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Airbus A320 [Family]

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Re: Airbus A320 [Family]

Postby FGRS » Tue Feb 18, 2014 7:46 pm

The real trouble is called A321.

That A/C is by far the worst. I will try that on it.

Every help is welcomed.

Cheers and thanks everyone.
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Re: Airbus A320 [Family]

Postby daveculp » Wed Feb 19, 2014 1:52 am

IRL and in the sim all airplanes should have elevator trim set for takeoff. For larger airplanes there can be a wide range of trim settings depending on payload and fuel. If you have the time you can, through flight testing or through calculation, come up with a table of good settings for various loads. As a first guess a setting of -0.15 to -0.2 seems to work well.
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Re: Airbus A320 [Family]

Postby HelldiverSquadron » Wed Feb 19, 2014 4:40 pm

-0.15? really? Hm, I'll try that. thats an all-around good setting for a normal pax/fuel load as far as Im aware. I'll check though. faa for the usa and australia has an aviation department thingy
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Re: Airbus A320 [Family]

Postby ja sam niko » Thu Mar 20, 2014 7:39 pm

Some bad and good news. Bad ones.

Still no way to solve the problems with this problematic family .

So I will have to ask again,common at least someone ,what and where to change?

After a lot of changing and testing,the aircraft (A321) takes off normally,at about 160 . On the climb-out,tends to up to 20 -30 deg,not so easy to control. When retracting flaps,it reacts with a unpredictable diving...which is quite tricky to control. After enabling the autopilot,the plane stabilizes and follows the set VS ,IAS, heading....everything.

When leveling off on the selected alt,there is no pitch -dive that goes on and on,like before. Now pitch is higher than normal,and it stays like that though out the flight.

I have also tried to use the FDM data from some old Omega's A330 which is 98% the same as the A320 ,but the result was catastrophic. Just to say ,that A330 have one of the most reliable FDMs I have ever seen. Even without the FBW ,i's really nice plane to fly on.




So after adding just this one fdm function from that old A330 to the A321's fdm and some changes to the elevators,I managed to achieve this current behavior of the A321.


Code: Select all
    <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/flap-pos-deg</property>
           <value> 0.03 </value>
       </product>
    </function>



So now it looks like this:

Code: Select all
<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="A320-211" version="2.0" release="BETA"
xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

<fileheader>
   <author> Unknown </author>
   <filecreationdate> 2003-01-01 </filecreationdate>
   <version> Version </version>
   <description> Airbus A320 </description>
</fileheader>

<metrics>
   <wingarea  unit="FT2"> 1319.79 </wingarea>
   <wingspan  unit="FT" >  111.26 </wingspan>
   <wing_incidence>          1.03 </wing_incidence>
   <chord     unit="FT" >   13.76 </chord>
   <htailarea unit="FT2">  334.24 </htailarea>
   <htailarm  unit="FT" >   57.88 </htailarm>
   <vtailarea unit="FT2">  248.79 </vtailarea>
   <vtailarm  unit="FT" >   57.33 </vtailarm>
   <location name="AERORP" unit="IN">
   <x> 642.122 </x>
   <y> 0 </y>
   <z> -25.2091 </z>
   </location>
   <location name="EYEPOINT" unit="IN">
   <x> 80 </x>
   <y> -30 </y>
   <z> 70 </z>
   </location>
   <location name="VRP" unit="IN">
   <x> 661.1 </x>
   <y> 0 </y>
   <z> -37 </z>
   </location>
</metrics>

<mass_balance>
   <ixx unit="SLUG*FT2">    611903 </ixx>
   <iyy unit="SLUG*FT2">   1735389 </iyy>
   <izz unit="SLUG*FT2">   2301293 </izz>
   <ixy unit="SLUG*FT2">         0 </ixy>
   <ixz unit="SLUG*FT2">         0 </ixz>
   <iyz unit="SLUG*FT2">         0 </iyz>
   <emptywt unit="LBS" >     87274 </emptywt>
   <location name="CG" unit="IN">
   <x> 642.122 </x>
   <y> 0 </y>
   <z> -41.7398 </z>
   </location>

   <pointmass name="Crew">
      <weight unit="LBS">600</weight>
      <location name="POINTMASS" unit="IN">
         <x>400</x>
         <y>0</y>
         <z>0</z>
      </location>
   </pointmass>
   <pointmass name="PAX">
      <weight unit="LBS">75500</weight>
      <location name="POINTMASS" unit="IN">
         <x>705</x>
         <y>0</y>
         <z>0</z>
      </location>
   </pointmass>
</mass_balance>

<ground_reactions>
   <contact type="BOGEY" name="NOSE_LG">
   <location unit="IN">
      <x> 29.566964</x>
      <y> 0 </y>
      <z> -137.9617 </z>
   </location>
   <static_friction> 0.5 </static_friction>
   <dynamic_friction> 0.8 </dynamic_friction>
   <rolling_friction> 0.02 </rolling_friction>
   <spring_coeff unit="LBS/FT"> 75000 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 16978.5 </damping_coeff>
   <max_steer unit="DEG"> 75 </max_steer>
   <brake_group> NONE </brake_group>
   <retractable>1</retractable>
   </contact>
   <contact type="BOGEY" name="LEFT_MLG">
   <location unit="IN">
      <x> 699.9243 </x>
      <y> -149.4094 </y>
      <z> -152.6824 </z>
   </location>
   <static_friction> 0.5 </static_friction>
   <dynamic_friction> 0.8 </dynamic_friction>
   <rolling_friction> 0.02 </rolling_friction>
   <spring_coeff unit="LBS/FT"> 180000 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 33957 </damping_coeff>
   <max_steer unit="DEG"> 0.0 </max_steer>
   <brake_group> LEFT </brake_group>
   <retractable>1</retractable>
   </contact>
   <contact type="BOGEY" name="RIGHT_MLG">
   <location unit="IN">
      <x> 697.3425 </x>
      <y> 149.4094 </y>
      <z> -152.6824</z>
   </location>
   <static_friction> 0.5 </static_friction>
   <dynamic_friction> 0.8 </dynamic_friction>
   <rolling_friction> 0.02 </rolling_friction>
   <spring_coeff unit="LBS/FT"> 180000 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 33957 </damping_coeff>
   <max_steer unit="DEG"> 0.0 </max_steer>
   <brake_group> RIGHT </brake_group>
   <retractable>1</retractable>
   </contact>

