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SEPECAT-Jaguar-vsp.xml
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<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://raw.githubusercontent.com/JSBSim-Team/jsbsim/master/JSBSimScript.xsl"?>
<fdm_config name="SEPECAT-Jaguar" version="2.0" release="BETA"
xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
xsi:noNamespaceSchemaLocation="http://raw.githubusercontent.com/JSBSim-Team/jsbsim/master/JSBSim.xsd">
<fileheader>
<author>Richard Harrison</author>
<filecreationdate>2020-04-30</filecreationdate>
<version>1.0</version>
<copyright>Copyright (C) 2020 Richard Harrison, All rights reserved</copyright>
<description></description>
<note>Built using VSPAERO.Aircraft origin for measurements is the nose
ref: Data from Jane's All The World's Aircraft 1980–81,[28]
General characteristics
Crew: 1 (A and S) ; 2 (B and E)
Length: (A and S) with minor variations dependent on nose configuration: 16.83 m (55 ft 3 in)
(B and E) with minor variations dependent on nose probe type (AAR or pitot) 17.53 m (57.5 ft)
Wing loading: 649.3 kg/m2 (133.0 lb/sq ft) maximum
Wingspan: 8.69 m (28 ft 6 in)
Height: 4.89 m (16 ft 1 in)
Wing area: 24.18 m2 (260.3 sq ft)
Aspect ratio: 3.12
Empty weight: 7000 kg (15432 lb)
Gross weight: 10954 kg (24149 lb) full internal fuel and 120 rpg
Max takeoff weight: 15700 kg (34613 lb) with external stores
Fuel capacity: internal 4200 l (1100 US gal; 920 imp gal)
three drop tanks on inboard and centreline pylons 1200 l (320 US gal; 260 imp gal) (each)
Mainplane
Span 8.690m (28 ft 6.13 in)
Sweepback at 25% chord 40 deg. 2 mm
Thickness ratio 5 to 5.5%
Aspect ratio 3.12
Anhedral 3 deg.
Total area 24.03 m2 (258.66 ft2)
Tail unit Fin :
Sweepback at 25% chord 46 deg. 30 min
Thickness ratio 5%
Area (with rudder) 3.71 m2 (39.93 ft2)
Tailplane
Span 4.530 m (14 ft 10.35 in)
Sweepback at 25% chord 40 deg. 20 min
Thickness ratio 5%
Anhedral 10 deg.
Area 3.97 m (42.73 ft2)
Landing gear
Wheel base 5.69 1 m (18 ft 8.05 in)
Track 2.400 m (7 ft 10.49in)
Nose undercarriage tyre 550 x 250 x 152
Main undercarriage tyre 615 x 225 x 254
Propulsion units
Mass 811 kg (1784 lb)
Maximum thrust (dry) 2452 daN (5515 lbf)
Maximum thrust (with afterburnmer) 3668 daN (8245 lbf)
Powerplant:
Mass 867 kg (1915 lb)
2 × Rolls-Royce Turbomeca Adour Mk.102 afterburning turbofan engines: 22.75 kN (5110 lbf) (each dry)
32.5 kN (7300 lbf) (each afterburner)
Performance
Maximum speed: at sea level 730 kt Mach 1.1
at 11,000 m (36,000 ft) 917 kt Mach 1.6
Landing speed: 115 kt
Take-off run: typical tactical load 580 m (1,900 ft)
Take-off run: typical tactical load to 15 m (49 ft): 940 m (3,080 ft)
Landing run typical tactical load from 15 m (49 ft): 785 m (2,575 ft)
Landing run: typical tactical load 470 m (1,540 ft)
Combat range: hi-lo-hi (internal fuel) 440 nm
lo-lo-lo (internal fuel) 310 nm
hi-lo-hi (with external fuel) 760 nm
lo-lo-lo (with external fuel) 490 nm
Ferry range: with full internal and external tanks 1027 nm
Service ceiling: 14000 m (46,000 ft)
g limits: +8.6 (ultimate load +12)
Time to altitude: 9,145 m (30,003 ft) in 1 minute 30 seconds[141]
Thrust/weight:
Adour Mk.102: 0.422
Adour Mk.104: 0.464
Adour Mk.811: 0.486
Armament
Guns: 2 × 30 mm (1.181 in) calibre DEFA cannon with up to 150 rounds/gun
Hardpoints: 5 (4× under-wing and 1× center-line) with a capacity of 10,000 lb (4,500 kg),with provisions to carry combinations of:
Rockets:
8× Matra rocket pods with 18× SNEB 68 mm rockets each
Missiles:
AS.37 Martel anti-radar missiles or
AS-30L laser guided air-to-ground missiles.
