tu154b.xml

<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http:https://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="tu154b" version="2.0" release="PRODUCTION"
    xmlns:xsi="http:https://www.w3.org/2001/XMLSchema-instance"
    xsi:noNamespaceSchemaLocation="http:https://jsbsim.sourceforge.net/JSBSim.xsd">

<!-- For FG-devel -->

    <fileheader>
        <author> Yurik V. Nikiforoff </author>
        <filecreationdate> 2009-05-23 </filecreationdate>
        <description>TU-154b airliner</description>
        <version> 3.0 </version>
    </fileheader>

    <metrics>
        <wingarea unit="M2"> 200 </wingarea>
        <wingspan unit="M"> 37.55 </wingspan>
        <chord unit="M"> 5.285 </chord>
        <wing_incidence unit="DEG"> 3.0 </wing_incidence>
        <htailarea unit="M2"> 40.55 </htailarea>
        <htailarm unit="M"> 30 </htailarm>
        <vtailarea unit="M2"> 31.7 </vtailarea>
        <vtailarm unit="M"> 21.64 </vtailarm>
        <location name="AERORP" unit="M">
            <x> 27.211 </x>
            <y> 0 </y>
            <z> 0 </z>
        </location>
        <location name="EYEPOINT" unit="M">
            <x> 3.35 </x>
            <y> -0.76 </y>
            <z> 1.9 </z>
        </location>
        <location name="VRP" unit="M">
            <x> 26.0 </x>
            <y> 0 </y>
            <z> 0.0 </z>
        </location>
    </metrics>

    <mass_balance>
        <ixx unit="KG*M2">1.3e+06</ixx>
        <iyy unit="KG*M2">4.36916e+06</iyy>
        <izz unit="KG*M2">5.92493e+06</izz>
        <ixz unit="KG*M2">0</ixz>
        <iyz unit="KG*M2">0</iyz>
        <ixy unit="KG*M2">0</ixy>
        <emptywt unit="KG">53000</emptywt>
        <location name="CG" unit="M">
            <x>26.68</x>
            <y>0</y>
            <z>1.8</z>
        </location>

        <pointmass name="Crew">
            <weight unit="KG">320</weight>
            <location unit="M">
                <x>3.847</x>
                <y>0</y>
                <z>0</z>
            </location>
        </pointmass>

	<pointmass name="Pax1">
            <weight unit="KG">4160</weight>
            <location unit="M">
                <x>12.0</x>
                <y>0</y>
                <z>0</z>
            </location>
        </pointmass>       
	
        <pointmass name="Pax2">
            <weight unit="KG">4000</weight>
            <location unit="M">
                <x>20.0</x>
<!--<x>5.84</x>-->
<!--<x>0.5</x>-->
                <y>0</y>
                <z>0</z>
            </location>
        </pointmass>

        <pointmass name="Pax3">
            <weight unit="KG">3840</weight>
            <location unit="M">
                <x>30.0</x>
                <y>0</y>
                <z>0</z>
            </location>
        </pointmass>       

	<!--Luggage-->

        <pointmass name="Luggage_1">
            <weight unit="KG">0</weight>
            <location unit="M">
                <x>13.022</x>
                <y>0</y>
                <z>0</z>
            </location>
        </pointmass>       
        <pointmass name="Luggage_2">
            <weight unit="KG">0</weight>
            <location unit="M">
                <x>14.022</x>
                <y>0</y>
                <z>0</z>
            </location>
        </pointmass>       
        <pointmass name="Luggage_3">
            <weight unit="KG">300</weight>
            <location unit="M">
                <x>16.022</x>
                <y>0</y>
                <z>0</z>
            </location>
        </pointmass>       
        <pointmass name="Luggage_4">
            <weight unit="KG">300</weight>
            <location unit="M">
                <x>19.022</x>
                <y>0</y>
                <z>0</z>
            </location>
        </pointmass>       
        <pointmass name="Luggage_5">
            <weight unit="KG">1900</weight>
            <location unit="M">
                <x>27.272</x>
                <y>0</y>
                <z>0</z>
            </location>
        </pointmass>       
        <pointmass name="Luggage_6">
            <weight unit="KG">0</weight>
            <location unit="M">
                <x>29.772</x>
                <y>0</y>
                <z>0</z>
            </location>
        </pointmass>       
        <pointmass name="Luggage_7">
            <weight unit="KG">0</weight>
            <location unit="M">
                <x>31.722</x>
                <y>0</y>
                <z>0</z>
            </location>
        </pointmass>
        <pointmass name="Gear shift">
            <weight unit="KG">1000</weight>
            <location unit="M">
                <x>26.68</x>
                <y>0</y>
                <z>1.8</z>
            </location>
        </pointmass>      
    </mass_balance>

