engines/engine[3]/throttle-lever" value="0.5"/>
<control-setting axis="/controls/flight/flaps" value="1.0"/>
<control-setting axis="/controls/flight/slats" value="1.0"/>
<control-setting axis="/controls/flight/spoilers" value="0.0"/>
<control-setting axis="/controls/gear/gear-down" value="1"/>
</approach>
<cruise speed="470" alt="36000" fuel="0.8">
<control-setting axis="/controls/engines/engine[0]/throttle-lever" value="0.85"/>
<control-setting axis="/controls/engines/engine[1]/throttle-lever" value="0.85"/>
<control-setting axis="/controls/engines/engine[2]/throttle-lever" value="0.85"/>
<control-setting axis="/controls/engines/engine[3]/throttle-lever" value="0.85"/>
<control-setting axis="/controls/flight/flaps" value="0.0"/>
<control-setting axis="/controls/flight/slats" value="0.0"/>
<control-setting axis="/controls/flight/spoilers" value="0.0"/>
<control-setting axis="/controls/gear/gear-down" value="0"/>
</cruise>
<cockpit x="24.41012" y="0.41799" z="-0.67554"/>
<!-- Fuselage -->
<fuselage ax=" 23.326" ay=" 0.000" az="-3.506" bx=" 19.383" by=" 0.000" bz="-3.506" width="4.724" taper="0.1" midpoint="1.0"/>
<fuselage ax=" 19.383" ay=" 0.000" az="-3.506 " bx=" -5.563" by=" 0.000" bz="-3.506" width="4.70" taper="1.0" midpoint="1.0"/>
<fuselage ax=" -5.563" ay=" 0.000" az="-3.506" bx="-19.762" by=" 0.000" bz="-0.259" width="4.70" taper="0.1" midpoint="0.0"/>
<!-- Tail -->
<fuselage ax=" -13.93" ay=" 0.0" az="6.833" bx=" -22.93" by=" 0.0" bz="6.713" width="0.99" taper="1.0" midpoint="1.0"/>
<!-- GearBox -->
<fuselage ax=" 7.984" ay=" 2.427" az="-4.865" bx=" -4.016" by=" 2.427" bz="-4.865" width="1.8" taper="1.0" midpoint="1.0"/>
<fuselage ax=" 7.984" ay="-2.427" az="-4.865" bx=" -4.016" by="-2.427" bz="-4.865" width="1.8" taper="1.0" midpoint="1.0"/>
<!-- Engine exterior left -->
<fuselage ax=" 9.653" ay=" 10.784" az="-3.425" bx=" 3.653" by=" 10.784" bz="-3.425" width="1.7" taper="1.0" midpoint="1.0"/>
<!-- Engine interior left -->
<fuselage ax="11.683" ay=" 6.473" az="-3.193" bx=" 5.683" by=" 6.473" bz="-3.193" width="1.7" taper="1.0" midpoint="1.0"/>
<!-- Engine interior right -->
<fuselage ax="11.683" ay=" 6.473" az="-3.193" bx=" 5.683" by=" 6.473" bz="-3.193" width="1.7" taper="1.0" midpoint="1.0"/>
<!-- Engine exterior right -->
<fuselage ax=" 9.653" ay="-10.784" az="-3.425" bx=" 3.653" by="-10.784" bz="-3.425" width="1.7" taper="1.0" midpoint="1.0"/>
<!-- Wing -->
<wing x="5.906" y="1.797" z="-0.821"
chord="10.65"
length="25.39"
taper="0.26"
sweep="21"
dihedral="-3"
camber="0.1">
<stall aoa="10.0" width="3" peak="1.3"/>
<flap0 start="0.0" end="0.75" lift="1.5" drag="1.9"/>
<flap1 start="0.75" end="0.95" lift="1.3" drag="1.3"/>
<slat start="0.1" end="0.95" aoa="4" drag="1.4"/>
<spoiler start="0.2" end="0.75" lift="0.8" drag="4"/>
<control-input axis="/controls/flight/flaps" control="FLAP0"/>
<control-input axis="/controls/flight/aileron" control="FLAP1" split="true"/>
<control-input axis="/controls/flight/aileron-trim" control="FLAP1" split="true"/>
<control-input axis="/controls/flight/slats" control="SLAT"/>
<control-input axis="/controls/flight/spoilers" control="SPOILER"/>
<control-output control="FLAP0" side="left" prop="/surface-positions/flap-pos-norm"/>
<control-output control="FLAP0" side="right" prop="/surface-positions/flap-pos-norm"/>
<control-output control="FLAP0" prop="/surface-positions/flap-pos-norm"/>
<control-output control="FLAP1" side="left" prop="/surface-positions/left-aileron-pos-norm"/>
<control-output control="FLAP1" side="right" prop="/surface-positions/right-aileron-pos-norm"/>
<control-output control="SLAT" prop="/surface-positions/slat-pos-norm"/>
