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Aerodynamicschannel written new, old one was a chaos.

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This commit is contained in:
JWocky 2016-11-08 16:11:39 -06:00
parent 34c3f1024b
commit d2f2b26bb9
2 changed files with 398 additions and 746 deletions
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152
A320-200-IAE (changed CG).xml → A320-200-IAE (before rewriting aerodynamics channel).xml
View file

@ -30,7 +30,7 @@ xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">
<z> -25.2091 </z>
</location -->
<location name="AERORP" unit="IN">
<x> 650.00 </x>
<x> 680.00 </x>
<y> 0 </y>
<z> 0.00 </z>
</location>
@ -75,8 +75,8 @@ YAW MOI_________3950000______23089847_______24848934
<iyz unit="SLUG*FT2"> 0 </iyz>
<emptywt unit="LBS">80431</emptywt> <!-- #ref-1 page 67, WV016. 90927lbs - 5248x2 (engines)=80431lbs-->
<!-- #### PB: That makes no sense, the wohle aircraft is 1479.1339 inches long. 650inches eqauls to about 43.95% MAC with the Airbus limits according to the AMM between 45% and 49%
Also: The z-axis is -41.73 unches under the zero line of the plane while the pressure point is only -25,91 under the same line and slightly ahead, that causes the plane to behave quite unstable
<!-- #### PB: That makes no sense, the whole aircraft is 1479.1339 inches long. 650inches eqauls to about 43.95% MAC with the Airbus limits according to the AMM between 45% and 49%
Also: The z-axis is -41.73 inches under the zero line of the plane while the pressure point is only -25,91 under the same line and slightly ahead, that causes the plane to behave quite unstable
-->
<!-- location name="CG" unit="IN">
<! - -x> 642.122 </x- - >
@ -85,104 +85,82 @@ YAW MOI_________3950000______23089847_______24848934
<z> -41.7398 </z>
</location -->
<location name="CG" unit="IN">
<x> 650.00 </x>
<x> 655.00 </x>
<y> 0 </y>
<z> 0.00 </z>
</location>
<pointmass name="Crew">
<weight unit="LBS">400</weight> <!-- MAX: 600lbs-->
<pointmass name="Cockpit Crew">
<weight unit="LBS">400</weight> <!-- MAX: 400lbs, two pilots-->
<location name="POINTMASS" unit="IN">
<x>200</x>
<y>0</y>
<z>0</z>
</location>
</pointmass>
<pointmass name="PAX">
<weight unit="LBS">19750</weight> <!-- MAX: 39500 lbs ** looks too heavy. maybe low it and give a long cilinder shape. need to do some maths-->
<form shape="cylinder">
<radius unit="M"> 2.13 </radius>
<length unit="M"> 24.44 </length>
</form>
<pointmass name="Cabin Crew">
<weight unit="LBS">600</weight> <!-- MAX: 1320lbs, up to six flight-attendants-->
<location name="POINTMASS" unit="IN">
<x>705</x>
<x>696</x>
<y>0</y>
<z>0</z>
</location>
</pointmass>
<!-- NEW Pointmasses Start Weights for good CG -->
<pointmass name="Fwd Cargo">
<weight unit="LBS">3750</weight> <!-- #REF-3 page 19, MAX 3402 kilograms = 7500.12616 lbs -->
<form shape="cylinder">
<radius unit="M"> 1.24 </radius>
<length unit="M"> 4.95 </length>
</form>
<pointmass name="PAX 0A (60 seats)">
<weight unit="LBS">6600</weight> <!-- MAX: 13200lbs, 60 seats -->
<location name="POINTMASS" unit="IN">
<!-- #REF-1 page 88+98,
x= (door form nose(8.16m))-(door with(1.816m)/2)+(Cargo compartment lenght(4.953m)/2)
x= 9.7285 meters = 383.011811 in
-->
<x>383.01</x>
<x>450.1711</x>
<y>0</y>
<z>-59.05</z> <!-- Aprox lower deck 1.5 meters = 59.0551181 in -->
<z>0</z>
</location>
</pointmass>
<pointmass name="Aft Cargo">
<weight unit="LBS">0</weight> <!-- #REF-3 page 19, MAX 4536 kilograms = 10000.1682 lbs -->