    <ground_reactions>
        <contact type="BOGEY" name="NOSE">
            <location unit="M">
                <x> 6.0 </x>
                <y> 0.0 </y>
                <z> -2.7 </z>
            </location>
            <static_friction> 0.6 </static_friction>
            <dynamic_friction> 0.8 </dynamic_friction>
            <rolling_friction> 0.02 </rolling_friction>
            <spring_coeff unit="N/M"> 800000 </spring_coeff><!--800000-->
            <damping_coeff unit="N/M/SEC"> 150000 </damping_coeff><!--150000-->
            <max_steer unit="DEG"> 63.0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable> 1 </retractable>
        </contact>
        <contact type="BOGEY" name="LEFT_MAIN">
            <location unit="M">
                <x> 26.82 </x>
                <y> -6.195 </y>
                <z> -2.5 </z>
            </location>
            <static_friction> 0.6 </static_friction>
            <dynamic_friction> 0.5 </dynamic_friction>
            <rolling_friction> 0.02 </rolling_friction><!--0.02-->
            <spring_coeff unit="N/M"> 1.7e+06 </spring_coeff><!--1.7e+06 -->
            <damping_coeff unit="N/M/SEC"> 100000 </damping_coeff>
            <max_steer unit="DEG"> 0 </max_steer>
            <brake_group> LEFT </brake_group>
            <retractable> 1 </retractable>
        </contact>
        <contact type="BOGEY" name="RIGHT_MAIN">
            <location unit="M">
                <x> 26.82 </x>
                <y> 6.195 </y>
                <z> -2.5 </z>
            </location>
            <static_friction> 0.6 </static_friction>
            <dynamic_friction> 0.5 </dynamic_friction>
            <rolling_friction> 0.02 </rolling_friction>
            <spring_coeff unit="N/M"> 1.7e+06 </spring_coeff>
            <!--<spring_coeff unit="N/M"> 3.1536e+06 </spring_coeff>-->
            <!--<damping_coeff unit="N/M/SEC"> 630720 </damping_coeff>-->
            <damping_coeff unit="N/M/SEC"> 100000 </damping_coeff><!--100000-->
            <max_steer unit="DEG"> 0 </max_steer>
            <brake_group> RIGHT </brake_group>
            <retractable> 1 </retractable>
        </contact>

        <contact type="BOGEY" name="LEFT TILT FRONT">
            <location unit="M">
              <x>25.51</x>
              <y>-6.195</y>
              <z>-2.7</z>
            </location>
            <static_friction>0.0000</static_friction>
            <dynamic_friction>0.0000</dynamic_friction>
            <rolling_friction>0.0000</rolling_friction>
            <spring_coeff unit="N/M">0.0</spring_coeff>
            <damping_coeff unit="N/M/SEC">0.0</damping_coeff>
            <max_steer unit="DEG">0.0</max_steer>
            <brake_group>NONE</brake_group>
            <retractable>1</retractable>
        </contact>
        <contact type="BOGEY" name="LEFT TILT REAR">
            <location unit="M">
              <x>28.13</x>
              <y>-6.195</y>
              <z>-2.3</z>
            </location>
            <static_friction>0.0000</static_friction>
            <dynamic_friction>0.0000</dynamic_friction>
            <rolling_friction>0.0000</rolling_friction>
            <spring_coeff unit="N/M">0.0</spring_coeff>
            <damping_coeff unit="N/M/SEC">0.0</damping_coeff>
            <max_steer unit="DEG">0.0</max_steer>
            <brake_group>NONE</brake_group>
            <retractable>1</retractable>
        </contact>
        <contact type="BOGEY" name="RIGHT TILT FRONT">
            <location unit="M">
              <x>25.51</x>
              <y>6.195</y>
              <z>-2.7</z>
            </location>
            <static_friction>0.0000</static_friction>
            <dynamic_friction>0.0000</dynamic_friction>
            <rolling_friction>0.0000</rolling_friction>
            <spring_coeff unit="N/M">0.0</spring_coeff>
            <damping_coeff unit="N/M/SEC">0.0</damping_coeff>
            <max_steer unit="DEG">0.0</max_steer>
            <brake_group>NONE</brake_group>
            <retractable>1</retractable>
        </contact>
        <contact type="BOGEY" name="RIGHT TILT REAR">
            <location unit="M">
              <x>28.13</x>
              <y>6.195</y>
              <z>-2.3</z>
            </location>
            <static_friction>0.0000</static_friction>
            <dynamic_friction>0.0000</dynamic_friction>
            <rolling_friction>0.0000</rolling_friction>
            <spring_coeff unit="N/M">0.0</spring_coeff>
            <damping_coeff unit="N/M/SEC">0.0</damping_coeff>
            <max_steer unit="DEG">0.0</max_steer>
            <brake_group>NONE</brake_group>
            <retractable>1</retractable>
        </contact>