2× R550 Magic air-to-air missiles on overwing pylons
2× AIM-9 Sidewinder air-to-air missiles on overwing pylons
2× AIM-9 Sidewinder air-to-air missiles on outboard pylons
Bombs:
various unguided or laser-guided bombs or
2× WE177A nuclear bombs
1× AN-52 nuclear bomb
Other:
ECM protection pods
Reconnaissance Pod
ATLIS laser/electro-optical targeting pod
External drop tanks for extended range/loitering time
</note>
<note>Built with AeroTool 1.0.0.0: Options: AeroDetail=High, ExternalTanks, Flaps, Gear, GroundEffect, Mach, Speedbrake, WakeIterations=3</note>
<limitation></limitation>
<reference
refID="ZDAT/AED/2019/11-01"
author="Richard Harrison, [email protected]"
title="SEPECAT Jaguar Aerodynamic data built from vspaero; CG (8.0247, 0, -0.005)M"
date="November, 2019"
URL="http://www.zaretto.com/sites/zaretto.com/files/SEPECAT-Jaguar-data/rjh-zaretto-SEPECAT-Jaguar-aerodynamic-data-vspaero.pdf"
/>
<reference
refID="ZDAT/AED/2019/11-1"
author="Richard Harrison, [email protected]"
title="SEPECAT-Jaguar Aerodynamic"
date="November 2019"
URL="http://www.zaretto.com/sites/zaretto.com/files/SEPECAT-Jaguar-data/rjh-zaretto-SEPECAT-Jaguar-aerodynamic-data.pdf"
/>
</fileheader>
<metrics>
<wingarea unit="M2">24.15</wingarea>
<wingspan unit="M">8.543</wingspan>
<wing_incidence>1.52</wing_incidence>
<chord unit="M">3.317</chord>
<htailarm>0</htailarm>
<location unit="M" name="EYEPOINT">
<x>3.371</x>
<y>0</y>
<z>0.965</z>
</location>
<location unit="M" name="VRP">
<x>1.877</x>
<y>0</y>
<z>1.25</z>
</location>
<location unit="M" name="AERORP">
<x>8.6247</x>
<y>0</y>
<z>-0.005</z>
</location>
</metrics>
<mass_balance>
<ixx>3418</ixx>
<iyy>82395</iyy>
<izz>61297</izz>
<ixz>-804</ixz>
<emptywt unit="KG">7000</emptywt>
<location unit="M" name="CG">
<x>8.0247</x>
<y>0</y>
<z>-0.005</z>
</location>
<pointmass name="pylon-left-over-wing">
<weight unit="LBS">0</weight>
<location unit="M" name="Pointmass pylon-left-over-wing">
<x>8.8507</x>
<y>-2.08</y>
<z>0.12</z>
</location>
</pointmass>
<pointmass name="pylon-left-outboard-wing">
<weight unit="LBS">0</weight>
<location unit="M" name="Pointmass pylon-left-outboard-wing">
<x>9.0507</x>
<y>-2.98</y>
<z>-0.23</z>
</location>
</pointmass>
<pointmass name="pylon-left-inboard-wing">
<weight unit="LBS">0</weight>
<location unit="M" name="Pointmass pylon-left-inboard-wing">
<x>8.7507</x>
<y>-2.08</y>
<z>-0.23</z>
</location>
</pointmass>
<pointmass name="pylon-fuselage">
<weight unit="LBS">0</weight>
<location unit="M" name="Pointmass pylon-fuselage">
<x>8.6107</x>
<y>0</y>
<z>-0.875</z>
</location>
</pointmass>
<pointmass name="pylon-right-inboard-wing">
<weight unit="LBS">0</weight>
<location unit="M" name="Pointmass pylon-right-inboard-wing">
<x>8.7507</x>
<y>2.08</y>
<z>-0.23</z>
</location>
</pointmass>
<pointmass name="pylon-right-outboard-wing">
<weight unit="LBS">0</weight>
<location unit="M" name="Pointmass pylon-right-outboard-wing">
<x>9.0507</x>
<y>2.98</y>
<z>-0.23</z>
</location>
</pointmass>
<pointmass name="pylon-right-over-wing">
<weight unit="LBS">0</weight>
<location unit="M" name="Pointmass pylon-right-over-wing">
<x>8.8507</x>
<y>2.08</y>
<z>0.12</z>
</location>
</pointmass>
<pointmass name="internal-gun">
<weight unit="LBS">0</weight>
<location unit="M" name="Pointmass internal-gun">
<x>5.4147</x>
<y>0</y>
<z>-0.68</z>
</location>
</pointmass>
</mass_balance>
<propulsion>
<engine file="Adour804">
<location unit="M">
<x>12.916</x>
<y>-0.4127</y>
<z>-0.2</z>
</location>
<orient unit="DEG">
<roll>0</roll>
<pitch>6</pitch>
<yaw>0</yaw>
</orient>
<feed>8</feed>
<feed>7</feed>
<feed>6</feed>
<feed>5</feed>
<feed>4</feed>
<feed>3</feed>
<feed>2</feed>
<feed>1</feed>
<feed>0</feed>
<thruster file="direct">
<location unit="M">
<x>12.916</x>
<y>-0.4127</y>
<z>-0.2</z>
</location>
<orient unit="DEG">
<roll>0</roll>
<pitch>6</pitch>
<yaw>0</yaw>
</orient>
</thruster>
</engine>
<engine file="Adour804">
<location unit="M">
<x>12.916</x>
<y>0.4127</y>
<z>-0.2</z>
</location>
<orient unit="DEG">
<roll>0</roll>
<pitch>6</pitch>
<yaw>0</yaw>
</orient>
<feed>8</feed>
<feed>7</feed>
<feed>6</feed>
<feed>5</feed>
<feed>4</feed>
<feed>3</feed>
<feed>2</feed>
<feed>1</feed>
<feed>0</feed>
<thruster file="direct">
<location unit="M">
<x>12.916</x>
<y>0.4127</y>
<z>-0.2</z>
</location>
<orient unit="DEG">