<control-output control="SPOILER" prop="/surface-positions/spoiler-pos-norm"/>
<control-speed control="FLAP0" transition-time="45"/>
<control-speed control="FLAP1" transition-time="1.0"/>
<control-speed control="SLAT" transition-time="10"/>
<control-speed control="SPOILER" transition-time="1.0"/>
</wing>
<!-- Elevator -->
<hstab x="-18.103" y="0" z="7.016"
chord="5.551"
length="9.6"
sweep="25"
taper="0.4">
<stall aoa="20" width="3" peak="1.5"/>
<flap0 start="0" end="1" lift="1.6" drag="1.1"/>
<control-input axis="/controls/flight/elevator" control="FLAP0"/>
<control-input axis="/controls/flight/elevator-trim" control="FLAP0"/>
<control-output control="FLAP0" prop="/surface-positions/elevator-pos-norm"/>
<control-speed control="FLAP0" transition-time="15.0"/>
</hstab>
<!-- Ruder -->
<vstab x="-14.890" y="0" z="-0.773"
chord="8.2"
length="8.5"
sweep="30"
taper="0.7">
<stall aoa="18" width="3" peak="1.5"/>
<flap0 start="0" end="1" lift="1.6" drag="1.6"/>
<control-input axis="/controls/flight/rudder" control="FLAP0" invert="true"/>
<control-output control="FLAP0" prop="/surface-positions/rudder-pos-norm"/>
<control-speed control="FLAP0" transition-time="2.0"/>
</vstab>
<!-- Engines source : https://en.wikipedia.org/wiki/Aviadvigatel_PS-90
name : Aviadvigatel PS-90
type : Twin-spool high bypass turbofan with a single-stage fan
power cruise : 38400 lbf
weight : 2950 kg ( 6500 lb )
-->
<!-- Engine left exterior -->
<jet x="7.381" y="10.756" z="-3.415"
mass="6500"
thrust="38400"
n1-idle="26"
n1-max="99.2"
n2-idle="60"
n2-max="102.5"
egt="840"
tsfc="0.5"
reverse="0.33">
<actionpt x="3.518" y="10.754" z="-3.408"/>
<control-input axis="/controls/engines/engine[0]/throttle-lever" control="THROTTLE" src0="0" src1="1" dst0="0.05" dst1="1"/>
<control-input axis="/controls/engines/engine[0]/reverser" control="REVERSE_THRUST"/>
<control-output control="REVERSE_THRUST" prop="/surface-positions/reverser-norm[0]"/>
<control-speed control="REVERSE_THRUST" transition-time="1.5"/>
</jet>
<!-- Engine left interior -->
<jet x="9.431" y="6.400" z="-3.158"
mass="6500"
thrust="38400"
n1-idle="26"
n1-max="99.2"
n2-idle="60"
n2-max="102.5"
egt="840"
tsfc="0.5"
reverse="0.33">
<actionpt x="5.568" y="6.396" z="-3.150"/>
<control-input axis="/controls/engines/engine[1]/throttle-lever" control="THROTTLE" src0="0" src1="1" dst0="0.05" dst1="1"/>
<control-input axis="/controls/engines/engine[1]/reverser" control="REVERSE_THRUST"/>
<control-output control="REVERSE_THRUST" prop="/surface-positions/reverser-norm[1]"/>
<control-speed control="REVERSE_THRUST" transition-time="1.5"/>
</jet>
<!-- Engine right interior-->
<jet x="9.431" y="-6.400" z="-3.158"
mass="6500"
thrust="38400"
n1-idle="26"
n1-max="99.2"
n2-idle="60"
n2-max="102.5"
egt="840"
tsfc="0.5"
reverse="0.33">
<actionpt x="5.568" y="-6.396" z="-3.150"/>
<control-input axis="/controls/engines/engine[2]/throttle-lever" control="THROTTLE" src0="0" src1="1" dst0="0.05" dst1="1"/>
<control-input axis="/controls/engines/engine[2]/reverser" control="REVERSE_THRUST"/>
<control-output control="REVERSE_THRUST" prop="/surface-positions/reverser-norm[2]"/>
<control-speed control="REVERSE_THRUST" transition-time="1.5"/>
</jet>
<!-- Engine right exterior-->
<jet x="7.381" y="-10.756" z="-3.415"
mass="6500"
thrust="38400"
n1-idle="26"
n1-max="99.2"
n2-idle="60"
n2-max="102.5"
egt="840"
tsfc="0.5"
reverse="0.33">
<actionpt x="3.518" y="-10.754" z="-3.408"/>
<control-input axis="/controls/engines/engine[3]/throttle-lever" control="THROTTLE" src0="0" src1="1" dst0="0.05" dst1="1"/>
<control-input axis="/controls/engines/engine[3]/reverser" control="REVERSE_THRUST"/>