        <contact type="STRUCTURE" name="FRONT">
            <location unit="M">
                <x> 3.5 </x>
                <y> 0.0 </y>
                <z> -0.2 </z>
            </location>
            <static_friction> 0.8 </static_friction>
            <dynamic_friction> 0.5 </dynamic_friction>
            <rolling_friction> 0 </rolling_friction>
            <spring_coeff unit="N/M"> 3e+06 </spring_coeff>
            <damping_coeff unit="N/M/SEC"> 630720 </damping_coeff>
            <max_steer unit="DEG"> 0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable> 0 </retractable>
        </contact>
        <contact type="STRUCTURE" name="LEFT_WING">
            <location unit="M">
                <x> 26.82 </x>
                <y> -18.7 </y>
                <z> -0.5 </z>
            </location>
            <static_friction> 0.8 </static_friction>
            <dynamic_friction> 0.5 </dynamic_friction>
            <rolling_friction> 0 </rolling_friction>
            <spring_coeff unit="N/M"> 3e+06 </spring_coeff>
            <damping_coeff unit="N/M/SEC"> 630720 </damping_coeff>
            <max_steer unit="DEG"> 0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable> 0 </retractable>
        </contact>
        <contact type="STRUCTURE" name="RIGHT_WING">
            <location unit="M">
                <x> 26.82 </x>
                <y> 18.7 </y>
                <z> -0.5 </z>
            </location>
            <static_friction> 0.8 </static_friction>
            <dynamic_friction> 0.5 </dynamic_friction>
            <rolling_friction> 0 </rolling_friction>
            <spring_coeff unit="N/M"> 3e+06 </spring_coeff>
            <damping_coeff unit="N/M/SEC"> 630720 </damping_coeff>
            <max_steer unit="DEG"> 0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable> 0 </retractable>
        </contact>
        <contact type="STRUCTURE" name="TAIL">
            <location unit="M">
                <x> 41 </x>
                <y> 0 </y>
                <z> 1 </z>
            </location>
            <static_friction> 0.8 </static_friction>
            <dynamic_friction> 0.5 </dynamic_friction>
            <rolling_friction> 0 </rolling_friction>
            <spring_coeff unit="N/M"> 3e+06 </spring_coeff>
            <damping_coeff unit="N/M/SEC"> 630720 </damping_coeff>
            <max_steer unit="DEG"> 0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable> 0 </retractable>
        </contact>
    </ground_reactions>
    