<roll>0</roll>
<pitch>6</pitch>
<yaw>0</yaw>
</orient>
</thruster>
</engine>
<tank number="0" type="FUEL">
<!--0: FuselageFrontTank-->
<location unit="M">
<x>6.0827</x>
<y>0</y>
<z>0</z>
</location>
<capacity unit="LBS">1559</capacity>
<standpipe unit="LBS">80</standpipe>
<contents unit="LBS">1559</contents>
<priority>3</priority>
</tank>
<tank number="1" type="FUEL">
<!--1: FuselageCenterTank1-->
<location unit="M">
<x>7.6127</x>
<y>0</y>
<z>0</z>
</location>
<capacity unit="LBS">864</capacity>
<standpipe unit="LBS">40</standpipe>
<contents unit="LBS">864</contents>
<priority>4</priority>
</tank>
<tank number="2" type="FUEL">
<!--2: FuselageCenterTank2-->
<location unit="M">
<x>8.7257</x>
<y>0</y>
<z>0</z>
</location>
<capacity unit="LBS">1146</capacity>
<standpipe unit="LBS">60</standpipe>
<contents unit="LBS">1146</contents>
<priority>4</priority>
</tank>
<tank number="3" type="FUEL">
<!--3: FuselageRearTank-->
<location unit="M">
<x>11.0727</x>
<y>0</y>
<z>0</z>
</location>
<capacity unit="LBS">1962</capacity>
<standpipe unit="LBS">100</standpipe>
<contents unit="LBS">1962</contents>
<priority>3</priority>
</tank>
<tank number="4" type="FUEL">
<!--4: LeftWingTank-->
<location unit="M">
<x>9.2247</x>
<y>-2.09</y>
<z>0.005</z>
</location>
<capacity unit="LBS">820</capacity>
<standpipe unit="LBS">40</standpipe>
<contents unit="LBS">820</contents>
<priority>2</priority>
</tank>
<tank number="5" type="FUEL">
<!--5: RightWingTank-->
<location unit="M">
<x>9.2247</x>
<y>2.09</y>
<z>0.005</z>
</location>
<capacity unit="LBS">820</capacity>
<standpipe unit="LBS">40</standpipe>
<contents unit="LBS">820</contents>
<priority>2</priority>
</tank>
<tank number="6" type="FUEL">
<!--6: ExternalLeftWingTank-->
<location unit="M">
<x>8.7507</x>
<y>-2.08</y>
<z>-0.23</z>
</location>
<capacity unit="LBS">2037</capacity>
<standpipe unit="LBS">100</standpipe>
<contents unit="LBS">2037</contents>
<priority>1</priority>
</tank>
<tank number="7" type="FUEL">
<!--7: ExternalCentreTank-->
<location unit="M">
<x>8.6107</x>
<y>0</y>
<z>-0.875</z>
</location>
<capacity unit="LBS">2037</capacity>
<standpipe unit="LBS">100</standpipe>
<contents unit="LBS">2037</contents>
<priority>2</priority>
</tank>
<tank number="8" type="FUEL">
<!--8: ExternalRightWingTank-->
<location unit="M">
<x>8.7507</x>
<y>2.08</y>
<z>-0.23</z>
</location>
<capacity unit="LBS">2037</capacity>
<standpipe unit="LBS">100</standpipe>
<contents unit="LBS">2037</contents>
<priority>1</priority>
</tank>
</propulsion>
<system file="Propulsion"/>
<system file="autoflight"/>
<system file="jaguar-sas"/>
<system file="Aircraftcontrol"/>
<system file="jaguar-controls"/>
<system file="electrical"/>
<system file="hydraulics"/>
<ground_reactions file="Systems/ground-reactions"/>
<flight_control name="SEPECAT-Jaguar-FCS">
<channel name="extra-aero">
<!-- need %Cg in chord for moments [Xcg - Xref)/100] -->
<summer name="cg-x-offset-chord-in">
<input> inertia/cg-x-in</input>
<input> -metrics/aero-rp-x-in</input>
<output>inertia/cg-x-offset-chord-in</output>
</summer>
<!-- figure out the factor for the fuel tank aero -->
<pure_gain name="cg-x-chord-percent">
<description>Percent offset of the CoP from the CG</description>
<input>inertia/cg-x-offset-chord-in</input>
<gain> -0.01</gain>
<clipto>
<min> -1 </min>
<max> 1 </max>
</clipto>
<output> inertia/cg-x-mac-percent </output>
</pure_gain>
<fcs_function name="pb">
<description>PB Denormalization</description>
<function>
<product>
<property>aero/bi2vel</property>
<property>velocities/p-aero-rad_sec</property>
</product>
</function>
<output>aero/pb</output>
</fcs_function>
<fcs_function name="cbarq-2vo">
<description>For denormalization</description>
<function>
<product>
<property>aero/ci2vel</property>
<property>velocities/q-aero-rad_sec</property>
</product>
</function>
<output>aero/qb</output>
</fcs_function>
<fcs_function name="rb-2vo">
<description>For denormalization</description>
<function>
<product>
<property>aero/bi2vel</property>
<property>velocities/r-aero-rad_sec</property>
</product>
</function>
<output>aero/rb</output>
</fcs_function>
<fcs_function name="aero-cos-alpha">
<function>
<cos>
<property>aero/alpha-rad</property>
</cos>
</function>
<output>aero/cos-alpha</output>
</fcs_function>
<fcs_function name="aero-sin-alpha">