<form shape="cylinder">
<radius unit="M"> 1.24 </radius>
<length unit="M"> 6.6 </length>
</form>
<pointmass name="PAX 0B (60 seats)">
<weight unit="LBS">6600</weight> <!-- MAX: 13200lbs, 60 seats -->
<location name="POINTMASS" unit="IN">
<!-- #REF-1 page 88+98,
x= (door form nose(22.69m))-(door with(1.816m)/2)
x= 21.78200 meters = 857.559055 in
-->
<x>857.55</x>
<x>739.5669</x>
<y>0</y>
<z>-59.05</z> <!-- Aprox lower deck 1.5 meters = 59.0551181 in -->
<z>0</z>
</location>
</pointmass>
<pointmass name="Rear Bulk Cargo">
<weight unit="LBS">0</weight> <!-- #REF-3 page 19, MAX 1497 kilograms = 3300.32006 lbs -->
<form shape="cylinder">
<radius unit="M"> 1.24 </radius>
<length unit="M"> 2 </length>
</form>
<pointmass name="PAX 0C (54 seats)">
<weight unit="LBS">5940</weight> <!-- MAX: 11880lbs, 54 seats -->
<location name="POINTMASS" unit="IN">
<!-- #REF-1 page 88+102,
x= (door form nose(22.69m))+(door with(1.816m)/2)+( Dist. between rear doors(2.19))+(Aprox to compartment center (2m))
x= 27.78800 meters = 1 094.01575 in
-->
<x>1094</x>
<x>1093.2729</x>
<y>0</y>
<z>-39.37</z> <!-- Aprox bulk lower deck 1 meter = 39.3700787 in -->
<z>0</z>
</location>
</pointmass>
<pointmass name="Engine1">
<weight unit="LBS">5248</weight>
<form shape="cylinder">
<radius unit="M"> 1.31 </radius>
<length unit="M"> 5 </length>
</form>
<pointmass name="Cargo Hold 1">
<weight unit="LBS">2000</weight> <!-- MAX: 7500.126lbs -->
<location name="POINTMASS" unit="IN">
<x>589.735</x>
<y>-226.575</y>
<z>-45.567</z>
<x>383.4792</x>
<y>0</y>
<z>-29.5</z> <!-- 1.5m and now half of it for the center point of the load -->
</location>
</pointmass>
<pointmass name="Engine2">
<weight unit="LBS">5248</weight>
<form shape="cylinder">
<radius unit="M"> 1.31 </radius>
<length unit="M"> 5 </length>
</form>
<!-- Cargo Hold 2 doesn't exist, that is the center tank -->
<pointmass name="Cargo Hold 3">
<weight unit="LBS">2000</weight> <!-- MAX: 5384.414lbs -->
<location name="POINTMASS" unit="IN">
<x>589.735</x>
<y>226.575</y>
<z>-45.567</z>
<x>849.1324</x>
<y>0</y>
<z>-29.5</z>
</location>
</pointmass>
<pointmass name="Cargo Hold 4">
<weight unit="LBS">1500</weight> <!-- MAX: 4651.754lbs -->
<location name="POINTMASS" unit="IN">
<x>931.0653</x>
<y>0</y>
<z>-29.5</z>
</location>
</pointmass>
<pointmass name="Cargo Hold 5">
<weight unit="LBS">2000</weight> <!-- MAX: 3300.320lbs -->
<location name="POINTMASS" unit="IN">
<x>1068.2634</x>
<y>0</y>
<z>0</z> <!-- Cargo Hold #5 sits higher on the range of the cabin deck, it's only loadable with lifter -->
</location>
</pointmass>
@ -430,6 +408,7 @@ YAW MOI_________3950000______23089847_______24848934
</ground_reactions>
<propulsion>
<engine file="v2527_a5">
<location unit="IN">
<x> 589.735 </x>
@ -457,6 +436,7 @@ YAW MOI_________3950000______23089847_______24848934
</orient>
</thruster>
</engine>
<engine file="v2527_a5">
<location unit="IN">
<x> 589.735 </x>
@ -488,7 +468,7 @@ YAW MOI_________3950000______23089847_______24848934
<tank type="FUEL"> <!-- Left Tank (Wing tip Ventilation Surge) 0 -->
<location unit="IN">
<x> 788.4322 </x>
<x> 783.0709 </x>
<y> -574.4148 </y>
<z> 3.1080 </z>
</location>
@ -501,11 +481,11 @@ YAW MOI_________3950000______23089847_______24848934
</tank>
<tank type="FUEL"> <!-- Left Tank (Outer) 1 -->
<location unit="IN">
<x> 737.4190 </x>
<x> 739.5669 </x>
<y> -457.4259 </y>
<z> -8.0898 </z>
</location>
<capacity unit="LBS"> 1548.8 </capacity><!-- need review -->
<capacity unit="LBS"> 1520.00 </capacity><!-- need review -->