    
    <propulsion>

        <engine file="nk-8-2u">
            <location unit="M">
                <x> 34 </x>
                <y> -3.13 </y>
                <z> 1.78 </z>
            </location>
            <orient unit="DEG">
                <roll> 0 </roll>
                <pitch> 0 </pitch>
                <yaw> 0 </yaw>
            </orient>
            <feed>0</feed>
            <thruster file="direct">
                <location unit="M">
                    <x> 37.27 </x>
                    <y> -3.03 </y>
                    <z> 1.7 </z>
                </location>
                <orient unit="DEG">
                    <roll> 0 </roll>
                    <pitch> 2 </pitch>
                    <yaw> -6.5 </yaw>
                </orient>
            </thruster>
        </engine>
        <engine file="nk-8-2u">
            <location unit="M">
                <x> 38 </x>
                <y> 0 </y>
                <z> 2.3 </z>
            </location>
            <orient unit="DEG">
                <roll> 0 </roll>
                <pitch> 0 </pitch>
                <yaw> 0 </yaw>
            </orient>
            <feed>0</feed>
            <thruster file="direct">
                <location unit="M">
                    <x> 41.6 </x>
                    <y> 0 </y>
                    <z> 2.26 </z>
                </location>
                <orient unit="DEG">
                    <roll> 0 </roll>
                    <pitch> -2.5 </pitch>
                    <yaw> 0 </yaw>
                </orient>
            </thruster>
        </engine>
        <engine file="nk-8-2u">
            <location unit="M">
                <x> 34 </x>
                <y> 3.13 </y>
                <z> 1.78 </z>
            </location>
            <orient unit="DEG">
                <roll> 0 </roll>
                <pitch> 0 </pitch>
                <yaw> 0 </yaw>
            </orient>
            <feed>0</feed>
            <thruster file="direct">
                <location unit="M">
                    <x> 37.27 </x>
                    <y> 3.03 </y>
                    <z> 1.7 </z>
                </location>
                <orient unit="DEG">
                    <roll> 0 </roll>
                    <pitch> 2 </pitch>
                    <yaw> 6.5 </yaw>
                </orient>
            </thruster>
        </engine>
        <engine file="tsa-6a">
          <location unit="M">
            <x> 32 </x>
            <y> 0 </y>
            <z> 2.3 </z>
          </location>
          <orient unit="DEG">
            <roll> 0 </roll>
            <pitch> 0 </pitch>
            <yaw> 0 </yaw>
          </orient>
          <feed>0</feed>
          <thruster file="direct">
            <location unit="M">
              <x> 32 </x>
              <y> 0 </y>
              <z> 2.26 </z>
            </location>
            <orient unit="DEG">
              <roll> 0 </roll>
              <pitch> 0 </pitch>
              <yaw> 90 </yaw>
            </orient>
          </thruster>
        </engine>
        <tank type="FUEL">
            <location unit="M">
                <x> 25 </x>
                <y> 0 </y>
                <z> 0 </z>
            </location>
            <capacity unit="KG">3350</capacity><!-- 3300 + 50 margin -->
            <contents unit="KG">3300</contents>
        </tank>
        <tank type="FUEL">
            <location unit="M">
                <x> 24 </x>
                <y> -4 </y>
                <z> 0 </z>
            </location>
            <capacity unit="KG">9550</capacity><!-- 9500 + 50 margin -->
            <contents unit="KG">1500</contents>
        </tank>
        <tank type="FUEL">
            <location unit="M">
                <x> 24 </x>
                <y> 4 </y>
                <z> 0 </z>
            </location>
            <capacity unit="KG">9550</capacity><!-- 9500 + 50 margin -->
            <contents unit="KG">1500</contents>
        </tank>
        <tank type="FUEL">
            <location unit="M">
                <x> 27.5 </x>
                <y> -10 </y>
                <z> 0 </z>
            </location>
            <capacity unit="KG">5425</capacity>
            <contents unit="KG">3225</contents>
        </tank>
        <tank type="FUEL">
            <location unit="M">
                <x> 27.5 </x>
                <y> 10 </y>
                <z> 0 </z>
            </location>
            <capacity unit="KG">5425</capacity>
            <contents unit="KG">3225</contents>
        </tank>
        <tank type="FUEL">
            <location unit="M">
                <x> 21 </x>
                <y> 0 </y>
                <z> 0 </z>
            </location>
            <capacity unit="KG">6600</capacity>
            <contents unit="KG">1000</contents>
        </tank>
    </propulsion>