   <contact type="STRUCTURE" name="NOSE_1">
   <location unit="IN">
      <x> 205.905536 </x>
      <y> 0 </y>
      <z> -38.1374 </z>
   </location>
   <static_friction> 1.0 </static_friction>
   <dynamic_friction> 1.4 </dynamic_friction>
   <rolling_friction> 1.0 </rolling_friction>
   <spring_coeff unit="LBS/FT"> 1.5e+06 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
   <max_steer unit="DEG"> 0.0 </max_steer>
   <brake_group> NONE </brake_group>
   <retractable>0</retractable>
   </contact>
   <contact type="STRUCTURE" name="NOSE_2">
   <location unit="IN">
      <x> 296.220436 </x>
      <y> 0 </y>
      <z> -55.0271 </z>
   </location>
   <static_friction> 1.0 </static_friction>
   <dynamic_friction> 1.4 </dynamic_friction>
   <rolling_friction> 1.0 </rolling_friction>
   <spring_coeff unit="LBS/FT"> 1.5e+06 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
   <max_steer unit="DEG"> 0.0 </max_steer>
   <brake_group> NONE </brake_group>
   <retractable>0</retractable>
   </contact>
   <contact type="STRUCTURE" name="CENTER_1">
   <location unit="IN">
      <x> 274.0157 </x>
      <y> 0 </y>
      <z> -60.0665 </z>
   </location>
   <static_friction> 1.0 </static_friction>
   <dynamic_friction> 1.4 </dynamic_friction>
   <rolling_friction> 1.0 </rolling_friction>
   <spring_coeff unit="LBS/FT"> 1.5e+06 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
   <max_steer unit="DEG"> 0.0 </max_steer>
   <brake_group> NONE </brake_group>
   <retractable>0</retractable>
   </contact>
   <contact type="STRUCTURE" name="CENTER_2">
   <location unit="IN">
      <x> 930 </x>
      <y> 0 </y>
      <z> -60.0665 </z>
   </location>
   <static_friction> 1.0 </static_friction>
   <dynamic_friction> 1.4 </dynamic_friction>
   <rolling_friction> 1.0 </rolling_friction>
   <spring_coeff unit="LBS/FT"> 1.5e+06 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
   <max_steer unit="DEG"> 0.0 </max_steer>
   <brake_group> NONE </brake_group>
   <retractable>0</retractable>
   </contact>
   <contact type="STRUCTURE" name="TAIL_1">
   <location unit="IN">
      <x> 992.87399 </x>
      <y> 0 </y>
      <z> -44.7722 </z>
   </location>
   <static_friction> 1.0 </static_friction>
   <dynamic_friction> 1.4 </dynamic_friction>
   <rolling_friction> 1.0 </rolling_friction>
   <spring_coeff unit="LBS/FT"> 1.5e+06 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
   <max_steer unit="DEG"> 0.0 </max_steer>
   <brake_group> NONE </brake_group>
   <retractable>0</retractable>
   </contact>
   <contact type="STRUCTURE" name="TAIL_2">
   <location unit="IN">
      <x> 1119.88189 </x>
      <y> 0 </y>
      <z> -18.8067 </z>
   </location>
   <static_friction> 1.0 </static_friction>
   <dynamic_friction> 1.4 </dynamic_friction>
   <rolling_friction> 1.0 </rolling_friction>
   <spring_coeff unit="LBS/FT"> 1.5e+06 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
   <max_steer unit="DEG"> 0.0 </max_steer>
   <brake_group> NONE </brake_group>
   <retractable>0</retractable>
   </contact>
   <contact type="STRUCTURE" name="TAIL_3">
   <location unit="IN">
      <x> 1236.49609 </x>
      <y> 0 </y>
      <z> -10.2599 </z>
   </location>
   <static_friction> 1.0 </static_friction>
   <dynamic_friction> 1.4 </dynamic_friction>
   <rolling_friction> 1.0 </rolling_friction>
   <spring_coeff unit="LBS/FT"> 1.5e+06 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
   <max_steer unit="DEG"> 0.0 </max_steer>
   <brake_group> NONE </brake_group>
   <retractable>0</retractable>
   </contact>
   <contact type="STRUCTURE" name="TAIL_4">
   <location unit="IN">
      <x> 232.59841 </x>
      <y> 0 </y>
      <z> 47.4138 </z>
   </location>
   <static_friction> 1.0 </static_friction>
   <dynamic_friction> 1.4 </dynamic_friction>
   <rolling_friction> 1.0 </rolling_friction>
   <spring_coeff unit="LBS/FT"> 1.5e+06 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
   <max_steer unit="DEG"> 0.0 </max_steer>
   <brake_group> NONE </brake_group>
   <retractable>0</retractable>
   </contact>
   <contact type="STRUCTURE" name="WING_TIP_1">
   <location unit="IN">
      <x> 838.8898 </x>
      <y> -667.5197 </y>
      <z> 35.7926 </z>
   </location>
   <static_friction> 1.0 </static_friction>
   <dynamic_friction> 1.4 </dynamic_friction>
   <rolling_friction> 1.0 </rolling_friction>
   <spring_coeff unit="LBS/FT"> 1.5e+06 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
   <max_steer unit="DEG"> 0.0 </max_steer>
   <brake_group> NONE </brake_group>
   <retractable>0</retractable>
   </contact>
   <contact type="STRUCTURE" name="WING_TIP_2">
   <location unit="IN">
      <x> 838.8898 </x>
      <y> 667.5197 </y>
      <z> 35.7926 </z>
   </location>
   <static_friction> 1.0 </static_friction>
   <dynamic_friction> 1.4 </dynamic_friction>
   <rolling_friction> 1.0 </rolling_friction>
   <spring_coeff unit="LBS/FT"> 1.5e+06 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
   <max_steer unit="DEG"> 0.0 </max_steer>
   <brake_group> NONE </brake_group>
   <retractable>0</retractable>
   </contact>
</ground_reactions>

<propulsion>
   <engine file="cfm56_5b3">
   <location unit="IN">
      <x> 589.735 </x>
      <y> -226.575 </y>
      <z> -45.567 </z>
   </location>
   <orient unit="DEG">
      <roll> 0.0 </roll>
      <pitch> 2.2 </pitch>
      <yaw> 1 </yaw>
   </orient>
   <feed>0</feed>
   <feed>1</feed>
   <feed>3</feed>
   <feed>4</feed>
   <feed>5</feed>
   <thruster file="direct">
      <location unit="IN">
      <x> 589.735 </x>
      <y> -226.575 </y>
      <z> -45.567 </z>
      </location>
      <orient unit="DEG">
      <roll> 0.0 </roll>
      <pitch> 2.2 </pitch>
      <yaw> 1 </yaw>
      </orient>
   </thruster>
   </engine>
   <engine file="cfm56_5b3">
   <location unit="IN">
      <x> 589.735 </x>
      <y> 226.575 </y>
      <z> -45.567 </z>
   </location>
   <orient unit="DEG">
      <roll> 0.0 </roll>
      <pitch> 2.2 </pitch>
      <yaw> -1 </yaw>
   </orient>
   <feed>0</feed>
   <feed>1</feed>
   <feed>3</feed>
   <feed>4</feed>
   <feed>5</feed>
   <thruster file="direct">
      <location unit="IN">
      <x> 589.735 </x>
      <y> 226.575 </y>
      <z> -45.567 </z>
      </location>
      <orient unit="DEG">
      <roll> 0.0 </roll>
      <pitch> 2.2 </pitch>
      <yaw> -1 </yaw>
      </orient>
   </thruster>
   </engine>
   <tank type="FUEL">    <!-- Left Tank (Inner) -->
      <location unit="IN">
         <x> 630.6588 </x>
         <y> -236.2992 </y>
         <z> -33.9470 </z>
      </location>
      <capacity unit="LBS"> 12186.9 </capacity>
      <contents unit="LBS"> 2437.38 </contents>
   </tank>
   <tank type="FUEL">    <!-- Left Tank (Outer) -->
      <location unit="IN">
         <x> 737.4190 </x>
         <y> -457.4259 </y>
         <z> -8.0898 </z>
      </location>
      <capacity unit="LBS"> 1548.8 </capacity>
      <contents unit="LBS"> 154.88 </contents>
   </tank>
   <tank type="FUEL">    <!-- Left Tank (Surge) -->
      <location unit="IN">
         <x> 788.4322 </x>
         <y> -574.4148 </y>
         <z> 3.1080 </z>
      </location>
      <capacity unit="LBS"> 328.13 </capacity>
      <contents unit="LBS"> 0 </contents>
   </tank>
   <tank type="FUEL">    <!-- Center Tank -->
      <location unit="IN">
         <x> 580.9955 </x>
         <y> 0 </y>
         <z> -47.0 </z>
      </location>
      <capacity unit="LBS"> 14520 </capacity>
      <contents unit="LBS"> 0 </contents>
   </tank>
   <tank type="FUEL">    <!-- Right Tank (Inner) -->
      <location unit="IN">
         <x> 630.6588 </x>
         <y> 236.2992 </y>
         <z> -33.9470 </z>
      </location>
      <capacity unit="LBS"> 12186.9 </capacity>
      <contents unit="LBS"> 2437.38 </contents>
   </tank>
   <tank type="FUEL">    <!-- Right Tank (Outer) -->
      <location unit="IN">
         <x> 737.4190 </x>
         <y> 457.4259 </y>
         <z> -8.0898 </z>
      </location>
      <capacity unit="LBS"> 1548.8 </capacity>
      <contents unit="LBS"> 154.88 </contents>
   </tank>
   <tank type="FUEL">    <!-- Right Tank (Surge) -->
      <location unit="IN">
         <x> 788.4322 </x>
         <y> 574.4148 </y>
         <z> 3.1080 </z>
      </location>
      <capacity unit="LBS"> 328.13 </capacity>
      <contents unit="LBS"> 0 </contents>
   </tank>
</propulsion>

<system file="pushback" />

<flight_control name="FCS: A320">
   <channel name="Pitch">
   <summer name="Pitch Trim Sum">
      <input>fcs/elevator-cmd-norm</input>
      <input>fcs/pitch-trim-cmd-norm</input>
      <clipto>
      <min>-1</min>
      <max>1</max>
      </clipto>
   </summer>

   <aerosurface_scale name="Elevator Control">
      <input>fcs/pitch-trim-sum</input>
      <gain>0.018</gain>
      <range>
      <min>-20</min>
      <max>15</max>
      </range>
      <output>fcs/elevator-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="Elevator position normalized">
      <input>fcs/elevator-pos-deg</input>
      <domain>
      <min>-20</min>
      <max>15</max>
      </domain>
      <range>
      <min>-1</min>
      <max>1</max>
      </range>
      <output>fcs/elevator-pos-norm</output>
   </aerosurface_scale>
   </channel>
   <channel name="Roll">
   <summer name="Roll Trim Sum">
      <input>fcs/aileron-cmd-norm</input>
      <input>fcs/roll-trim-cmd-norm</input>
      <clipto>
      <min>-1</min>
      <max>1</max>
      </clipto>
   </summer>

   <aerosurface_scale name="Left Aileron Control">
      <input>fcs/roll-trim-sum</input>
      <gain>0.02</gain>
      <range>
      <min>-25</min>
      <max>25</max>
      </range>
      <output>fcs/left-aileron-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="Right Aileron Control">
      <input>-fcs/roll-trim-sum</input>
      <gain>0.02</gain>
      <range>
      <min>-25</min>
      <max>25</max>
      </range>
      <output>fcs/right-aileron-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="Left Aileron position normalized">
      <input>fcs/left-aileron-pos-deg</input>
      <domain>
      <min>-25</min>
      <max>25</max>
      </domain>
      <range>
      <min>-0.75</min>
      <max>1</max>
      </range>
      <output>fcs/left-aileron-pos-norm</output>
   </aerosurface_scale>