<function>
<sin>
<property>aero/alpha-rad</property>
</sin>
</function>
<output>aero/sin-alpha</output>
</fcs_function>
<fcs_function name="position/h-agl-m">
<description>Height above ground (meters)</description>
<function>
<product>
<property>position/h-agl-ft</property>
<value>0.3048</value>
</product>
</function>
<output>position/h-agl-m</output>
</fcs_function>
</channel>
</flight_control>
<aerodynamics>
<function name="aero/c/CFXB">
<description>BASE DRAG</description>
<table>
<independentVar lookup="row">aero/alpha-deg</independentVar>
<independentVar lookup="column">aero/beta-deg</independentVar>
<tableData>
-20 -15 -10 -7 -5 -2 0 2 5 7 10 15 20
-20 0.19929 0.19607 0.19251 0.19100 0.19027 0.18917 0.19002 0.18916 0.19023 0.19100 0.19249 0.19608 0.19930
-10 0.08672 0.07564 0.06734 0.06418 0.06244 0.06126 0.06082 0.06126 0.06244 0.06418 0.06733 0.07565 0.08672
-8 0.07484 0.06282 0.05426 0.05075 0.04905 0.04779 0.04743 0.04779 0.04905 0.05075 0.05426 0.06282 0.07484
-4 0.06083 0.04824 0.03925 0.03554 0.03379 0.03231 0.03205 0.03231 0.03379 0.03554 0.03925 0.04824 0.06083
0 0.06043 0.04775 0.03856 0.03469 0.03361 0.03201 0.02814 0.03201 0.03361 0.03469 0.03856 0.04774 0.06043
2 0.06617 0.05285 0.04480 0.03959 0.03741 0.03647 0.03598 0.03647 0.03741 0.03959 0.04480 0.05285 0.06618
4 0.07307 0.06237 0.05122 0.04798 0.04620 0.04487 0.04466 0.04487 0.04620 0.04798 0.05122 0.06238 0.07307
6 0.08502 0.07227 0.06254 0.06315 0.05713 0.05589 0.05666 0.05589 0.05713 0.06315 0.06253 0.07227 0.08502
8 0.09926 0.08645 0.07839 0.07473 0.07315 0.07200 0.07177 0.07200 0.07315 0.07474 0.07839 0.08645 0.09926
10 0.11604 0.10456 0.09622 0.09280 0.09139 0.09039 0.09021 0.09039 0.09138 0.09279 0.09622 0.10458 0.11605
12 0.13465 0.12511 0.11758 0.12986 0.11165 0.11182 0.11190 0.11182 0.11164 0.12985 0.11759 0.12513 0.13464
14 0.18360 0.14840 0.14310 0.13875 0.13731 0.13632 0.13630 0.13632 0.13730 0.13874 0.14308 0.14844 0.18362
16 0.18354 0.17582 0.16886 0.16594 0.16450 0.16375 0.16396 0.16374 0.16452 0.16597 0.16886 0.17580 0.18355
18 0.21108 0.20670 0.19968 0.19574 0.19451 0.19383 0.19426 0.19385 0.19447 0.19573 0.19970 0.20684 0.21108
20 0.24338 0.23847 0.23125 0.22867 0.22639 0.22649 0.22647 0.22643 0.22638 0.22864 0.23123 0.23845 0.24340
24 0.31154 0.30717 0.30101 0.29755 0.29607 0.29399 0.29331 0.29395 0.29603 0.29748 0.30093 0.30721 0.31158
28 0.38800 0.38170 0.37609 0.37010 0.36815 0.36502 0.36664 0.36500 0.36803 0.37028 0.37607 0.38199 0.38804
30 0.42637 0.40372 0.41710 0.40977 0.40684 0.40580 0.40674 0.40567 0.40679 0.40954 0.41709 0.40376 0.42651
35 0.51848 0.52598 0.52197 0.51865 0.51607 0.51452 0.51433 0.51448 0.51602 0.51870 0.52212 0.52525 0.51867
45 0.75561 0.78268 0.79047 0.79448 0.79257 0.79131 0.79189 0.79091 0.79225 0.79481 0.79063 0.78217 0.75597
50 0.95906 0.99447 1.00921 1.01348 1.00909 1.01029 1.00877 1.00952 1.00904 1.01341 1.00944 0.99474 0.95927
55 1.12790 1.16397 1.21196 1.22708 1.23136 1.22724 1.22662 1.22711 1.23159 1.22773 1.21243 1.16423 1.12811
60 1.34550 1.40885 1.48063 1.51451 1.52424 1.51172 1.51183 1.51208 1.52436 1.51386 1.47996 1.41204 1.34775
</tableData>
</table>
</function>
<function name="aero/c/CFXBRK">
<description>DRAG DUE TO SPEEDBRAKE</description>
<product>
<property>fcs/speedbrake-pos-norm</property>
<table>
<independentVar lookup="row">aero/alpha-deg</independentVar>
<independentVar lookup="column">aero/beta-deg</independentVar>
<tableData>
-20 -15 -10 -7 -5 -2 0 2 5 7 10 15 20
-20 0.00613 0.00759 0.00878 0.01501 0.00729 0.01618 0.00767 0.01618 0.00732 0.01508 0.00878 0.00752 0.00614
-10 0.01838 0.01652 0.01186 0.01273 0.01185 0.01286 0.01254 0.01286 0.01185 0.01273 0.01187 0.01639 0.01838
-8 0.01374 0.01348 0.01337 0.01333 0.01309 0.01298 0.01310 0.01298 0.01309 0.01333 0.01337 0.01347 0.01373
-4 0.01421 0.01450 0.01463 0.01464 0.01465 0.01453 0.01448 0.01453 0.01465 0.01464 0.01463 0.01450 0.01421
0 0.01524 0.01564 0.01606 0.01619 0.01646 0.01643 0.01610 0.01643 0.01646 0.01619 0.01607 0.01566 0.01524
2 0.01586 0.01626 0.01701 0.01707 0.01714 0.01715 0.01712 0.01715 0.01713 0.01706 0.01700 0.01625 0.01584
4 0.01606 0.01690 0.01812 0.01754 0.01794 0.01801 0.01775 0.01801 0.01794 0.01753 0.01812 0.01688 0.01607
6 0.01607 0.01726 0.01831 0.01934 0.01839 0.02195 0.01777 0.02195 0.01839 0.01934 0.01832 0.01727 0.01608