<contents unit="LBS"> 154.88 </contents>
<standpipe unit="LBS">21</standpipe><!-- minimun fuel on pipes -->
<priority>2</priority>
@ -514,12 +494,12 @@ YAW MOI_________3950000______23089847_______24848934
</tank>
<tank type="FUEL"> <!-- Left Tank (Inner) 2 -->
<location unit="IN">
<x> 630.6588 </x>
<x> 652.5591 </x>
<y> -236.2992 </y>
<z> -33.9470 </z>
</location>
<capacity unit="LBS"> 12186.9 </capacity><!-- need review -->
<contents unit="LBS"> 2437.38 </contents>
<capacity unit="LBS"> 11982 </capacity><!-- need review -->
<contents unit="LBS"> 11982 </contents>
<standpipe unit="LBS">31</standpipe><!-- minimun fuel on pipes -->
<priority>3</priority>
<type>JET-A1</type>
@ -527,12 +507,12 @@ YAW MOI_________3950000______23089847_______24848934
</tank>
<tank type="FUEL"> <!-- Center Tank 3 -->
<location unit="IN">
<x> 580.9955 </x>
<x> 522.0473 </x>
<y> 0 </y>
<z> -47.0 </z>
</location>
<capacity unit="LBS"> 14520 </capacity><!-- need review -->
<contents unit="LBS"> 0 </contents>
<capacity unit="LBS"> 14281 </capacity><!-- need review -->
<contents unit="LBS"> 7260 </contents>
<standpipe unit="LBS">43</standpipe><!-- minimun fuel on pipes -->
<priority>1</priority>
<type>JET-A1</type>
@ -540,24 +520,24 @@ YAW MOI_________3950000______23089847_______24848934
</tank>
<tank type="FUEL"> <!-- Right Tank (Inner) 4 -->
<location unit="IN">
<x> 630.6588 </x>
<x> 652.5591 </x>
<y> 236.2992 </y>
<z> -33.9470 </z>
</location>
<capacity unit="LBS"> 12186.9 </capacity><!-- need review -->
<contents unit="LBS"> 2437.38 </contents>
<standpipe unit="LBS">31</standpipe><!-- minimun fuel on pipes -->
<capacity unit="LBS"> 11982 </capacity><!-- need review -->
<contents unit="LBS"> 11982 </contents>
<standpipe unit="LBS">31</standpipe><!-- minimum fuel on pipes -->
<priority>3</priority>
<type>JET-A1</type>
<temperature>50</temperature>
</tank>
<tank type="FUEL"> <!-- Right Tank (Outer) 5 -->
<location unit="IN">
<x> 737.4190 </x>
<x> 739.5669 </x>
<y> 457.4259 </y>
<z> -8.0898 </z>
</location>
<capacity unit="LBS"> 1548.8 </capacity><!-- need review -->
<capacity unit="LBS"> 1520 </capacity><!-- need review -->
<contents unit="LBS"> 154.88 </contents>
<standpipe unit="LBS">21</standpipe><!-- minimun fuel on pipes -->
<priority>2</priority>
@ -566,7 +546,7 @@ YAW MOI_________3950000______23089847_______24848934
</tank>
<tank type="FUEL"> <!-- Right Tank (Wing tip Ventilation Surge) 6 -->
<location unit="IN">
<x> 788.4322 </x>
<x> 783.0709 </x>
<y> 574.4148 </y>
<z> 3.1080 </z>
</location>

566
A320-200-IAE.xml
View file

@ -526,7 +526,7 @@ YAW MOI_________3950000______23089847_______24848934
</location>
<capacity unit="LBS"> 11982 </capacity><!-- need review -->
<contents unit="LBS"> 11982 </contents>
<standpipe unit="LBS">31</standpipe><!-- minimun fuel on pipes -->
<standpipe unit="LBS">31</standpipe><!-- minimum fuel on pipes -->
<priority>3</priority>
<type>JET-A1</type>
<temperature>50</temperature>
@ -802,7 +802,9 @@ YAW MOI_________3950000______23089847_______24848934
</aerosurface_scale>
</channel>
<channel name="Flaps">
<kinematic name="Flaps Control">
<input>fcs/flap-cmd-norm</input>
<traverse>
@ -830,7 +832,9 @@ YAW MOI_________3950000______23089847_______24848934
</range>
<output>fcs/flap-pos-norm</output>
</aerosurface_scale>
</channel>
<channel name="Landing Gear">
<kinematic name="Gear Control">
<input>gear/gear-cmd-norm</input>
@ -914,341 +918,89 @@ YAW MOI_________3950000______23089847_______24848934