   <aerosurface_scale name="Right Aileron position normalized">
      <input>fcs/right-aileron-pos-deg</input>
      <domain>
      <min>-25</min>
      <max>25</max>
      </domain>
      <range>
      <min>-0.75</min>
      <max>1</max>
      </range>
      <output>fcs/right-aileron-pos-norm</output>
   </aerosurface_scale>
   </channel>
   <channel name="Yaw">
   <pure_gain name="Yaw Damper Rate">
      <input>velocities/r-rad_sec</input>
      <gain>2</gain>
   </pure_gain>

   <pure_gain name="Yaw Damper Beta">
      <input>aero/beta-rad</input>
      <gain>-5</gain>
   </pure_gain>

   <summer name="Yaw Trim Sum">
      <input>fcs/rudder-cmd-norm</input>
      <input>fcs/yaw-trim-cmd-norm</input>
      <clipto>
      <min>-1</min>
      <max>1</max>
      </clipto>
   </summer>

   <summer name="Rudder Sum">
      <input>fcs/yaw-trim-sum</input>
      <input>fcs/yaw-damper-rate</input>
      <input>fcs/yaw-damper-beta</input>
      <clipto>
      <min>-1</min>
      <max>1</max>
      </clipto>
   </summer>

   <aerosurface_scale name="Rudder Control">
      <input>fcs/rudder-sum</input>
      <gain>0.01745</gain>
      <range>
      <min>-25</min>
      <max>25</max>
      </range>
      <output>fcs/rudder-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="Rudder position normalized">
      <input>fcs/rudder-pos-deg</input>
      <domain>
      <min>-25</min>
      <max>25</max>
      </domain>
      <range>
      <min>-1</min>
      <max>1</max>
      </range>
      <output>fcs/rudder-pos-norm</output>
   </aerosurface_scale>
   </channel>
   <channel name="Flaps">
   <kinematic name="Flaps Control">
      <input>fcs/flap-cmd-norm</input>
      <traverse>
      <setting>
         <position>0</position>
         <time>0</time>
      </setting>
      <setting>
         <position>40</position>
         <time>40</time>
      </setting>
      </traverse>
      <output>fcs/flap-pos-deg</output>
   </kinematic>

   <aerosurface_scale name="Flap position normalized">
      <input>fcs/flap-pos-deg</input>
      <domain>
      <min>0</min>
      <max>40</max>
      </domain>
      <range>
      <min>0</min>
      <max>1</max>
      </range>
      <output>fcs/flap-pos-norm</output>
   </aerosurface_scale>
   </channel>
   <channel name="Landing Gear">
   <kinematic name="Gear Control">
      <input>gear/gear-cmd-norm</input>
      <traverse>
      <setting>
         <position>0</position>
         <time>0</time>
      </setting>
      <setting>
         <position>1</position>
         <time>10</time>
      </setting>
      </traverse>
      <output>gear/gear-pos-norm</output>
   </kinematic>
   </channel>
   <channel name="Speedbrake">
   <kinematic name="Speedbrake">
      <input>fcs/speedbrake-cmd-norm</input>
      <traverse>
      <setting>
         <position>0</position>
         <time>0</time>
      </setting>
      <setting>
         <position>1</position>
         <time>2</time>
      </setting>
      </traverse>
      <output>fcs/speedbrake-pos-norm</output>
   </kinematic>
   </channel>
</flight_control>
<aerodynamics>

   <axis name="DRAG">
   <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/coefficient/CDalpha">
      <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
         </tableData>
      </table>
      </product>
   </function>
   <function name="aero/coefficient/CDde">
      <description>Drag_due_to_elevator_Deflection</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/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/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/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>
   </axis>

   <axis name="SIDE">
   <function name="aero/coefficient/CYb">
      <description>Side_force_due_to_beta</description>
      <product>
      <property>aero/qbar-psf</property>
      <property>metrics/Sw-sqft</property>
      <table>
         <independentVar>aero/beta-rad</independentVar>
         <tableData>
         -0.3500   0.5000
         0.0000   0.0000
         0.3500   -0.5000
         </tableData>
      </table>
      </product>
   </function>
   </axis>

   <axis name="LIFT">
   <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/coefficient/CLDe">
      <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>
      </product>
   </function>
       <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/flap-pos-deg</property>
           <value> 0.03 </value>
       </product>
    </function>
   </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/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/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/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>
      </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>
   </axis>

   <axis name="PITCH">
   <function name="aero/coefficient/Cmo">
      <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   0.0400
         40.0000   -0.1000
         </tableData>
      </table>
      </product>
   </function>
   <function name="aero/coefficient/Cmalpha">
      <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>
      </product>
   </function>
   <function name="aero/coefficient/CmDe">
      <description>Pitch_moment_due_to_elevator_Deflection</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>
      </product>
   </function>
   <function name="aero/coefficient/Cmq">
      <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>
      </product>
   </function>
   <function name="aero/coefficient/Cmadot">
      <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>
      </product>
   </function>
   </axis>

   <axis name="YAW">
   <function name="aero/coefficient/Cnr">
      <description>Yaw_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>-0.0400</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/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>
      </product>
   </function>
   </axis>
</aerodynamics>

   <external_reactions>
      <force name="pushback" frame="BODY">
         <location unit="IN">
            <x>294</x>
            <y>0</y>
            <z>-149</z>
         </location>
         <direction>
            <x>1</x>
            <y>0</y>
            <z>0</z>
         </direction>
      </force>
   </external_reactions>
</fdm_config>




Now ,the problem seems to be the insufficient lift of the wings .

Does anyone have some idea how to fix this completely?


Good ones.
I think I'm close to solving the rudder hard over on start up.

Thank you all. .

Cheers
The worst floods in the Balkans ever,follow these links to learn more how to help. Thank you.
http://www.google.org/crisisresponse/2014-balkans-floods

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Re: Airbus A320 [Family]

Postby HelldiverSquadron » Thu Mar 20, 2014 10:33 pm

ah...
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Re: Airbus A320 [Family]

Postby ja sam niko » Sat Mar 22, 2014 5:55 pm

I 'm giving up of any further work on this.

Mostly because I just can't do it. The FDM is one huge disaster and there's nothing I can do.

Also,the reason is that I had no support or help from anyone here.

You just don't care...all of you.
The worst floods in the Balkans ever,follow these links to learn more how to help. Thank you.
http://www.google.org/crisisresponse/2014-balkans-floods

http://www.mvp.gov.ba/HTML/eng-help.pdf
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Re: Airbus A320 [Family]

Postby Bjoern » Sun Mar 23, 2014 3:33 pm

Of course I don't care; I don't fly this thing!

However, I am two thirds down a road to hell by trying to make a MSFS 727 fly closer to the published numbers. And as the situation is similar to yours, here's what I've learned so far...

1. You need tons of time.
2. You need performance manuals for the aircraft and its engines.
3. You need documentation of the simulator's handling of flight dynamics.
4. You need a basic understanding of aerodynamics and aircraft performance.
5. You need honest dedication to see this through.

Put all five into a blender and the end result should be something usable or at least something better than the current state.

If you think that fixing a complete flight dynamics envelope is something that can be done on a rainy afternoon while someone holds your hand on live-chat, you're dead wrong. You need a bloody lot of time, you *really* need to study if you don't have the background (I, for myself, don't) and, in worst case. you're on your own all along the way. Flight dynamics engineering isn't the most popular activity among aircraft developers (at least in the MSFS world) and experts for consultation are hard to come by.

So if you really want to see this thing fixed, do more ground work or throw it away and try the A320neo model.

But in any case, never, ever again, accuse the bunch of volunteers keeping FG running of "not caring". People have only so much time available for FG a day and have absolutely no obligation for "serve-cut up-munch-swallow" levels of support.
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Re: Airbus A320 [Family]

Postby ja sam niko » Sun Mar 23, 2014 8:51 pm

The reason why I was trying to fix that,is that my PC can't run the Omega's Neo.

And before you start talking about some nice and shiny "machine" I will tell you this,I can't have anything better,and probably I won't have better ever.

Not everyone have all the best. :cry:
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Re: Airbus A320 [Family]

Postby Bjoern » Mon Mar 24, 2014 3:07 pm

Okay, so using the NEO is not an option then and I'm cool with that.
This, however, means that you really have to do some digging, studying and calculating now if you want this bird to fly by the numbers!

Start with the YASIM (or JSB) documentation and primarily determine if they suggest anything in terms of tackling flight dynamics creation.
Then try to find as much info on the A320 as possible. Determine what aerodynamic equations you can solve with the given info on the A320 and work your way from these to the other equations. If you have the aerodynamic info hacked into the FD file, you should get some usable drag numbers. With these drag numbers, you can tackle engine performance with which you *should* be able to results reasonably close to the published numbers. If you don't have data for some variables, make assumptions and tweak them until you're content.
And if you don't understand what some equations do: Google and Wikipedia. There's lots of at least semi-usable info about them on the web!

(Or just use the NEO's flight dynamics information, add a bit of drag and decrease engine efficiency and you should get something resonably close to a regular A320.)
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Re: Airbus A320 [Family]

Postby ja sam niko » Mon Mar 24, 2014 3:24 pm

Nice to see some understanding here... :D

Ok first of all,A320 has the complete FDM,but something in it,is making it to have some weird pitch-dive behavior. It goes up-down,on and on....and all of that is after enabling the AP. With the increase of weight,this problem becomes muuuuuuuch more present. It goes to the point when the aircraft just stalls and goes down....