8 0.01633 0.01707 0.01764 0.01966 0.01904 0.01973 0.01898 0.01975 0.01904 0.01964 0.01765 0.01707 0.01629
10 0.01791 0.01826 0.01916 0.01997 0.01994 0.02083 0.02046 0.02081 0.01995 0.01997 0.01916 0.01819 0.01793
12 0.01688 0.01825 0.01964 0.02066 0.02136 0.02163 0.02188 0.02161 0.02137 0.02069 0.01960 0.01824 0.01688
14 0.01773 0.01975 0.02134 0.02142 0.02353 0.02178 0.02396 0.02178 0.02356 0.02142 0.02139 0.01970 0.01777
16 0.01927 0.02172 0.02292 0.02256 0.02422 0.02300 0.02414 0.02300 0.02421 0.02248 0.02302 0.02172 0.01921
18 0.02056 0.02351 0.02429 0.02407 0.02425 0.02445 0.02449 0.02440 0.02428 0.02399 0.02424 0.02340 0.02058
20 0.02462 0.02484 0.02542 0.02533 0.02521 0.02492 0.02539 0.02497 0.02521 0.02541 0.02540 0.02482 0.02465
24 0.03043 0.02890 0.02783 0.02767 0.02754 0.02824 0.02788 0.02829 0.02767 0.02773 0.02779 0.02897 0.03035
28 0.03373 0.03205 0.03160 0.03090 0.03102 0.03056 0.03077 0.03049 0.03113 0.03072 0.03166 0.03185 0.03377
30 0.03571 0.03296 0.03215 0.03168 0.03132 0.03136 0.03169 0.03149 0.03140 0.03192 0.03198 0.03321 0.03571
35 0.03169 0.03635 0.03427 0.03427 0.03465 0.03457 0.03413 0.03468 0.03470 0.03409 0.03407 0.03702 0.03119
45 0.03564 0.03493 0.03657 0.03908 0.03724 0.03814 0.03926 0.03850 0.03812 0.03868 0.03624 0.03545 0.03582
50 0.03355 0.03484 0.03749 0.03910 0.04067 0.04142 0.04261 0.04182 0.04082 0.03863 0.03846 0.03488 0.03370
55 0.03907 0.03670 0.04184 0.04033 0.04226 0.04093 0.03985 0.04120 0.04246 0.04009 0.04020 0.03741 0.03985
60 0.04250 0.04403 0.03048 0.04429 0.03686 0.04264 0.04470 0.04208 0.04338 0.04611 0.03068 0.04047 0.04565
</tableData>
</table>
</product>
</function>
<function name="aero/c/CFXDGE">
<description>DRAG DUE TO GROUND EFFECT</description>
<table>
<independentVar lookup="row">position/h-agl-m</independentVar>
<independentVar lookup="column">aero/alpha-deg</independentVar>
<tableData>
0 2 4 6 8 10 12 14 16 20
1 -0.00009 -0.00036 -0.00213 -0.00562 -0.00792 -0.01113 -0.01710 -0.01668 -0.02068 -0.01615
2 -0.00003 -0.00004 -0.00017 -0.00057 -0.00141 -0.00314 -0.00579 -0.00989 -0.01595 -0.03950
3 -0.00002 -0.00002 -0.00003 -0.00009 -0.00027 -0.00073 -0.00158 -0.00296 -0.00530 -0.01333
8 -0.00001 0.00001 0.00007 0.00016 0.00028 0.00044 0.00058 0.00067 0.00061 0.00029
10 -0.00001 0.00001 0.00006 0.00015 0.00027 0.00044 0.00059 0.00072 0.00078 0.00073
30 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000
</tableData>
</table>
</function>
<function name="aero/c/CFXDRD">
<description>DRAG DUE TO RUDDER DEFLECTION</description>
<product>
<property>fcs/rudder-deg</property>
<table>
<independentVar lookup="row">aero/alpha-deg</independentVar>
<independentVar lookup="column">aero/beta-deg</independentVar>
<tableData>
-20 -15 -10 -7 -5 -2 0 2 5 7 10 15 20
-20 0.00075 0.00046 0.00018 -0.00001 -0.00013 -0.00030 -0.00042 -0.00052 -0.00069 -0.00079 -0.00094 -0.00116 -0.00138
-10 0.00080 0.00049 0.00018 0.00000 -0.00011 -0.00029 -0.00040 -0.00051 -0.00068 -0.00078 -0.00094 -0.00119 -0.00141
-8 0.00081 0.00050 0.00019 0.00001 -0.00011 -0.00028 -0.00040 -0.00051 -0.00067 -0.00078 -0.00094 -0.00119 -0.00142
-4 0.00082 0.00051 0.00021 0.00003 -0.00009 -0.00026 -0.00038 -0.00049 -0.00065 -0.00077 -0.00093 -0.00118 -0.00141
0 0.00084 0.00053 0.00022 0.00004 -0.00006 -0.00028 -0.00036 -0.00046 -0.00066 -0.00075 -0.00091 -0.00116 -0.00141
2 0.00085 0.00053 0.00025 0.00005 -0.00008 -0.00024 -0.00035 -0.00048 -0.00064 -0.00075 -0.00093 -0.00116 -0.00141
4 0.00086 0.00057 0.00023 0.00006 -0.00006 -0.00023 -0.00035 -0.00048 -0.00063 -0.00075 -0.00088 -0.00118 -0.00139
6 0.00090 0.00058 0.00022 0.00032 -0.00014 -0.00045 -0.00036 -0.00024 -0.00055 -0.00101 -0.00089 -0.00117 -0.00139
8 0.00093 0.00057 0.00028 0.00010 -0.00002 -0.00020 -0.00035 -0.00046 -0.00062 -0.00075 -0.00092 -0.00116 -0.00139
10 0.00095 0.00061 0.00029 0.00011 -0.00002 -0.00018 -0.00032 -0.00043 -0.00060 -0.00074 -0.00089 -0.00112 -0.00140
12 0.00092 0.00062 0.00033 0.00105 -0.00010 -0.00019 -0.00031 -0.00042 -0.00053 -0.00160 -0.00092 -0.00117 -0.00137
14 0.00149 0.00064 0.00040 0.00017 0.00002 -0.00017 -0.00029 -0.00042 -0.00058 -0.00073 -0.00094 -0.00116 -0.00185
16 0.00097 0.00069 0.00037 0.00018 0.00003 -0.00015 -0.00027 -0.00038 -0.00056 -0.00070 -0.00087 -0.00113 -0.00133