    <flight_control name="tu154b">
<!--      
	<property>fcs/stab-auto-cmd</property>
	<property>fcs/stabilizer-cmd-norm</property>
	-->
	<!--<property>fcs/met</property>-->
        <channel name="Pitch">
<!--Modified by yurik nov 2013-->
<!--		
	    <aerosurface_scale name="fcs/met-trimmer">
		<input>fcs/pitch-trim-cmd-norm</input>
		<domain>
			<min>-1</min> 
			<max>1</max>
		</domain>
		<range>
			<min>-0.5</min>
			<max>0.6</max>
		</range>
	    	<output>fcs/met</output>
	    </aerosurface_scale>
-->
            <summer name="Pitch Trim Sum">
              <input>fcs/elevator-cmd-norm</input>
	      <!--<input>fcs/met</input>--> <!--By Yurik-->
	      <input>ap/pitch/met</input>
              <clipto>
                <min>-1</min>
                <max>1</max>
              </clipto>
            </summer>
            
            <switch name="fcs/pitch-ra-56-hydropower">
              <default value="0.0"/>
              <test value="fcs/absu-pitch">
                hs/ra-56-pitch-serviceable > 0
              </test>
            </switch>

            <summer name="Pitch Absu Sum">
              <input>fcs/pitch-trim-sum</input>
              <input>fcs/pitch-ra-56-hydropower</input>
              <clipto>
                <min>-1</min>
                <max>1</max>
              </clipto>
            </summer>
            
            <switch name="fcs/pitch-hydropower">
              <default value="fcs/elevator-pos-static"/>
              <test value="fcs/pitch-absu-sum">
                hs/busters-serviceable > 0
              </test>
            </switch>

            <aerosurface_scale name="Elevator Control">
              <input>fcs/pitch-hydropower</input>
              <range>
                <min>-0.506</min>
                <max>0.28</max>
              </range>
              <output>fcs/elevator-pos-raw</output>
            </aerosurface_scale>

            <kinematic name="Elevator filter">
             <input>fcs/elevator-pos-raw</input>
              <traverse>
                <setting>
                  <position>-1</position>
                  <time>0</time>
                </setting>
                <setting>
                  <position>1</position>
                  <time>2.0</time>
                </setting>
              </traverse>
              <output>fcs/elevator-pos-rad</output>
            </kinematic>
            
            <aerosurface_scale name="Elevator Normalizer">
              <input>fcs/elevator-pos-rad</input>
              <domain>
                <min>-1</min> 
                <max>1</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>
            
            <switch name="fcs/roll-ra-56-hydropower">
              <default value="0.0"/>
              <test value="fcs/absu-roll">
                hs/ra-56-roll-serviceable > 0
              </test>
            </switch>

            <summer name="Roll Absu Sum">
              <input>fcs/roll-trim-sum</input>
              <input>fcs/roll-ra-56-hydropower</input>
              <clipto>
                <min>-1</min>
                <max>1</max>
              </clipto>
            </summer>
            
            <switch name="fcs/roll-hydropower">
              <default value="fcs/aileron-pos-static"/>
              <test value="fcs/roll-absu-sum">
                hs/busters-serviceable > 0
              </test>
            </switch>

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

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

            <kinematic name="Aileron filter">
             <input>fcs/left-aileron-pos-raw</input>
              <traverse>
                <setting>
                  <position>-1</position>
                  <time>0</time>
                </setting>
                <setting>
                  <position>1</position>
                  <time>2.0</time>
                </setting>
              </traverse>
              <output>fcs/left-aileron-pos-rad</output>
            </kinematic>
            
            <aerosurface_scale name="Aileron Normalizer">
              <input>fcs/left-aileron-pos-rad</input>
              <domain>
                <min>-1</min> 
                <max>1</max>
              </domain>
              <range>
                <min>-1</min>
                <max>1</max>
              </range>
              <output>fcs/left-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>
            </summer>
            
            <switch name="fcs/yaw-ra-56-hydropower">
              <default value="0.0"/>
              <test value="fcs/absu-yaw">
                hs/ra-56-yaw-serviceable > 0
              </test>
            </switch>

            <summer name="Rudder Sum">
              <input>fcs/rudder-command-sum</input>
              <input>fcs/yaw-ra-56-hydropower</input>
            </summer>
            
            <switch name="fcs/yaw-hydropower">
              <default value="fcs/rudder-pos-static"/>
              <test value="fcs/rudder-sum">
                hs/busters-serviceable > 0
              </test>
            </switch>