By pure chance ,I found the way to reduce that weird behavior,so it's basically out. But then there's something else,the nose is quite high up. It can fly like that but landing is more than difficult ...impossible. So I found a way to put some data from some old A330 made by Omega (I will post the screenshot of it here) ,which lowered the nose a bit down but still that's waaay to problematic to be good.

I 'm aware that the nose should be a little bit up,but not like it is now. Also,I tried to use the data from NEO,but as strange as it may look,it's almost (ok 98% ) the same as it is in the A320 Family. The main difference is "Fly by Wire" which in Neo ,helps the FDM to make the aircraft more stable and the overall behavior of the aircraft much more reliable.. You just know that the aircarft will react and fly just the way you want it.

I will post here the .xml files of both,A320 and that old A330 ,so if anyone else have some idea ,I'm ready to do it.

Thanks everyone and of course ,thanks Bjoern.

Cheers

BTW ,would it possible to use the FDM data from the 737-300?
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Re: Airbus A320 [Family]

Postby Soitanen » Mon Mar 24, 2014 5:00 pm

Main difference between 737 and 320 - Fly by Wire.
To make realistick behaviour from the sidestick, it must not be connected directly to control surface. Signal from elevator (if build very easy model) sets normal acceleration in Z axis. If sidestick is in neutral position - aircraft tries to maintain acceleration at 1G. If it fully pulled, then AC tries to make something like 2.5G (depends on flaps position). In my 737 I have autopilot, which controls pitch via acceleration. So it's possible to do the same thing for A320. Taking whole FDM from another aircraft can be not best idea, IMHO.
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Re: Airbus A320 [Family]

Postby ja sam niko » Mon Mar 24, 2014 5:49 pm

OK....thanks for clearing that up.

So I will have to find something useful from some other Airbus.

Talking of which,here are two .xml files ,first one is from this Airbus A330-200 (247) .

Image


A330-200 (247) .xml file

Code: Select all
<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="A330-243" version="2.0" release="BETA"
   xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
   xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

<fileheader>
  <author> Aeromatic, Narendran </author>
  <filecreationdate> 2011-08-08 </filecreationdate>el
  <version>$Revision: 1.10 $</version>
  <description> Tweaked Flight Dynamics of an Aeromatic FDM for A330-200 </description>
</fileheader>

<!-- Sources http://en.wikipedia.org/wiki/Airbus_A330#Specifications, http://www.airbus.com, ac3D, http://jsbsim.sourceforge.net/JSBSimReferenceManual.pdf -->

<!--
  File:     A330-243.xml
  Inputs:
    name:          A330-243
    type:          two-engine transonic transport
    max weight:    507150 lb
    wing span:     197.8443 ft
    length:        192.98842 ft
    wing area:     3892.624 sq-ft
    gear type:     tricycle
    retractable?:  yes
    # engines:     2
    engine type:   turbine
    engine layout: wings
    yaw damper?    yes
  Outputs:
    wing loading:  130.28 lb/sq-ft
    CL-alpha:      4.4 per radian
    CL-0:          0.2
    CL-max:        1.2
    CD-0:          0.02
    K:             0.043

UNIT CONVERSIONS :
1 meter = 3.2 feet
1 meter = 39.4 inches
1 sq. m = 10.24 sq. ft.
1 feet  = 12 inches

-->

<metrics>
<!-- Wingarea = 3,892 sq ft from wikipedia -->
   <wingarea  unit="FT2">3892.62 </wingarea>
<!-- Wingspan = 197.84 ft from wikipeda -->
   <wingspan  unit="FT" >  197.84 </wingspan>
<!-- Wing Incidence = 2 deg from Aeromatic -->
   <wing_incidence unit="DEG"> 2 </wing_incidence>
<!-- Chord = 6.55 m from Ac3D -->
   <chord     unit="FT" >   20.96 </chord>
<!-- Horizontal Tail Area = 66.6 sq m (calculated on paper) -->
   <htailarea unit="FT2">  681.984 </htailarea>
<!-- Horizontal Tail Arm = 32.2 m from Ac3D -->
   <htailarm  unit="FT" >   103.04 </htailarm>
<!-- Vertical Tail Area = 58.757 m (calculated on paper) -->
   <vtailarea unit="FT2">  499.27 </vtailarea>
<!-- NOT SURE WHAT TO DO HERE YET, USED 747-400 VALUE -->
   <vtailarm  unit="FT" >   0 </vtailarm>
   <location name="AERORP" unit="IN">
     <x> 0 </x>
     <y> 0 </y>
     <z> 0 </z>
   </location>
<!-- Center of AircrafT (0,0,0 in Ac3D) is taken as the Eyepoint -->
   <location name="EYEPOINT" unit="IN">
     <x> 0 </x>
     <y> 0 </y>
     <z> 0 </z>
   </location>
<!-- Center of Aircraft (in Ac3D) is taken as the Vehicle Reference Point -->
   <location name="VRP" unit="IN">
     <x> 0 </x>
     <y> 0 </y>
     <z> 0 </z>
   </location>
</metrics>

<mass_balance>
<!-- I let the intertia values remain as from Aeromatic as I don't know how to calculate it. It should work out as for this is set to an idea Transonic Aircraft. If I feel that the plane needs to turn slower, or be heavier in that aspect, I can just increase the value to what I need it to be -->
        <ixx unit="SLUG*FT2">    562000 </ixx>
        <iyy unit="SLUG*FT2"> 1.473e+06 </iyy>
        <izz unit="SLUG*FT2"> 1.894e+06 </izz>
   <ixy unit="SLUG*FT2">         0 </ixy>
   <ixz unit="SLUG*FT2">         0 </ixz>
   <iyz unit="SLUG*FT2">         0 </iyz>
<!-- Operational Empty Weight = 264,000 lbs from wikipedia -->
   <emptywt unit="LBS" >    264000 </emptywt>
<!-- Center of Gravity (37%) = (-7.99,0,-0.89) m -->
   <location name="CG" unit="IN">
     <x> -55.06 </x>
     <y>   0.00 </y>
     <z> -35.07 </z>
   </location>
</mass_balance>

<ground_reactions>

<!-- Nose Gear Contact Point -->
  <contact type="BOGEY" name="NOSE_GEAR">
   <location unit="IN">
     <x> -961.36 </x>
     <y>   0.00 </y>
     <z> -190.968 </z>
   </location>
   <static_friction>  0.80 </static_friction>
   <dynamic_friction> 0.50 </dynamic_friction>
   <rolling_friction> 0.02 </rolling_friction>
   <spring_coeff unit="LBS/FT"> 180000 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 33957 </damping_coeff>
   <max_steer unit="DEG"> 70 </max_steer>
   <brake_group>NONE</brake_group>
   <retractable>1</retractable>
</contact>

<!-- Left Main Gear Contact Point -->
  <contact type="BOGEY" name="LEFT_MAIN">
   <location unit="IN">
     <x> 0 </x>
     <y> -214.73 </y>
     <z> -207.304 </z>
   </location>
   <static_friction>  0.80 </static_friction>
   <dynamic_friction> 0.50 </dynamic_friction>
   <rolling_friction> 0.02 </rolling_friction>
   <spring_coeff unit="LBS/FT"> 180000 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 33957 </damping_coeff>
   <max_steer unit="DEG">0</max_steer>
   <brake_group>LEFT</brake_group>
   <retractable>1</retractable>
</contact>

<!-- Right Main Gear Contact Point -->
  <contact type="BOGEY" name="RIGHT_MAIN">
   <location unit="IN">
     <x> 0 </x>
     <y> 214.73 </y>
     <z> -207.304 </z>
   </location>
   <static_friction>  0.80 </static_friction>
   <dynamic_friction> 0.50 </dynamic_friction>
   <rolling_friction> 0.02 </rolling_friction>
   <spring_coeff unit="LBS/FT"> 180000 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 33957 </damping_coeff>
   <max_steer unit="DEG">0</max_steer>
   <brake_group>RIGHT</brake_group>
   <retractable>1</retractable>
</contact>

<!-- Left Wing Tip Contact Point -->
  <contact type="STRUCTURE" name="LEFT_WING_TIP">
    <location unit="IN">
     <x> 295.894 </x>
     <y> -1189.092 </y>
     <z> 56.342 </z>
    </location>
    <static_friction>  0.9 </static_friction>
    <dynamic_friction> 0.8 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      200000.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 10000.00 </damping_coeff>
    <brake_group> NONE </brake_group>
    <retractable>0</retractable>
</contact>

<!-- Right Wing Tip Contact Point -->
  <contact type="STRUCTURE" name="RIGHT_WING_TIP">
    <location unit="IN">
     <x> 295.894 </x>
     <y> 1189.092 </y>
     <z> 56.342 </z>
    </location>
    <static_friction>  0.9 </static_friction>
    <dynamic_friction> 0.8 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      200000.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 10000.00 </damping_coeff>
    <brake_group> NONE </brake_group>
    <retractable>0</retractable>
</contact>