<control-output control="REVERSE_THRUST" prop="/surface-positions/reverser-norm[3]"/>
<control-speed control="REVERSE_THRUST" transition-time="1.5"/>
</jet>
<!-- Noze wheel -->
<gear x="14.70944" y="0" z="-7.22"
retract-time="7"
compression="0.3"
spring="1"
damp="1.0"
sfric="1.6"
dfric="0.7">
<control-input axis="/controls/flight/rudder" control="STEER" src0="-1.0" dst0="-0.8052" src1="1.0" dst1="0.8052" square="true"/>
<control-input axis="/controls/gear/gear-down" control="EXTEND"/>
<control-input axis="/controls/gear/brake-parking" control="BRAKE"/>
<control-speed control="EXTEND" transition-time="7"/>
<control-speed control="BRAKE" transition-time="0.7"/>
<control-speed control="STEER" transition-time="2.5"/>
<control-output control="STEER" prop="/gear/gear[0]/steering-norm"/>
<control-output control="EXTEND" prop="/gear/gear[0]/position-norm"/>
</gear>
<!-- Left wheel 1 -->
<gear x="3.18118" y="3.19368" z="-7.45"
retract-time="7"
compression="0.8"
spring="1.2"
damp="1.0"
sfric="1.6"
dfric="0.8">
<control-input axis="/controls/gear/brake-left" control="BRAKE"/>
<control-input axis="/controls/gear/brake-parking" control="BRAKE"/>
<control-input axis="/controls/gear/gear-down" control="EXTEND"/>
<control-output control="EXTEND" prop="/gear/gear[1]/position-norm"/>
<control-speed control="BRAKE" transition-time="0.7"/>
<control-speed control="EXTEND" transition-time="7"/>
</gear>
<!-- Left wheel 2 -->
<gear x="0.67003" y="3.19368" z="-7.45"
retract-time="7"
compression="0.8"
spring="1.2"
damp="1.0"
sfric="1.6"
dfric="0.8">
<control-input axis="/controls/gear/brake-left" control="BRAKE"/>
<control-input axis="/controls/gear/brake-parking" control="BRAKE"/>
<control-input axis="/controls/gear/gear-down" control="EXTEND"/>
<control-output control="EXTEND" prop="/gear/gear[1]/position-norm"/>
<control-speed control="BRAKE" transition-time="0.7"/>
<control-speed control="EXTEND" transition-time="7"/>
</gear>
<!-- Right wheel 1 -->
<gear x="3.18118" y="-3.19368" z="-7.45"
retract-time="7"
compression="0.8"
spring="1.2"
damp="1.0"
sfric="1.6"
dfric="0.8">
<control-input axis="/controls/gear/brake-right" control="BRAKE"/>
<control-input axis="/controls/gear/brake-parking" control="BRAKE"/>
<control-input axis="/controls/gear/gear-down" control="EXTEND"/>
<control-output control="EXTEND" prop="/gear/gear[2]/position-norm"/>
<control-speed control="BRAKE" transition-time="0.7"/>
<control-speed control="EXTEND" transition-time="7"/>
</gear>
<!-- Right wheel 2 -->
<gear x="0.67003" y="-3.19368" z="-7.45"
retract-time="7"
compression="0.8"
spring="1.2"
damp="1.0"
sfric="1.6"
dfric="0.8">
<control-input axis="/controls/gear/brake-right" control="BRAKE"/>
<control-input axis="/controls/gear/brake-parking" control="BRAKE"/>
<control-input axis="/controls/gear/gear-down" control="EXTEND"/>
<control-output control="EXTEND" prop="/gear/gear[2]/position-norm"/>
<control-speed control="BRAKE" transition-time="0.7"/>
<control-speed control="EXTEND" transition-time="7"/>
</gear>
<!-- Total : 187044 lbs in 6 tanks - 31174 each -->
<tank x="5" y=" 4.361" z="-1.261" capacity="31714"/>
<tank x="4" y=" 7.361" z="-1.261" capacity="31714"/>
<tank x="3" y=" 10.361" z="-1.261" capacity="31714"/>
<tank x="3" y="-10.361" z="-1.261" capacity="31174"/>
<tank x="4" y=" -7.361" z="-1.261" capacity="31174"/>
<tank x="5" y=" -4.361" z="-1.261" capacity="31174"/>
<!-- Mass distribution -->
<ballast x="26" y="0" z="-4" mass="40850"/>
<weight x="20.0" y="0" z="1.67" mass-prop="/sim/weight[0]/weight-lb"/>
<weight x="4.9" y="0" z="-3" mass-prop="/sim/weight[1]/weight-lb"/>
<weight x="4.9" y="0" z="-3" mass-prop="/sim/weight[2]/weight-lb"/>
</airplane>