</flight_control>
<aerodynamics>
<function name="aero/function/kCDge">
<description>Change_in_drag_due_to_ground_effect</description>
<product>
<table>
<independentVar>aero/h_b-mac-ft</independentVar>
<tableData>
0.0000 0.4800
0.1000 0.5150
0.1500 0.6290
0.2000 0.7090
0.3000 0.8150
0.4000 0.8820
0.5000 0.9280
0.6000 0.9620
0.7000 0.9880
0.8000 1.0000
0.9000 1.0000
1.0000 1.0000
1.1000 1.0000
</tableData>
</table>
</product>
</function>
<function name="aero/function/kCLge">
<description>Change_in_lift_due_to_ground_effect</description>
<product>
<table>
<independentVar>aero/h_b-mac-ft</independentVar>
<tableData>
0.0000 1.2030
0.1000 1.1270
0.1500 1.0900
0.2000 1.0730
0.3000 1.0460
0.4000 1.0550
0.5000 1.0190
0.6000 1.0130
0.7000 1.0080
0.8000 1.0060
0.9000 1.0030
1.0000 1.0020
1.1000 1.0000
</tableData>
</table>
</product>
</function>
<aerodynamics>
<axis name="LIFT">
<function name="aero/force/Lift_gain">
<description>Drag_at_zero_lift</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<value>0.30</value>
</product>
</function>
<!--function name="aero/coefficient/CLalpha">
<description>Lift_due_to_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">fcs/flap-pos-deg</independentVar>
<tableData>
0.0000 1.0000 9.0000 10.0000 40.0000
-0.0900 -0.2200 -0.2200 -0.1200 -0.1200 0.3200
0.0000 0.2500 0.2500 0.3500 0.3500 0.7500
0.0900 0.7300 0.7300 0.8300 0.8300 1.2300
0.1000 0.8300 0.8300 0.9300 0.9300 1.3300
0.1200 0.9200 0.9200 1.0200 1.0200 1.4200
0.1400 1.0200 1.0200 1.1200 1.1200 1.5200
0.1600 1.0800 1.0800 1.1800 1.1800 1.5800
0.1700 1.1300 1.1300 1.2300 1.2300 1.6300
0.1900 1.1900 1.1900 1.2900 1.2900 1.6900
0.2100 1.2500 1.2500 1.3500 1.3500 1.7700
0.2400 1.3500 1.3700 1.4700 1.4800 1.9300
0.2600 1.4400 1.4700 1.5700 1.6200 2.1200
0.2800 1.4700 1.5100 1.6100 1.7800 2.4000
0.3000 1.5000 1.5600 1.6600 1.9000 2.3000
0.3200 1.4700 1.6100 1.6000 1.7000 2.0300
0.3400 1.3500 1.5000 1.4100 1.5000 1.5300
0.3600 1.1500 1.2000 1.2000 1.2000 1.2000
</tableData>
</table>
</product>
</function-->
<function name="aero/force/Lift_alpha">
<description>Lift_due_to_alpha</description>
<description>Lift due to alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/function/kCLge</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">fcs/flap-pos-deg</independentVar>
<tableData>
0.0000 1.0000 9.0000 10.0000 40.0000
-0.0900 -0.2200 -0.2200 -0.1200 -0.1200 0.2500
0.0000 0.2500 0.2500 0.3500 0.3500 0.7500
0.0900 0.7300 0.7300 0.8300 0.8300 1.2300
0.1000 0.8300 0.8300 0.9300 0.9300 1.3300
0.1200 0.9200 0.9200 1.0200 1.0200 1.4200
0.1400 1.0200 1.0200 1.1200 1.1200 1.5200
0.1600 1.0800 1.0800 1.1800 1.1800 1.5800
0.1700 1.1300 1.1300 1.2300 1.2300 1.6300
0.1900 1.1900 1.1900 1.2900 1.2900 1.6900
0.2100 1.2500 1.2500 1.3500 1.3500 1.7700
0.2400 1.3500 1.3700 1.4700 1.4800 1.9300
0.2600 1.4400 1.4700 1.5700 1.6200 2.1200
0.2800 1.4700 1.5100 1.6100 1.7800 2.4000
0.3000 1.5000 1.5600 1.6600 1.9000 2.3000
0.3200 1.4700 1.6100 1.6000 1.7000 2.0300
0.3400 1.3500 1.5000 1.4100 1.5000 1.5300
0.3600 1.1500 1.2000 1.2000 1.2000 1.2000
-0.20 -0.880
0.00 0.500
0.23 1.500
0.60 0.900
</tableData>
</table>
</product>
</function>
<!--function name="aero/coefficient/CLDe">
<description>Lift_due_to_Elevator_Deflection</description>
<function name="aero/force/Lift_flap">
<description>Delta Lift due to flaps</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/elevator-pos-rad</property>
<value>0.1930</value>
</product>
</function>-->