<!-- Tail (in case of a tail strike) Contact Point -->
  <contact type="STRUCTURE" name="TAIL_STRIKE">
    <location unit="IN">
     <x> 722.99 </x>
     <y> 0 </y>
     <z> -42.946 </z>
    </location>
    <static_friction>  0.95 </static_friction>
    <dynamic_friction> 0.9 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      200000.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 10000.00 </damping_coeff>
    <brake_group> NONE </brake_group>
    <retractable>0</retractable>
</contact>

<!-- Nose (used for Ditching) Contact Point -->
  <contact type="STRUCTURE" name="TAIL_STRIKE">
    <location unit="IN">
     <x> -981.06 </x>
     <y> 0 </y>
     <z> -70.74 </z>
    </location>
    <static_friction>  0.95 </static_friction>
    <dynamic_friction> 0.9 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      200000.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 10000.00 </damping_coeff>
    <brake_group> NONE </brake_group>
    <retractable>0</retractable>
</contact>

</ground_reactions>

<!-- 2x Rolls Royce Trent 700 (772B-60) Engines -->
<propulsion>

   <engine file="trent_772B-60">
    <location unit="IN">
      <x> -335.294 </x>
      <y> -395.97 </y>
      <z> -90.62 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>1</feed>
    <feed>0</feed>
    <feed>3</feed>
    <thruster file="direct">
     <location unit="IN">
      <x> -335.294 </x>
      <y> -395.97 </y>
      <z> -90.62 </z>
     </location>
     <orient unit="DEG">
       <pitch> -2.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

   <engine file="trent_772B-60">
    <location unit="IN">
      <x> -335.294 </x>
      <y> 395.97 </y>
      <z> -90.62 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>1</feed>
    <feed>2</feed>
    <feed>4</feed>
    <thruster file="direct">
     <location unit="IN">
      <x> -335.294 </x>
      <y> 395.97 </y>
      <z> -90.62 </z>
     </location>
     <orient unit="DEG">
       <pitch> -2.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- Inner Wing Fuel Tank LEFT -->
  <tank type="FUEL" number="0">
     <location unit="IN">
       <x> -10.962 </x>
       <y> -360.51 </y>
       <z> -28.762 </z>
     </location>
     <capacity unit="KG"> 32970 </capacity>
     <contents unit="KG"> 25000 </contents>
  </tank>

<!-- Central Fuel Tank -->
  <tank type="FUEL" number="1">
     <location unit="IN">
       <x> -50.162 </x>
       <y> 0.00 </y>
       <z> -33.884 </z>
     </location>l
     <capacity unit="KG"> 32625 </capacity>
     <contents unit="KG"> 30000 </contents>
  </tank>

<!-- Inner Wing Fuel Tank RIGHT -->
  <tank type="FUEL" number="2">
     <location unit="IN">
       <x> -10.962 </x>
       <y> 360.51 </y>
       <z> -28.762 </z>
     </location>
     <capacity unit="KG"> 32970 </capacity>
     <contents unit="KG"> 25000 </contents>
  </tank>

<!-- Outer Wing Fuel Tank LEFT -->
  <tank type="FUEL" number="3">
     <location unit="IN">
       <x> 120.56 </x>
       <y> -965.3 </y>
       <z> 19.306 </z>
     </location>
     <capacity unit="KG"> 2865 </capacity>
     <contents unit="KG"> 2000 </contents>
  </tank>

<!-- Outer Wing Fuel Tank RIGHT -->
  <tank type="FUEL" number="4">
     <location unit="IN">
       <x> 120.56 </x>
       <y> 965.3 </y>
       <z> 19.306 </z>
     </location>
     <capacity unit="KG"> 2865 </capacity>
     <contents unit="KG"> 2000 </contents>
  </tank>

<!-- Trim Fuel Tank -->
  <tank type="FUEL" number="5">
     <location unit="IN">
       <x> 971.21 </x>
       <y> 0 </y>
       <z> 86.68 </z>
     </location>
     <capacity unit="KG"> 4890 </capacity>
     <contents unit="KG"> 4000 </contents>
  </tank>

</propulsion>

    <system file="pushback"/>

<flight_control name="FCS: A330-243">

  <channel name="Pitch">
   <summer name="Pitch Trim Sum">
      <input>fcs/elevator-cmd-norm</input>
      <input>fcs/pitch-trim-cmd-norm</input>
      <clipto>
        <min> -1 </min>
        <max>  1 </max>
      </clipto>
   </summer>

   <aerosurface_scale name="Elevator Control">
      <input>fcs/pitch-trim-sum</input>
      <range>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </range>
      <output>fcs/elevator-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="elevator normalization">
      <input>fcs/elevator-pos-rad</input>
      <range>
        <min> -1 </min>
        <max>  1 </max>
      </range>
      <output>fcs/elevator-pos-norm</output>
   </aerosurface_scale>

  </channel>

  <channel name="Roll">
   <summer name="Roll Trim Sum">
      <input>fcs/aileron-cmd-norm</input>
      <input>fcs/roll-trim-cmd-norm</input>
      <clipto>
        <min> -1 </min>
        <max>  1 </max>
      </clipto>
   </summer>

   <aerosurface_scale name="Left Aileron Control">
      <input>fcs/roll-trim-sum</input>
      <range>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </range>
      <output>fcs/left-aileron-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="Right Aileron Control">
      <input>fcs/roll-trim-sum</input>
      <range>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </range>
      <output>fcs/right-aileron-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="left aileron normalization">
      <input>fcs/left-aileron-pos-rad</input>
      <domain>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </domain>
      <range>
        <min> -1 </min>
        <max>  1 </max>
      </range>
      <output>fcs/left-aileron-pos-norm</output>
   </aerosurface_scale>

   <aerosurface_scale name="right aileron normalization">
      <input>fcs/right-aileron-pos-rad</input>
      <domain>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </domain>
      <range>
        <min> -1 </min>
        <max>  1 </max>
      </range>
      <output>fcs/right-aileron-pos-norm</output>
   </aerosurface_scale>

  </channel>

  <channel name="Yaw">
   <summer name="Rudder Command Sum">
      <input>fcs/rudder-cmd-norm</input>
      <input>fcs/yaw-trim-cmd-norm</input>
      <clipto>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </clipto>
   </summer>

        <scheduled_gain name="Yaw Damper Rate">
            <input>velocities/r-aero-rad_sec</input>
            <table>
                <independentVar>aero/qbar-psf</independentVar>
                <tableData>
                    3.0000   0.0000   
                    11.0000   2.0000   
                </tableData>
            </table>
        </scheduled_gain>

        <scheduled_gain name="Yaw Damper Beta">
            <input>aero/beta-rad</input>
            <table>
                <independentVar>aero/qbar-psf</independentVar>
                <tableData>
                    3.0000   0.0000   
                    11.0000   0.0000   
                </tableData>
            </table>
        </scheduled_gain>

        <summer name="Yaw Damper Sum">
            <input>fcs/yaw-damper-beta</input>
            <input>fcs/yaw-damper-rate</input>
            <clipto>
                <min>-0.2000</min>
                <max>0.2000</max>
            </clipto>
        </summer>

        <scheduled_gain name="Yaw Damper Final">
            <input>fcs/yaw-damper-sum</input>
            <table>
                <independentVar>aero/qbar-psf</independentVar>
                <tableData>
                    2.9900   0.0000   
                    3.0000   1.0000   
                </tableData>
            </table>
        </scheduled_gain>

   <summer name="Rudder Sum">
      <input>fcs/rudder-command-sum</input>
      <input>fcs/yaw-damper-final</input>
      <clipto>
        <min> -1 </min>
        <max>  1 </max>
      </clipto>
   </summer>

   <aerosurface_scale name="Rudder Control">
      <input>fcs/rudder-sum</input>
      <range>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </range>
      <output>fcs/rudder-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="rudder normalization">
      <input>fcs/rudder-pos-rad</input>
      <domain>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </domain>
      <range>
        <min> -1 </min>
        <max>  1 </max>
      </range>
      <output>fcs/rudder-pos-norm</output>
   </aerosurface_scale>

  </channel>

  <channel name="Flaps">
   <kinematic name="Flaps Control">
     <input>fcs/flap-cmd-norm</input>
     <traverse>
                <setting>
                    <position>0.0</position>
                    <time>0.0000</time>
                </setting>
                <setting>
                    <position>10.000</position>
                    <time>7.0000</time>
                </setting>
                <setting>
                    <position>25.0000</position>
                    <time>5.0000</time>
                </setting>
                <setting>
                    <position>30.0000</position>
                    <time>10.0000</time>
                </setting>
                <setting>
                    <position>40.0000</position>
                    <time>10.0000</time>
                </setting>
     </traverse>
     <output>fcs/flap-pos-deg</output>
   </kinematic>

   <aerosurface_scale name="flap normalization">
      <input>fcs/flap-pos-deg</input>
      <domain>
        <min>  0 </min>
        <max> 35 </max>
      </domain>
      <range>
        <min> 0 </min>
        <max> 1 </max>
      </range>
      <output>fcs/flap-pos-norm</output>
   </aerosurface_scale>