            <aerosurface_scale name="Rudder Control">
              <input>fcs/yaw-hydropower</input>
              <range>
                <min>-0.4363</min>
                <max>0.4363</max>
              </range>
              <output>fcs/rudder-pos-raw</output>
            </aerosurface_scale>

            <kinematic name="Rudder filter">
             <input>fcs/rudder-pos-raw</input>
              <traverse>
                <setting>
                  <position>-1</position>
                  <time>0</time>
                </setting>
                <setting>
                  <position>1</position>
                  <time>2.0</time>
                </setting>
              </traverse>
              <output>fcs/rudder-pos-rad</output>
            </kinematic>
            
            <aerosurface_scale name="Rudder Normalizer">
              <input>fcs/rudder-pos-rad</input>
              <domain>
                <min>-1</min> 
                <max>1</max>
              </domain>
              <range>
                <min>-1</min>
                <max>1</max>
              </range>
              <output>fcs/rudder-pos-norm</output>
            </aerosurface_scale>

        </channel>

        <channel name="Flaps">
          
          <switch name="fcs/flap-cmd-switched">
            <default value="fcs/flap-cmd-static"/>
            <test value="fcs/flap-cmd-norm">
              hs/flaps-serviceable > 0
            </test>
          </switch>

            <kinematic name="Flaps Control">
             <input>fcs/flap-cmd-switched</input>
              <traverse>
                <setting>
                  <position>0</position>
                  <time>0</time>
                </setting>
                <setting>
                  <position>15</position>
                  <time>7</time>
                </setting>
                <setting>
                  <position>28</position>
                  <time>8</time>
                </setting>
                <setting>
                  <position>45</position>
                  <time>12</time>
                </setting>
              </traverse>
              <output>fcs/flap-pos-deg</output>
            </kinematic>
            
            <aerosurface_scale name="Flap Position Normalizer">
              <input>fcs/flap-pos-deg</input>
              <domain>
                <min>0</min>  <!-- Flaps actual minimum position -->
                <max>45</max>  <!-- Flaps actual maximum position -->
              </domain>
              <range>
                <min>0</min>  <!-- Flaps normalized minimum position -->
                <max>1</max>  <!-- Flaps normalized maximum position -->
              </range>
              <output>fcs/flap-pos-norm</output>
            </aerosurface_scale>
        </channel>

        <channel name="Landing Gear">
          
          <switch name="gear/gear-cmd-switched">
            <default value="gear/gear-cmd-static"/>
            <test value="gear/gear-cmd-norm">
              hs/hs1-busters-ok > 0
            </test>
          </switch>

            <kinematic name="Gear Control">
              <input>gear/gear-cmd-norm</input>
              <!--<input>gear/gear-cmd-switched</input>-->
              <traverse>
                <setting>
                  <position>0</position>
                  <time>0</time>
                </setting>
                <setting>
                  <position>1</position>
                  <time>7</time>
                </setting>
              </traverse>
              <output>gear/gear-pos-norm</output>
            </kinematic>

        </channel>

        <channel name="Speedbrake">

          
          <pure_gain name="Speedbrake outer">
            <input>fcs/spoiler-cmd-norm</input>
            <gain>0.4</gain>
          </pure_gain>

          
          <switch name="Wow">
            <default value="0.0"/>
            <test value="1.0">
              forces/fbz-gear-lbs lt -1000
            </test>
          </switch>
          
          <switch name="revers on ground">
            <default value="0.0"/>
            <test value="fcs/wow">
              propulsion/engine[0]/reverser-angle-rad gt 0.1
            </test>
          </switch>

          <switch name="rejected takeoff">
            <default value="0.0"/>
            <test value="1.0">
              fcs/flap-pos-deg gt 10
              fcs/revers-on-ground gt 0
            </test>
          </switch>

          <switch name="normal landing">
            <default value="0.0"/>
            <test value="1.0">
              fcs/flap-pos-deg gt 30
              fcs/revers-on-ground gt 0.5
	      fcs/throttle-cmd-norm[0] lt fcs/revers-1-limit
              fcs/throttle-cmd-norm[1] lt fcs/revers-1-limit
              fcs/throttle-cmd-norm[2] lt fcs/revers-1-limit
	      fcs/throttle-cmd-norm[0] gt fcs/revers-2-limit
	      fcs/throttle-cmd-norm[1] gt fcs/revers-2-limit
	      fcs/throttle-cmd-norm[2] gt fcs/revers-2-limit
            </test>
          </switch>
          