18 0.00100 0.00072 0.00033 0.00019 0.00004 -0.00014 -0.00026 -0.00039 -0.00054 -0.00070 -0.00081 -0.00112 -0.00131
20 0.00100 0.00077 0.00042 0.00021 0.00005 -0.00014 -0.00024 -0.00037 -0.00057 -0.00070 -0.00089 -0.00115 -0.00129
24 0.00111 0.00080 0.00045 0.00023 0.00007 -0.00014 -0.00022 -0.00036 -0.00055 -0.00070 -0.00088 -0.00115 -0.00135
28 0.00104 0.00065 0.00037 0.00016 0.00007 -0.00020 -0.00024 -0.00024 -0.00053 -0.00058 -0.00078 -0.00091 -0.00122
30 0.00099 0.00058 0.00035 0.00019 0.00008 -0.00007 -0.00021 -0.00031 -0.00045 -0.00058 -0.00072 -0.00088 -0.00120
35 0.00086 0.00068 0.00036 0.00021 0.00010 -0.00007 -0.00017 -0.00030 -0.00045 -0.00052 -0.00066 -0.00093 -0.00108
45 0.00067 0.00050 0.00031 0.00013 0.00012 -0.00005 -0.00013 -0.00020 -0.00029 -0.00035 -0.00043 -0.00061 -0.00070
50 0.00065 0.00046 0.00023 0.00015 0.00006 -0.00003 -0.00009 -0.00013 -0.00030 -0.00024 -0.00033 -0.00048 -0.00057
55 0.00055 0.00041 0.00022 0.00011 0.00007 0.00004 -0.00007 -0.00009 -0.00014 -0.00017 -0.00030 -0.00035 -0.00051
60 0.00057 0.00029 0.00013 0.00012 -0.00022 0.00007 -0.00003 0.00002 -0.00006 -0.00017 -0.00018 -0.00019 -0.00026
</tableData>
</table>
</product>
</function>
<function name="aero/c/CFXDRDMN">
<description>DRAG DUE TO MACH DUE TO RUDDER DEFLECTION</description>
<product>
<property>fcs/rudder-deg</property>
<table>
<independentVar lookup="row">velocities/mach</independentVar>
<independentVar lookup="column">aero/alpha-deg</independentVar>
<tableData>
-10 -5 -2 0.01 1 2 6 7 10
0.2 0.00026 0.00009 0.00006 0.00005 0.00009 0.00011 0.00022 0.00026 0.00037
0.4 0.00017 0.00006 0.00004 0.00004 0.00006 0.00007 0.00015 0.00017 0.00024
0.6 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000
0.8 -0.00035 -0.00011 -0.00009 -0.00007 -0.00012 -0.00015 -0.00028 -0.00033 -0.00043
0.86 -0.00053 -0.00017 -0.00013 -0.00011 -0.00019 -0.00023 -0.00042 -0.00048 -0.00061
0.88 -0.00061 -0.00019 -0.00015 -0.00013 -0.00021 -0.00026 -0.00048 -0.00054 -0.00067
0.91 -0.00075 -0.00023 -0.00018 -0.00016 -0.00026 -0.00031 -0.00056 -0.00063 -0.00076
0.955 -0.00106 -0.00032 -0.00025 -0.00023 -0.00035 -0.00042 -0.00067 -0.00072 -0.00075
0.98 -0.00146 -0.00042 -0.00031 -0.00030 -0.00044 -0.00052 -0.00069 -0.00067 -0.00044
0.99 -0.00190 -0.00052 -0.00038 -0.00040 -0.00054 -0.00061 -0.00066 -0.00056 0.00002
1.1 -0.00033 -0.00217 -0.00101 -0.00122 -0.00138 -0.00181 -0.00040 -0.00040 -0.00040
1.7 -0.00370 -0.00140 -0.00063 -0.00069 -0.00069 -0.00091 -0.00327 -0.00427 -0.00051
2 -0.00386 -0.00126 -0.00047 -0.00052 -0.00049 -0.00066 -0.00248 -0.00323 -0.00059
2.4 -0.00316 -0.00096 -0.00032 -0.00037 -0.00030 -0.00041 -0.00164 -0.00216 -0.00418
</tableData>
</table>
</product>
</function>
<function name="aero/c/CFXDSL">
<description>DRAG DUE TO SLATS</description>
<table>
<independentVar lookup="row">aero/alpha-deg</independentVar>
<independentVar lookup="column">fcs/slats-deg</independentVar>
<tableData>
0 10 23
-20 0.00000 0.00277 0.00277
-10 0.00000 0.00053 0.00053
-8 0.00000 0.00028 0.00028
-4 0.00000 0.00006 0.00006
0 0.00000 0.00072 0.00072
2 0.00000 0.00046 0.00046
4 0.00000 0.00075 0.00075
6 0.00000 0.00121 0.00121
8 0.00000 0.00172 0.00173
10 0.00000 0.00234 0.00234
12 0.00000 0.00302 0.00302
14 0.00000 0.00356 0.00356
16 0.00000 0.00431 0.00430
18 0.00000 0.00541 0.00540
20 0.00000 0.00723 0.00723
24 0.00000 0.01221 0.01221
28 0.00000 0.01727 0.01728
30 0.00000 0.01773 0.01764
35 0.00000 0.02250 0.02250
45 0.00000 0.03467 0.03472
50 0.00000 0.05361 0.05373
55 0.00000 0.05741 0.05712
60 0.00000 0.06425 0.06528
</tableData>
</table>
</function>
<function name="aero/c/CFXDSPL">
<description>DRAG DUE TO SPOILERS LEFT</description>
<table>
<independentVar lookup="row">aero/alpha-deg</independentVar>
<independentVar lookup="column">aero/beta-deg</independentVar>
<independentVar lookup="table">fcs/spoiler-left-deg</independentVar>
<tableData breakPoint="0">
-20 -15 -10 -7 -5 -2 0 2 5 7 10 15 20
-20 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000
-10 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000
-8 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000
-4 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000
0 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000
2 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000