  </channel>

  <channel name="Landing Gear">
   <kinematic name="Gear Control">
     <input>gear/gear-cmd-norm</input>
     <traverse>
       <setting>
          <position> 0 </position>
          <time>     0 </time>
       </setting>
       <setting>
          <position> 1 </position>
          <time>     12 </time>
       </setting>
     </traverse>
     <output>gear/gear-pos-norm</output>
   </kinematic>

  </channel>

  <channel name="Speedbrake">
   <kinematic name="Speedbrake Control">
     <input>fcs/speedbrake-cmd-norm</input>
     <traverse>
       <setting>
          <position> 0 </position>
          <time>     0 </time>
       </setting>
       <setting>
          <position> 1 </position>
          <time>     1 </time>
       </setting>
     </traverse>
     <output>fcs/speedbrake-pos-norm</output>
   </kinematic>

  </channel>

</flight_control>

<aerodynamics>

<!-- Lift due to ground effects to make the take off faster -->
        <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   1.2000   
                          0.1000   1.3200   
                          0.1500   1.3600   
                          0.2000   1.4000   
                          1.1000   1.2000   
                      </tableData>
                  </table>
            </product>
        </function>

  <axis name="LIFT">

            <function name="aero/coefficient/CLalpha">
                <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">velocities/mach</independentVar>
                          <tableData>
                                        0.1000  0.1800  0.6500   
                             -0.200    -0.3400 -0.4000 -0.6800   
                              0.0000    0.0000  0.5000  0.5500   
                              0.2300    1.0000  1.3000  1.3500   
                              0.6000    0.3600  0.4600  0.5000   
                          </tableData>
                      </table>
                </product>
            </function>

    <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/flap-pos-deg</property>
           <value> 0.03 </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>-0.25</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>0.45</value>
       </product>
    </function>

  </axis>

  <axis name="DRAG">

    <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>
            <tableData>
             -1.57       1.200
             -0.26    0.018
              0.00    0.012
              0.26    0.020
              1.57       1.200
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/force/Drag_induced">
       <description>Induced drag</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>aero/cl-squared</property>
           <value>0.035</value>
         </product>
    </function>

    <function name="aero/force/Drag_mach">
       <description>Drag due to mach</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
                0.00      0.000
                0.79      0.000
                1.10      0.023
                1.80      0.015
            </tableData>
          </table>
        </product>
    </function>

    <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> 0.005 </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>0.003</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>0.055</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 lookup="row">aero/beta-rad</independentVar>
            <tableData>
              -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 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>
       </product>
    </function>

  </axis>

  <axis name="SIDE">

    <function name="aero/force/Side_beta">
       <description>Side force due to beta</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>aero/beta-rad</property>
           <value>-1</value>
       </product>
    </function>

  </axis>

  <axis name="ROLL">

    <function name="aero/moment/Roll_beta">
       <description>Roll 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>-0.1</value>
       </product>
    </function>

    <function name="aero/moment/Roll_damp">
       <description>Roll moment due to roll rate</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>-0.4</value>
       </product>
    </function>

    <function name="aero/moment/Roll_yaw">
       <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>0.15</value>
       </product>
    </function>

    <function name="aero/moment/Roll_aileron">
       <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>
          <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_rudder">
       <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>0.01</value>
       </product>
    </function>

  </axis>

  <axis name="PITCH">

    <function name="aero/moment/Pitch_alpha">
       <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>-0.6</value>
       </product>
    </function>

    <function name="aero/moment/Pitch_elevator">
       <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>
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
                              0.0000   -1.3000   
                              2.0000   -0.3250   
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/moment/Pitch_damp">
       <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>-17</value>
       </product>
    </function>

    <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>-6</value>
       </product>
    </function>

  </axis>

  <axis name="YAW">

    <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/moment/Yaw_damp">
       <description>Yaw 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>-0.15</value>
       </product>
    </function>

    <function name="aero/moment/Yaw_rudder">
       <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>-0.1</value>
       </product>
    </function>

    <function name="aero/moment/Yaw_aileron">
       <description>Adverse yaw</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</value>
       </product>
    </function>

  </axis>

</aerodynamics>

</fdm_config>



This is some old A330 made by Omega ,which is very,very close to the A320 Family ,regarding the FDM ,which on this aircraft is very good one. It's the behavior I would like to see on the A320. Since this family of aircraft ,doesn't have the FBW like the Neo,no need for some complicated systems or something.
The worst floods in the Balkans ever,follow these links to learn more how to help. Thank you.
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ja sam niko
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Posts: 210
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Re: Airbus A320 [Family]

Postby ja sam niko » Mon Mar 24, 2014 5:54 pm

A321-200 .xml file

Code: Select all
<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="A320-211" version="2.0" release="BETA"
xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

<fileheader>
   <author> Unknown </author>
   <filecreationdate> 2003-01-01 </filecreationdate>
   <version> Version </version>
   <description> Airbus A320 </description>
</fileheader>

<metrics>
   <wingarea  unit="FT2"> 1319.79 </wingarea>
   <wingspan  unit="FT" >  111.26 </wingspan>
   <wing_incidence>          1.03 </wing_incidence>
   <chord     unit="FT" >   13.76 </chord>
   <htailarea unit="FT2">  334.24 </htailarea>
   <htailarm  unit="FT" >   57.88 </htailarm>
   <vtailarea unit="FT2">  248.79 </vtailarea>
   <vtailarm  unit="FT" >   57.33 </vtailarm>
   <location name="AERORP" unit="IN">
   <x> 642.122 </x>
   <y> 0 </y>
   <z> -25.2091 </z>
   </location>
   <location name="EYEPOINT" unit="IN">
   <x> 80 </x>
   <y> -30 </y>
   <z> 70 </z>
   </location>
   <location name="VRP" unit="IN">
   <x> 661.1 </x>
   <y> 0 </y>
   <z> -37 </z>
   </location>
</metrics>

<mass_balance>
   <ixx unit="SLUG*FT2">    611903 </ixx>
   <iyy unit="SLUG*FT2">   1735389 </iyy>
   <izz unit="SLUG*FT2">   2301293 </izz>
   <ixy unit="SLUG*FT2">         0 </ixy>
   <ixz unit="SLUG*FT2">         0 </ixz>
   <iyz unit="SLUG*FT2">         0 </iyz>
   <emptywt unit="LBS" >     87274 </emptywt>
   <location name="CG" unit="IN">
   <x> 642.122 </x>
   <y> 0 </y>
   <z> -41.7398 </z>
   </location>

   <pointmass name="Crew">
      <weight unit="LBS">600</weight>
      <location name="POINTMASS" unit="IN">
         <x>400</x>
         <y>0</y>
         <z>0</z>
      </location>
   </pointmass>
   <pointmass name="PAX">
      <weight unit="LBS">75500</weight>
      <location name="POINTMASS" unit="IN">
         <x>705</x>
         <y>0</y>
         <z>0</z>
      </location>
   </pointmass>
</mass_balance>

<ground_reactions>
   <contact type="BOGEY" name="NOSE_LG">
   <location unit="IN">
      <x> 29.566964</x>
      <y> 0 </y>
      <z> -137.9617 </z>
   </location>
   <static_friction> 0.5 </static_friction>
   <dynamic_friction> 0.8 </dynamic_friction>
   <rolling_friction> 0.02 </rolling_friction>
   <spring_coeff unit="LBS/FT"> 75000 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 16978.5 </damping_coeff>
   <max_steer unit="DEG"> 75 </max_steer>
   <brake_group> NONE </brake_group>
   <retractable>1</retractable>
   </contact>
   <contact type="BOGEY" name="LEFT_MLG">
   <location unit="IN">
      <x> 699.9243 </x>
      <y> -149.4094 </y>
      <z> -152.6824 </z>
   </location>
   <static_friction> 0.5 </static_friction>
   <dynamic_friction> 0.8 </dynamic_friction>
   <rolling_friction> 0.02 </rolling_friction>
   <spring_coeff unit="LBS/FT"> 180000 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 33957 </damping_coeff>
   <max_steer unit="DEG"> 0.0 </max_steer>
   <brake_group> LEFT </brake_group>
   <retractable>1</retractable>
   </contact>
   <contact type="BOGEY" name="RIGHT_MLG">
   <location unit="IN">
      <x> 697.3425 </x>
      <y> 149.4094 </y>
      <z> -152.6824</z>
   </location>
   <static_friction> 0.5 </static_friction>
   <dynamic_friction> 0.8 </dynamic_friction>
   <rolling_friction> 0.02 </rolling_friction>
   <spring_coeff unit="LBS/FT"> 180000 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 33957 </damping_coeff>
   <max_steer unit="DEG"> 0.0 </max_steer>
   <brake_group> RIGHT </brake_group>
   <retractable>1</retractable>
   </contact>