<function name="aero/force/Lift_elevator">
<description>Lift due to Elevator Deflection</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/elevator-pos-rad</property>
<value>0.1930</value>
<property>fcs/flap-pos-deg</property>
<value> 0.03500 </value>
</product>
</function>
<function name="aero/force/Lift_speedbrake">
<description>Delta Lift due to speedbrake</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/speedbrake-pos-norm</property>
<value>-0.15</value>
<value>-0.1</value>
</product>
</function>
<function name="aero/force/Lift_elevator">
<description>Lift due to Elevator Deflection</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/elevator-pos-rad</property>
<value>0.15</value>
</product>
</function>
</axis>
<axis name="DRAG">
<function name="aero/force/Drag_zero_lift">
<description>Drag_at_zero_lift</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<value>0.016</value>
</product>
</function>
<!--function name="aero/coefficient/CDalpha">
<description>Drag_due_to_alpha</description>
<function name="aero/force/Drag_basic">
<description>Drag at zero lift</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">fcs/flap-pos-deg</independentVar>
<tableData>
0.0000 1.0000 25.0000 40.0000
-0.0873 0.0041 0.0000 0.0005 0.0014
-0.0698 0.0013 0.0004 0.0025 0.0041
-0.0524 0.0001 0.0023 0.0059 0.0084
-0.0349 0.0003 0.0057 0.0108 0.0141
-0.0175 0.0020 0.0105 0.0172 0.0212
0.0000 0.0052 0.0168 0.0251 0.0399
0.0175 0.0099 0.0248 0.0346 0.0502
0.0349 0.0162 0.0342 0.0457 0.0621
0.0524 0.0240 0.0452 0.0583 0.0755
0.0698 0.0334 0.0577 0.0724 0.0904
0.0873 0.0442 0.0718 0.0881 0.1068
0.1047 0.0566 0.0874 0.1053 0.1248
0.1222 0.0706 0.1045 0.1240 0.1443
0.1396 0.0860 0.1232 0.1442 0.1654
0.1571 0.0962 0.1353 0.1573 0.1790
0.1745 0.1069 0.1479 0.1708 0.1930
0.1920 0.1180 0.1610 0.1849 0.2075
0.2094 0.1298 0.1746 0.1995 0.2226
0.2269 0.1424 0.1892 0.2151 0.2386
0.2443 0.1565 0.2054 0.2323 0.2564
0.2618 0.1727 0.2240 0.2521 0.2767
0.2793 0.1782 0.2302 0.2587 0.2835
0.2967 0.1716 0.2227 0.2507 0.2753
0.3142 0.1618 0.2115 0.2388 0.2631
0.3316 0.1475 0.1951 0.2214 0.2451
0.3491 0.1097 0.1512 0.1744 0.1966
</tableData>
</table>
</product>
</function-->
<function name="aero/force/Drag_alpha">
<description>Drag_due_to_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">fcs/flap-pos-deg</independentVar>
<tableData>
0.0000 1.0000 25.0000 40.0000
-0.0873 0.0041 0.0000 0.0005 0.0014
-0.0698 0.0013 0.0004 0.0025 0.0041
-0.0524 0.0001 0.0023 0.0059 0.0084
-0.0349 0.0003 0.0057 0.0108 0.0141
-0.0175 0.0020 0.0105 0.0172 0.0212
0.0000 0.0052 0.0168 0.0251 0.0399
0.0175 0.0099 0.0248 0.0346 0.0502
0.0349 0.0162 0.0342 0.0457 0.0621
0.0524 0.0240 0.0452 0.0583 0.0755
0.0698 0.0334 0.0577 0.0724 0.0904
0.0873 0.0442 0.0718 0.0881 0.1068
0.1047 0.0566 0.0874 0.1053 0.1248
0.1222 0.0706 0.1045 0.1240 0.1443
0.1396 0.0860 0.1232 0.1442 0.1654
0.1571 0.0962 0.1353 0.1573 0.1790
0.1745 0.1069 0.1479 0.1708 0.1930
0.1920 0.1180 0.1610 0.1849 0.2075
0.2094 0.1298 0.1746 0.1995 0.2226
0.2269 0.1424 0.1892 0.2151 0.2386
0.2443 0.1565 0.2054 0.2323 0.2564
0.2618 0.1727 0.2240 0.2521 0.2767
0.2793 0.1782 0.2302 0.2587 0.2835
0.2967 0.1716 0.2227 0.2507 0.2753
0.3142 0.1618 0.2115 0.2388 0.2631
0.3316 0.1475 0.1951 0.2214 0.2451
0.3491 0.1097 0.1512 0.1744 0.1966
-1.57 1.500
-0.26 0.026
0.00 0.020
0.26 0.026
1.57 1.500
</tableData>
</table>
</product>
</function>
<!--function name="aero/coefficient/CDde">
<description>Drag_due_to_elevator_Deflection</description>