4 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000
6 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000
8 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000
10 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000
12 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000
14 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000
16 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000
18 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000
20 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000
24 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000
28 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000
30 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000
35 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000
45 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000
50 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000
55 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000
60 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000
</tableData>
<tableData breakPoint="20">
-20 -15 -10 -7 -5 -2 0 2 5 7 10 15 20
-20 0.02157 0.02219 0.02331 0.02242 0.02167 0.02023 0.01987 0.01941 0.01766 0.01694 0.01519 0.01261 0.00976
-10 0.01676 0.01600 0.01444 0.01353 0.01293 0.01157 0.01098 0.01035 0.00919 0.00856 0.00763 0.00561 0.00378
-8 0.01522 0.01420 0.01246 0.01150 0.01094 0.00979 0.00910 0.00855 0.00751 0.00684 0.00586 0.00414 0.00252
-4 0.01125 0.00985 0.00828 0.00720 0.00669 0.00577 0.00514 0.00453 0.00364 0.00300 0.00231 0.00095 -0.00039
0 0.00619 0.00510 0.00340 0.00280 0.00127 0.00171 0.00228 0.00026 -0.00025 -0.00065 -0.00123 -0.00244 -0.00347
2 0.00336 0.00140 -0.00149 0.00078 0.00071 -0.00052 -0.00074 -0.00130 -0.00197 -0.00242 -0.00323 -0.00416 -0.00523
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<description>DRAG DUE TO FLAPS INBOARD</description>
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20 0.00164 0.00166 0.00171 0.00172 0.00177 0.00173 0.00174 0.00178 0.00177
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55 0.00179 0.00172 0.00164 0.00168 0.00174 0.00163 0.00166 0.00175 0.00162
60 0.00154 0.00163 0.00156 0.00158 0.00149 0.00168 0.00145 0.00131 0.00150
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<tableData>
-25 -20 -15 -10 -5 0 5 10 15
-20 0.00330 0.00231 0.00138 0.00053 -0.00025 -0.00097 -0.00155 -0.00200 -0.00230
-10 0.00310 0.00232 0.00161 0.00096 0.00040 -0.00003 -0.00034 -0.00051 -0.00058
-8 0.00305 0.00232 0.00164 0.00103 0.00053 0.00014 -0.00011 -0.00024 -0.00027
-4 0.00296 0.00231 0.00172 0.00118 0.00076 0.00049 0.00033 0.00036 0.00050
0 0.00299 0.00242 0.00186 0.00143 0.00113 0.00045 0.00086 0.00102 0.00137
2 0.00287 0.00230 0.00182 0.00143 -0.00011 0.00094 0.00101 0.00125 0.00162
4 0.00281 0.00228 0.00183 -0.00046 0.00112 0.00110 0.00122 0.00149 0.00195
6 0.00270 0.00224 -0.00070 0.00132 0.00122 0.00124 0.00140 0.00176 0.00229
8 0.00258 -0.00061 0.00148 0.00136 0.00128 0.00135 0.00159 0.00201 0.00263
10 -0.00009 0.00162 0.00149 0.00133 0.00131 0.00145 0.00177 0.00228 0.00288
12 0.00171 0.00165 0.00144 0.00130 0.00134 0.00156 0.00195 0.00247 0.00317
14 0.00179 0.00146 0.00127 0.00121 0.00131 0.00161 0.00203 0.00264 0.00335
16 0.00140 0.00112 0.00100 0.00102 0.00121 0.00152 0.00205 0.00270 0.00347
18 0.00094 0.00075 0.00070 0.00079 0.00102 0.00144 0.00201 0.00271 0.00351
20 0.00049 0.00036 0.00037 0.00051 0.00081 0.00131 0.00192 0.00267 0.00354
24 -0.00038 -0.00036 -0.00023 0.00005 0.00049 0.00107 0.00180 0.00266 0.00365
28 -0.00117 -0.00106 -0.00079 -0.00042 0.00013 0.00088 0.00173 0.00266 0.00377
30 -0.00158 -0.00140 -0.00112 -0.00066 -0.00001 0.00079 0.00166 0.00272 0.00384
35 -0.00251 -0.00221 -0.00171 -0.00106 -0.00027 0.00071 0.00177 0.00296 0.00417
45 -0.00444 -0.00378 -0.00295 -0.00186 -0.00081 0.00061 0.00182 0.00316 0.00450
50 -0.00467 -0.00377 -0.00288 -0.00157 -0.00025 0.00120 0.00213 0.00391 0.00495
55 -0.00563 -0.00458 -0.00340 -0.00210 -0.00071 0.00085 0.00208 0.00331 0.00466
60 -0.00680 -0.00552 -0.00406 -0.00257 -0.00088 0.00100 0.00224 0.00388 0.00554
</tableData>
</table>
</product>
</function>
<function name="aero/c/CFXGEAR">
<description>DRAG DUE TO GEAR</description>
<product>
<property>gear/gear-pos-norm</property>
<table>
<independentVar lookup="row">aero/alpha-deg</independentVar>