   <contact type="STRUCTURE" name="NOSE_1">
   <location unit="IN">
      <x> 205.905536 </x>
      <y> 0 </y>
      <z> -38.1374 </z>
   </location>
   <static_friction> 1.0 </static_friction>
   <dynamic_friction> 1.4 </dynamic_friction>
   <rolling_friction> 1.0 </rolling_friction>
   <spring_coeff unit="LBS/FT"> 1.5e+06 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
   <max_steer unit="DEG"> 0.0 </max_steer>
   <brake_group> NONE </brake_group>
   <retractable>0</retractable>
   </contact>
   <contact type="STRUCTURE" name="NOSE_2">
   <location unit="IN">
      <x> 296.220436 </x>
      <y> 0 </y>
      <z> -55.0271 </z>
   </location>
   <static_friction> 1.0 </static_friction>
   <dynamic_friction> 1.4 </dynamic_friction>
   <rolling_friction> 1.0 </rolling_friction>
   <spring_coeff unit="LBS/FT"> 1.5e+06 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
   <max_steer unit="DEG"> 0.0 </max_steer>
   <brake_group> NONE </brake_group>
   <retractable>0</retractable>
   </contact>
   <contact type="STRUCTURE" name="CENTER_1">
   <location unit="IN">
      <x> 274.0157 </x>
      <y> 0 </y>
      <z> -60.0665 </z>
   </location>
   <static_friction> 1.0 </static_friction>
   <dynamic_friction> 1.4 </dynamic_friction>
   <rolling_friction> 1.0 </rolling_friction>
   <spring_coeff unit="LBS/FT"> 1.5e+06 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
   <max_steer unit="DEG"> 0.0 </max_steer>
   <brake_group> NONE </brake_group>
   <retractable>0</retractable>
   </contact>
   <contact type="STRUCTURE" name="CENTER_2">
   <location unit="IN">
      <x> 930 </x>
      <y> 0 </y>
      <z> -60.0665 </z>
   </location>
   <static_friction> 1.0 </static_friction>
   <dynamic_friction> 1.4 </dynamic_friction>
   <rolling_friction> 1.0 </rolling_friction>
   <spring_coeff unit="LBS/FT"> 1.5e+06 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
   <max_steer unit="DEG"> 0.0 </max_steer>
   <brake_group> NONE </brake_group>
   <retractable>0</retractable>
   </contact>
   <contact type="STRUCTURE" name="TAIL_1">
   <location unit="IN">
      <x> 992.87399 </x>
      <y> 0 </y>
      <z> -44.7722 </z>
   </location>
   <static_friction> 1.0 </static_friction>
   <dynamic_friction> 1.4 </dynamic_friction>
   <rolling_friction> 1.0 </rolling_friction>
   <spring_coeff unit="LBS/FT"> 1.5e+06 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
   <max_steer unit="DEG"> 0.0 </max_steer>
   <brake_group> NONE </brake_group>
   <retractable>0</retractable>
   </contact>
   <contact type="STRUCTURE" name="TAIL_2">
   <location unit="IN">
      <x> 1119.88189 </x>
      <y> 0 </y>
      <z> -18.8067 </z>
   </location>
   <static_friction> 1.0 </static_friction>
   <dynamic_friction> 1.4 </dynamic_friction>
   <rolling_friction> 1.0 </rolling_friction>
   <spring_coeff unit="LBS/FT"> 1.5e+06 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
   <max_steer unit="DEG"> 0.0 </max_steer>
   <brake_group> NONE </brake_group>
   <retractable>0</retractable>
   </contact>
   <contact type="STRUCTURE" name="TAIL_3">
   <location unit="IN">
      <x> 1236.49609 </x>
      <y> 0 </y>
      <z> -10.2599 </z>
   </location>
   <static_friction> 1.0 </static_friction>
   <dynamic_friction> 1.4 </dynamic_friction>
   <rolling_friction> 1.0 </rolling_friction>
   <spring_coeff unit="LBS/FT"> 1.5e+06 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
   <max_steer unit="DEG"> 0.0 </max_steer>
   <brake_group> NONE </brake_group>
   <retractable>0</retractable>
   </contact>
   <contact type="STRUCTURE" name="TAIL_4">
   <location unit="IN">
      <x> 232.59841 </x>
      <y> 0 </y>
      <z> 47.4138 </z>
   </location>
   <static_friction> 1.0 </static_friction>
   <dynamic_friction> 1.4 </dynamic_friction>
   <rolling_friction> 1.0 </rolling_friction>
   <spring_coeff unit="LBS/FT"> 1.5e+06 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
   <max_steer unit="DEG"> 0.0 </max_steer>
   <brake_group> NONE </brake_group>
   <retractable>0</retractable>
   </contact>
   <contact type="STRUCTURE" name="WING_TIP_1">
   <location unit="IN">
      <x> 838.8898 </x>
      <y> -667.5197 </y>
      <z> 35.7926 </z>
   </location>
   <static_friction> 1.0 </static_friction>
   <dynamic_friction> 1.4 </dynamic_friction>
   <rolling_friction> 1.0 </rolling_friction>
   <spring_coeff unit="LBS/FT"> 1.5e+06 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
   <max_steer unit="DEG"> 0.0 </max_steer>
   <brake_group> NONE </brake_group>
   <retractable>0</retractable>
   </contact>
   <contact type="STRUCTURE" name="WING_TIP_2">
   <location unit="IN">
      <x> 838.8898 </x>
      <y> 667.5197 </y>
      <z> 35.7926 </z>
   </location>
   <static_friction> 1.0 </static_friction>
   <dynamic_friction> 1.4 </dynamic_friction>
   <rolling_friction> 1.0 </rolling_friction>
   <spring_coeff unit="LBS/FT"> 1.5e+06 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 50000 </damping_coeff>
   <max_steer unit="DEG"> 0.0 </max_steer>
   <brake_group> NONE </brake_group>
   <retractable>0</retractable>
   </contact>
</ground_reactions>

<propulsion>
   <engine file="cfm56_5b3">
   <location unit="IN">
      <x> 589.735 </x>
      <y> -226.575 </y>
      <z> -45.567 </z>
   </location>
   <orient unit="DEG">
      <roll> 0.0 </roll>
      <pitch> 2.2 </pitch>
      <yaw> 1 </yaw>
   </orient>
   <feed>0</feed>
   <feed>1</feed>
   <feed>3</feed>
   <feed>4</feed>
   <feed>5</feed>
   <thruster file="direct">
      <location unit="IN">
      <x> 589.735 </x>
      <y> -226.575 </y>
      <z> -45.567 </z>
      </location>
      <orient unit="DEG">
      <roll> 0.0 </roll>
      <pitch> 2.2 </pitch>
      <yaw> 1 </yaw>
      </orient>
   </thruster>
   </engine>
   <engine file="cfm56_5b3">
   <location unit="IN">
      <x> 589.735 </x>
      <y> 226.575 </y>
      <z> -45.567 </z>
   </location>
   <orient unit="DEG">
      <roll> 0.0 </roll>
      <pitch> 2.2 </pitch>
      <yaw> -1 </yaw>
   </orient>
   <feed>0</feed>
   <feed>1</feed>
   <feed>3</feed>
   <feed>4</feed>
   <feed>5</feed>
   <thruster file="direct">
      <location unit="IN">
      <x> 589.735 </x>
      <y> 226.575 </y>
      <z> -45.567 </z>
      </location>
      <orient unit="DEG">
      <roll> 0.0 </roll>
      <pitch> 2.2 </pitch>
      <yaw> -1 </yaw>
      </orient>
   </thruster>
   </engine>
   <tank type="FUEL">    <!-- Left Tank (Inner) -->
      <location unit="IN">
         <x> 630.6588 </x>
         <y> -236.2992 </y>
         <z> -33.9470 </z>
      </location>
      <capacity unit="LBS"> 12186.9 </capacity>
      <contents unit="LBS"> 2437.38 </contents>
   </tank>
   <tank type="FUEL">    <!-- Left Tank (Outer) -->
      <location unit="IN">
         <x> 737.4190 </x>
         <y> -457.4259 </y>
         <z> -8.0898 </z>
      </location>
      <capacity unit="LBS"> 1548.8 </capacity>
      <contents unit="LBS"> 154.88 </contents>
   </tank>
   <tank type="FUEL">    <!-- Left Tank (Surge) -->
      <location unit="IN">
         <x> 788.4322 </x>
         <y> -574.4148 </y>
         <z> 3.1080 </z>
      </location>
      <capacity unit="LBS"> 328.13 </capacity>
      <contents unit="LBS"> 0 </contents>
   </tank>
   <tank type="FUEL">    <!-- Center Tank -->
      <location unit="IN">
         <x> 580.9955 </x>
         <y> 0 </y>
         <z> -47.0 </z>
      </location>
      <capacity unit="LBS"> 14520 </capacity>
      <contents unit="LBS"> 0 </contents>
   </tank>
   <tank type="FUEL">    <!-- Right Tank (Inner) -->
      <location unit="IN">
         <x> 630.6588 </x>
         <y> 236.2992 </y>
         <z> -33.9470 </z>
      </location>
      <capacity unit="LBS"> 12186.9 </capacity>
      <contents unit="LBS"> 2437.38 </contents>
   </tank>
   <tank type="FUEL">    <!-- Right Tank (Outer) -->
      <location unit="IN">
         <x> 737.4190 </x>
         <y> 457.4259 </y>
         <z> -8.0898 </z>
      </location>
      <capacity unit="LBS"> 1548.8 </capacity>
      <contents unit="LBS"> 154.88 </contents>
   </tank>
   <tank type="FUEL">    <!-- Right Tank (Surge) -->
      <location unit="IN">
         <x> 788.4322 </x>
         <y> 574.4148 </y>
         <z> 3.1080 </z>
      </location>
      <capacity unit="LBS"> 328.13 </capacity>
      <contents unit="LBS"> 0 </contents>
   </tank>
</propulsion>