<function name="aero/force/Drag_induced">
<description>Induced drag</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/mag-elevator-pos-rad</property>
<value>0.0500</value>
</product>
</function-->
<function name="aero/force/Drag_elevator">
<description>Drag due to Elevator Deflection</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<abs><property>fcs/elevator-pos-norm</property></abs>
<value>0.055</value>
<property>aero/cl-squared</property>
<value>0.043</value>
</product>
</function>
<!--function name="aero/coefficient/CDbeta">
<description>Drag_due_to_sideslip</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/mag-beta-rad</property>
<value>0.2000</value>
</product>
</function-->
<function name="aero/force/Drag_beta">
<description>Drag_due_to_sideslip</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/mag-beta-rad</property>
<value>0.2000</value>
</product>
</function>
<!--function name="aero/coefficient/CDgear">
<description>Drag_due_to_landing_gear</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>gear/gear-pos-norm</property>
<value>0.0400</value>
</product>
</function-->
<function name="aero/force/Drag_gear">
<description>Drag due to gear</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>gear/gear-pos-norm</property>
<value>0.04</value>
</product>
</function>
<!--function name="aero/coefficient/CDspeedbrake">
<description>Drag_due_to_speedbrake</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/speedbrake-pos-norm</property>
<value>0.0400</value>
</product>
</function-->
<function name="aero/force/Drag_speedbrake">
<description>Drag due to speedbrakes</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/speedbrake-pos-norm</property>
<value>0.04</value>
</product>
</function>
<!--function name="aero/coefficient/CDo">
<description>Drag_at_zero_lift</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<value>0.016</value>
</product>
</function-->
<function name="aero/force/Drag_mach">
<description>Drag due to mach</description>
<product>
@ -1266,24 +1018,68 @@ YAW MOI_________3950000______23089847_______24848934
</product>
</function>
</axis>
<function name="aero/force/Drag_flap">
<description>Drag due to flaps</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/flap-pos-deg</property>
<value> 0.00197 </value>
</product>
</function>
<axis name="SIDE">
<!-- function name="aero/coefficient/CYb">
<description>Side_force_due_to_beta</description>
<function name="aero/force/Drag_gear">
<description>Drag due to gear</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>gear/gear-pos-norm</property>
<value>0.025</value>
</product>
</function>
<function name="aero/force/Drag_speedbrake">
<description>Drag due to speedbrakes</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/speedbrake-pos-norm</property>
<value>0.02</value>
</product>
</function>
<function name="aero/force/Drag_beta">
<description>Drag due to sideslip</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar>aero/beta-rad</independentVar>
<independentVar lookup="row">aero/beta-rad</independentVar>
<tableData>
-0.3500 0.5000
0.0000 0.0000
0.3500 -0.5000
-1.57 1.230
-0.26 0.050
0.00 0.000
0.26 0.050
1.57 1.230
</tableData>
</table>
</product>
</function -->
</function>
<function name="aero/force/Drag_elevator">
<description>Drag due to Elevator Deflection</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<abs><property>fcs/elevator-pos-norm</property></abs>
<value>0.04</value>