<independentVar lookup="column">aero/beta-deg</independentVar>
<tableData>
-20 -15 -10 -7 -5 -2 0 2 5 7 10 15 20
-20 0.00254 0.00240 0.00203 0.00180 0.00160 0.00141 0.00141 0.00142 0.00162 0.00182 0.00207 0.00240 0.00271
-10 0.00188 0.00169 0.00132 0.00096 0.00079 0.00062 0.00058 0.00062 0.00079 0.00096 0.00133 0.00168 0.00187
-8 0.00165 0.00153 0.00114 0.00082 0.00064 0.00048 0.00046 0.00048 0.00064 0.00082 0.00114 0.00153 0.00166
-4 0.00116 0.00117 0.00084 0.00057 0.00043 0.00029 0.00026 0.00029 0.00043 0.00057 0.00084 0.00117 0.00116
0 0.00064 0.00079 0.00062 0.00044 0.00033 0.00021 0.00021 0.00021 0.00033 0.00044 0.00062 0.00080 0.00063
2 0.00045 0.00072 0.00057 0.00042 0.00033 0.00025 0.00023 0.00025 0.00033 0.00042 0.00057 0.00072 0.00043
4 0.00044 0.00064 0.00048 0.00047 0.00040 0.00033 0.00033 0.00033 0.00040 0.00047 0.00048 0.00063 0.00044
6 0.00060 0.00068 0.00054 0.00056 0.00053 0.00049 0.00049 0.00049 0.00054 0.00057 0.00055 0.00068 0.00061
8 0.00140 0.00110 0.00102 0.00091 0.00079 0.00070 0.00071 0.00070 0.00080 0.00091 0.00103 0.00110 0.00142
10 0.00384 0.00211 0.00204 0.00155 0.00116 0.00105 0.00103 0.00105 0.00117 0.00158 0.00204 0.00208 0.00384
12 0.00544 0.00418 0.00234 0.00186 0.00153 0.00149 0.00136 0.00149 0.00154 0.00186 0.00234 0.00417 0.00547
14 0.00591 0.00517 0.00546 0.00243 0.00266 0.00200 0.00197 0.00200 0.00268 0.00243 0.00551 0.00509 0.00589
16 0.00647 0.00559 0.00405 0.00333 0.00321 0.00246 0.00264 0.00247 0.00317 0.00331 0.00410 0.00563 0.00647
18 0.00716 0.00645 0.00311 0.00420 0.00375 0.00321 0.00322 0.00319 0.00376 0.00421 0.00303 0.00635 0.00714
20 0.00774 0.00677 0.00454 0.00490 0.00430 0.00389 0.00379 0.00392 0.00432 0.00495 0.00457 0.00673 0.00767
24 0.00919 0.00795 0.00633 0.00586 0.00538 0.00506 0.00444 0.00506 0.00542 0.00597 0.00640 0.00816 0.00910
28 0.01125 0.00913 0.00739 0.00685 0.00604 0.00642 0.00656 0.00637 0.00618 0.00659 0.00747 0.00884 0.01120
30 0.01379 0.01082 0.01003 0.00767 0.00552 0.00753 0.00708 0.00763 0.00562 0.00809 0.01004 0.01071 0.01371
35 0.01557 0.01355 0.01303 0.01025 0.01082 0.01076 0.01053 0.01098 0.01087 0.01028 0.01274 0.01439 0.01540
45 0.01748 0.01598 0.01547 0.01041 0.01744 0.01657 0.00833 0.01729 0.01793 0.00991 0.01560 0.01597 0.01799
50 0.01616 0.01541 0.01394 0.01159 0.01232 0.01228 0.01251 0.01295 0.01258 0.01177 0.01344 0.01479 0.01581
55 0.01763 0.01310 0.01477 0.01174 0.01135 0.01063 0.01098 0.01060 0.01119 0.01127 0.01384 0.01454 0.01768
60 0.01594 0.01759 0.01176 0.01018 0.01034 0.00969 0.01365 0.00962 0.01041 0.01087 0.01263 0.01425 0.01295
</tableData>
</table>
</product>
</function>
<function name="aero/c/CFXMN">
<description>DRAG DUE TO MACH</description>
<table>
<independentVar lookup="row">velocities/mach</independentVar>
<independentVar lookup="column">aero/alpha-deg</independentVar>
<tableData>
-10 -5 -2 0.01 1 2 6 7 10
0.2 -0.00417 -0.00065 -0.00018 0.00005 -0.00062 -0.00112 -0.00351 -0.00423 -0.00669
0.4 -0.00280 -0.00043 -0.00012 0.00004 -0.00042 -0.00076 -0.00232 -0.00280 -0.00439
0.6 0.00000 0.00000 0.00000 0.00000 0.00000 -0.00001 0.00000 0.00000 0.00000
0.8 0.00565 0.00075 0.00024 -0.00010 0.00092 0.00155 0.00446 0.00543 0.00750
0.86 0.00848 0.00108 0.00035 -0.00013 0.00141 0.00235 0.00654 0.00779 0.01035
0.88 0.00965 0.00122 0.00039 -0.00013 0.00162 0.00267 0.00732 0.00845 0.01124
0.91 0.01171 0.00145 0.00046 -0.00012 0.00196 0.00320 0.00852 0.00968 0.01223
0.955 0.01662 0.00203 0.00055 0.00005 0.00258 0.00412 0.00978 0.01060 0.01083
0.98 0.02361 0.00276 0.00060 0.00043 0.00313 0.00469 0.00866 0.00826 0.00304
0.99 0.03102 0.00358 0.00065 0.00089 0.00360 0.00507 0.00630 0.00431 -0.00800
1.1 0.13135 0.03101 0.00792 0.01227 0.01541 0.02421 0.09454 0.12059 0.21724
1.7 0.06646 0.02049 0.00512 0.00667 0.00661 0.01121 0.05914 0.07923 0.15994
2 0.07240 0.02028 0.00464 0.00574 0.00506 0.00859 0.04568 0.06088 0.12107
2.4 0.06056 0.01651 0.00358 0.00466 0.00325 0.00550 0.03085 0.04121 0.08158
</tableData>
</table>
</function>
<function name="aero/c/CFXTANKC">
<description>DRAG INCREMENT DUE TO CENTRE TANK</description>
<product>
<property>inertia/tank-centre-fitted</property>
<table>
<independentVar lookup="row">aero/alpha-deg</independentVar>
<independentVar lookup="column">aero/beta-deg</independentVar>