<system file="pushback" />

<flight_control name="FCS: A320">
   <channel name="Pitch">
   <summer name="Pitch Trim Sum">
      <input>fcs/elevator-cmd-norm</input>
      <input>fcs/pitch-trim-cmd-norm</input>
      <clipto>
      <min>-1</min>
      <max>1</max>
      </clipto>
   </summer>

   <aerosurface_scale name="Elevator Control">
      <input>fcs/pitch-trim-sum</input>
      <gain>0.030</gain>
      <range>
      <min>-16</min>
      <max>20</max>
      </range>
      <output>fcs/elevator-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="Elevator position normalized">
      <input>fcs/elevator-pos-deg</input>
      <domain>
      <min>-16</min>
      <max>20</max>
      </domain>
      <range>
      <min>-1</min>
      <max>1</max>
      </range>
      <output>fcs/elevator-pos-norm</output>
   </aerosurface_scale>
   </channel>
   <channel name="Roll">
   <summer name="Roll Trim Sum">
      <input>fcs/aileron-cmd-norm</input>
      <input>fcs/roll-trim-cmd-norm</input>
      <clipto>
      <min>-1</min>
      <max>1</max>
      </clipto>
   </summer>

   <aerosurface_scale name="Left Aileron Control">
      <input>fcs/roll-trim-sum</input>
      <gain>0.02</gain>
      <range>
      <min>-25</min>
      <max>25</max>
      </range>
      <output>fcs/left-aileron-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="Right Aileron Control">
      <input>-fcs/roll-trim-sum</input>
      <gain>0.02</gain>
      <range>
      <min>-25</min>
      <max>25</max>
      </range>
      <output>fcs/right-aileron-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="Left Aileron position normalized">
      <input>fcs/left-aileron-pos-deg</input>
      <domain>
      <min>-25</min>
      <max>25</max>
      </domain>
      <range>
      <min>-0.75</min>
      <max>1</max>
      </range>
      <output>fcs/left-aileron-pos-norm</output>
   </aerosurface_scale>

   <aerosurface_scale name="Right Aileron position normalized">
      <input>fcs/right-aileron-pos-deg</input>
      <domain>
      <min>-25</min>
      <max>25</max>
      </domain>
      <range>
      <min>-0.75</min>
      <max>1</max>
      </range>
      <output>fcs/right-aileron-pos-norm</output>
   </aerosurface_scale>
   </channel>
   <channel name="Yaw">
   <pure_gain name="Yaw Damper Rate">
      <input>velocities/r-rad_sec</input>
      <gain>2</gain>
   </pure_gain>

   <pure_gain name="Yaw Damper Beta">
      <input>aero/beta-rad</input>
      <gain>-5</gain>
   </pure_gain>

   <summer name="Yaw Trim Sum">
      <input>fcs/rudder-cmd-norm</input>
      <input>fcs/yaw-trim-cmd-norm</input>
      <clipto>
      <min>-1</min>
      <max>1</max>
      </clipto>
   </summer>

   <summer name="Rudder Sum">
      <input>fcs/yaw-trim-sum</input>
      <input>fcs/yaw-damper-rate</input>
      <input>fcs/yaw-damper-beta</input>
      <clipto>
      <min>-1</min>
      <max>1</max>
      </clipto>
   </summer>

   <aerosurface_scale name="Rudder Control">
      <input>fcs/rudder-sum</input>
      <gain>0.01745</gain>
      <range>
      <min>-25</min>
      <max>25</max>
      </range>
      <output>fcs/rudder-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="Rudder position normalized">
      <input>fcs/rudder-pos-deg</input>
      <domain>
      <min>-25</min>
      <max>25</max>
      </domain>
      <range>
      <min>-1</min>
      <max>1</max>
      </range>
      <output>fcs/rudder-pos-norm</output>
   </aerosurface_scale>
   </channel>
   <channel name="Flaps">
   <kinematic name="Flaps Control">
      <input>fcs/flap-cmd-norm</input>
      <traverse>
      <setting>
         <position>0</position>
         <time>0</time>
      </setting>
      <setting>
         <position>40</position>
         <time>40</time>
      </setting>
      </traverse>
      <output>fcs/flap-pos-deg</output>
   </kinematic>

   <aerosurface_scale name="Flap position normalized">
      <input>fcs/flap-pos-deg</input>
      <domain>
      <min>0</min>
      <max>40</max>
      </domain>
      <range>
      <min>0</min>
      <max>1</max>
      </range>
      <output>fcs/flap-pos-norm</output>
   </aerosurface_scale>
   </channel>
   <channel name="Landing Gear">
   <kinematic name="Gear Control">
      <input>gear/gear-cmd-norm</input>
      <traverse>
      <setting>
         <position>0</position>
         <time>0</time>
      </setting>
      <setting>
         <position>1</position>
         <time>10</time>
      </setting>
      </traverse>
      <output>gear/gear-pos-norm</output>
   </kinematic>
   </channel>
   <channel name="Speedbrake">
   <kinematic name="Speedbrake">
      <input>fcs/speedbrake-cmd-norm</input>
      <traverse>
      <setting>
         <position>0</position>
         <time>0</time>
      </setting>
      <setting>
         <position>1</position>
         <time>2</time>
      </setting>
      </traverse>
      <output>fcs/speedbrake-pos-norm</output>
   </kinematic>
   </channel>
</flight_control>
<aerodynamics>

   <axis name="DRAG">
   <function name="aero/coefficient/CDo">
      <description>Drag_at_zero_lift</description>
      <product>
      <property>aero/qbar-psf</property>
      <property>metrics/Sw-sqft</property>
      <value>0.010</value>
      </product>
   </function>
   <function name="aero/coefficient/CDalpha">
      <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
         </tableData>
      </table>
      </product>
   </function>
   <function name="aero/coefficient/CDde">
      <description>Drag_due_to_elevator_Deflection</description>
      <product>
      <property>aero/qbar-psf</property>
      <property>metrics/Sw-sqft</property>
      <property>fcs/mag-elevator-pos-rad</property>
      <value>0.0100</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>0.1000</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>0.0100</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>
   </axis>

   <axis name="SIDE">
   <function name="aero/coefficient/CYb">
      <description>Side_force_due_to_beta</description>
      <product>
      <property>aero/qbar-psf</property>
      <property>metrics/Sw-sqft</property>
      <table>
         <independentVar>aero/beta-rad</independentVar>
         <tableData>
         -0.3500   0.5000
         0.0000   0.0000
         0.3500   -0.5000
         </tableData>
      </table>
      </product>
   </function>
   </axis>

   <axis name="LIFT">
   <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/coefficient/CLDe">
      <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>0.2930</value>
      </product>
   </function>
   </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/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/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/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>
      </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>
   </axis>

   <axis name="PITCH">
   <function name="aero/coefficient/Cmo">
      <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   0.0400
         40.0000   -0.1000
         </tableData>
      </table>
      </product>
   </function>
   <function name="aero/coefficient/Cmalpha">
      <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>
      </product>
   </function>
   <function name="aero/coefficient/CmDe">
      <description>Pitch_moment_due_to_elevator_Deflection</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>
      </product>
   </function>
   <function name="aero/coefficient/Cmq">
      <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>
      </product>
   </function>
   <function name="aero/coefficient/Cmadot">
      <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>
      </product>
   </function>
   </axis>

   <axis name="YAW">
   <function name="aero/coefficient/Cnr">
      <description>Yaw_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>-0.0400</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/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>
      </product>
   </function>
   </axis>
</aerodynamics>

   <external_reactions>
      <force name="pushback" frame="BODY">
         <location unit="IN">
            <x>294</x>
            <y>0</y>
            <z>-149</z>
         </location>
         <direction>
            <x>1</x>
            <y>0</y>
            <z>0</z>
         </direction>
      </force>
   </external_reactions>
</fdm_config>
The worst floods in the Balkans ever,follow these links to learn more how to help. Thank you.
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ja sam niko
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Posts: 210
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Callsign: ex FGRS,now UAV001
Version: 2.8
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Re: Airbus A320 [Family]

Postby Bjoern » Mon Mar 24, 2014 10:55 pm

Your problem sounds like a borked center of gravity.

Try setting it (below <location name="CG" unit="IN">) to 0,0,0 (x,y,z) for a start and recheck.



General observation: YASIM FD files are so friggin' much cleaner and leaner than .air files for MSFS. Wow!
Do a barrel roll!
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Re: Airbus A320 [Family]

Postby ja sam niko » Tue Mar 25, 2014 3:12 pm

To "0" ? :?

OK ,but that will make a chaos in the FDM. I guess it could be like the A340-600 which jumps around when almost empty..but I will try.

Thanks.
The worst floods in the Balkans ever,follow these links to learn more how to help. Thank you.
http://www.google.org/crisisresponse/2014-balkans-floods

http://www.mvp.gov.ba/HTML/eng-help.pdf
ja sam niko
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Posts: 210
Joined: Sun Feb 23, 2014 7:52 pm
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Callsign: ex FGRS,now UAV001
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