</product>
</function>
</axis>
<axis name="SIDE">
<function name="aero/force/Side_beta">
<description>Side force due to beta</description>
<product>
@ -1297,22 +1093,7 @@ YAW MOI_________3950000______23089847_______24848934
</axis>
<axis name="ROLL">
<!--function name="aero/coefficient/Clb">
<description>Roll_moment_due_to_beta</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<table>
<independentVar>aero/beta-rad</independentVar>
<tableData>
-0.3500 0.0100
0.0000 0.0000
0.3500 -0.0100
</tableData>
</table>
</product>
</function-->
<function name="aero/moment/Roll_beta">
<description>Roll moment due to beta</description>
<product>
@ -1324,19 +1105,6 @@ YAW MOI_________3950000______23089847_______24848934
</product>
</function>
<!--function name="aero/coefficient/Clp">
<description>Roll_moment_due_to_roll_rate_(roll_damping)</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/p-aero-rad_sec</property>
<value>-0.5000</value>
</product>
</function-->
<function name="aero/moment/Roll_damp">
<description>Roll moment due to roll rate</description>
<product>
@ -1349,18 +1117,6 @@ YAW MOI_________3950000______23089847_______24848934
</product>
</function>
<!--function name="aero/coefficient/Clr">
<description>Roll_moment_due_to_yaw_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/r-aero-rad_sec</property>
<value>0.0050</value>
</product>
</function-->
<function name="aero/moment/Roll_yaw">
<description>Roll moment due to yaw rate</description>
<product>
@ -1369,29 +1125,10 @@ YAW MOI_________3950000______23089847_______24848934
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/r-aero-rad_sec</property>
<value>0.005</value>
<value>0.15</value>
</product>
</function>
<!--function name="aero/coefficient/Clda">
<description>Roll_moment_due_to_aileron</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/left-aileron-pos-rad</property>
<!- value>0.2000</value -> <!- Excesive roll !!! ->
<table>
<independentVar lookup="row">velocities/mach</independentVar>
<tableData>
0.0 0.100
2.0 0.033
</tableData>
</table>
</product>
</function-->
<function name="aero/moment/Roll_aileron">
<description>Roll moment due to aileron</description>
<product>
@ -1399,27 +1136,10 @@ YAW MOI_________3950000______23089847_______24848934
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/left-aileron-pos-rad</property>
<table>
<independentVar lookup="row">velocities/mach</independentVar>
<tableData>
<!-- 0.0 0.100 -->
0.0 0.080
2.0 0.033
</tableData>
</table>
<value>0.1</value>
</product>
</function>
<!--function name="aero/coefficient/Cldr">
<description>Roll_moment_due_to_rudder</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/rudder-pos-rad</property>
<value>0.0050</value>
</product>
</function-->
<function name="aero/moment/Roll_rudder">
<description>Roll moment due to rudder</description>
<product>
@ -1427,96 +1147,81 @@ YAW MOI_________3950000______23089847_______24848934
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/rudder-pos-rad</property>
<value>0.005</value>
<value>0.01</value>
</product>
</function>
</axis>
<axis name="PITCH">
<function name="aero/moment/Pitch_zero_alpha_and_flaps">
<description>Pitching_moment_at_zero_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<table>
<independentVar>fcs/flap-pos-deg</independentVar>
<tableData>
0.0000 0.0000
40.0000 -0.1000
</tableData>
</table>
</product>
</function>
<function name="aero/moment/Pitch_alpha">
<description>Pitch_moment_due_to_alpha</description>
<description>Pitch moment due to alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>aero/alpha-rad</property>
<!-- value>-4.0000</value> -->
<value>-0.8</value>
<value>-0.6</value>
</product>
</function>
<function name="aero/moment/Pitch_elevator">
<description>Pitch_moment_due_to_elevator_Deflection</description>
<description>Pitch moment due to elevator</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>fcs/elevator-pos-rad</property>
<!-- <value>-1.5000</value> Excesive Pitch -->
<table>
<independentVar lookup="row">velocities/mach</independentVar>
<tableData>
<!-- 0.0 -1.200 -->
0.0 -1.000
0.0 -1.200
2.0 -0.300
</tableData>
</table>
</product>
</function>
<function name="aero/moment/Pitch_damp">
<description>Pitch_moment_due_to_pitch_rate</description>
<description>Pitch moment due to pitch rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>aero/ci2vel</property>
<property>velocities/q-aero-rad_sec</property>
<!--value>-10.0000</value-->
<value>-10</value>
<value>-17</value>
</product>
</function>
<function name="aero/moment/Pitch_alpha_rate">
<description>Pitch_moment_due_to_alpha_rate</description>
<function name="aero/moment/Pitch_alphadot">
<description>Pitch moment due to alpha rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>aero/ci2vel</property>
<property>aero/alphadot-rad_sec</property>
<!--value>-12.0000</value-->
<value>-12</value>
<value>-6</value>
</product>
</function>
</axis>
<axis name="YAW">
<!--function name="aero/coefficient/Cnr">
<description>Yaw_moment_due_to_yaw_rate</description>
<function name="aero/moment/Yaw_beta">
<description>Yaw moment due to beta</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/r-aero-rad_sec</property>
<value>-0.0400</value>
<property>aero/beta-rad</property>
<value>0.12</value>
</product>
</function-->
</function>
<function name="aero/moment/Yaw_damp">
<description>Yaw moment due to yaw rate</description>
<product>
@ -1528,37 +1233,7 @@ YAW MOI_________3950000______23089847_______24848934
<value>-0.15</value>
</product>
</function>
<!--function name="aero/coefficient/Cnb">
<description>Yaw_moment_due_to_beta</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/beta-rad</property>
<value>0.2000</value>
</product>
</function-->
<function name="aero/moment/Yaw_beta">
<description>Yaw moment due to beta</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/beta-rad</property>
<value>0.12</value>
</product>
</function>
<!--function name="aero/coefficient/Cndr">
<description>Yaw_moment_due_to_rudder</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/rudder-pos-rad</property>
<!- <value>-0.5000</value> Excesive Yaw->
<value>-0.3</value>
</product>
</function-->
<function name="aero/moment/Yaw_rudder">
<description>Yaw moment due to rudder</description>
<product>
@ -1566,12 +1241,11 @@ YAW MOI_________3950000______23089847_______24848934
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/rudder-pos-rad</property>
<!--value>-0.2</value-->
<value>-0.15</value>
<value>-0.1</value>
</product>
</function>
<!--function name="aero/moment/Yaw_aileron">
<function name="aero/moment/Yaw_aileron">
<description>Adverse yaw</description>
<product>
<property>aero/qbar-psf</property>
@ -1580,13 +1254,11 @@ YAW MOI_________3950000______23089847_______24848934
<property>fcs/left-aileron-pos-rad</property>
<value>0</value>
</product>
</function-->
</function>
</axis>
</aerodynamics>
</aerodynamics>
<external_reactions>
<force name="pushback" frame="BODY">