          <summer name="Speedbrake cmd">
            <input>fcs/speedbrake-outer</input>
            <input>fcs/rejected-takeoff</input>
            <input>fcs/normal-landing</input>
            <clipto>
              <min>0.0</min>
              <max>1.0</max>
            </clipto>
          </summer>
          
          <switch name="fcs/speedbrake-cmd-switched">
            <default value="fcs/speedbrake-cmd-static"/>
            <test value="fcs/speedbrake-cmd">
              hs/hs1-busters-ok > 0
            </test>
          </switch>
          
          
            <kinematic name="Speedbrake Control">
              <input>fcs/speedbrake-cmd-switched</input>
              <traverse>
                <setting>
                  <position>0</position>
                  <time>0</time>
                </setting>
                <setting>
                  <position>1</position>
                  <time>1.0</time>
                </setting>
              </traverse>
              <output>fcs/speedbrake-pos-norm</output>
            </kinematic>

        </channel>

        <channel name="Stabilizer">

          <scheduled_gain name="Stabilizer Auto Pos">
            <input>fcs/stab-auto-cmd</input>
            <table>
              <independentVar> fcs/flap-pos-deg </independentVar>
              <tableData>
                0             0
                28            0.2727
                45            0.5454
              </tableData>
            </table>
            <clipto>
              <min>0.0</min>
              <max>1.0</max>
            </clipto>
          </scheduled_gain>
          
          <switch name="fcs/stab-manu-tgt">
            <default value="fcs/stabilizer-control-raw"/>
            <test value="1.0">
              fcs/stab-manu-selector eq 2.0
            </test>
            <test value="0.0">
              fcs/stab-manu-selector eq 0.0
            </test>
          </switch>

          <kinematic name="fcs/stab-manu-cmd">
	    <input>fcs/stab-manu-tgt</input>
<!--<input>fcs/stabilizer-cmd-norm</input>-->
              <traverse>
                <setting>
                  <position>0.0</position>
                  <time>0</time>
                </setting>
                <setting>
                  <position>1.0</position>
                  <time>15</time>
                </setting>
              </traverse>
          </kinematic>
          
          <switch name="Stabilizer Cmd">
            <default value="fcs/stabilizer-auto-pos"/>
            <test value="fcs/stab-manu-cmd">
              fcs/stab-manu-switch eq 1.0
            </test>
          </switch>
          
            <kinematic name="Stabilizer Control Raw">
	    <input>fcs/stabilizer-cmd</input>
<!--<input>fcs/stabilizer-cmd-norm</input>-->
              <traverse>
                <setting>
                  <position>0.0</position>
                  <time>0</time>
                </setting>
                <setting>
                  <position>1.0</position>
                  <time>15</time>
                </setting>
              </traverse>
            </kinematic>
          
            <pure_gain name="Stabilizer Control">
	            <input>fcs/stabilizer-control-raw</input>
              <gain>0.09602</gain>
            </pure_gain>
            
            <summer name="Stabilizer rad">
              <bias>0.02618</bias>
              <input>fcs/stabilizer-control</input>
              <output>fcs/stabilizer-pos-rad</output>
            </summer>
    
            <aerosurface_scale name="Stabilizer Normalizer">
              <input>fcs/stabilizer-pos-rad</input>
              <domain>
                <min>-1</min> 
                <max>1</max>
              </domain>
              <range>
                <min>-1</min>
                <max>1</max>
              </range>
              <output>fcs/right-aileron-pos-norm</output>
            </aerosurface_scale>

        </channel>
        
        <channel name="Brake">
<!--Left-->
<!--Check hydro power for brake-->
          <switch name="gear/left-brake-cmd-switched">
            <default value="0.0"/>
            <test logic="OR" value="gear/brake-left">
              hs/hs1-busters-ok > 0
              gear/brake-parking > 0
            </test>
            <output>fcs/left-brake-cmd-norm</output>
          </switch>
<!--Right-->
          
          <switch name="gear/right-brake-cmd-switched">
            <default value="0.0"/>
            <test logic="OR" value="gear/brake-right">
              hs/hs1-busters-ok > 0
              gear/brake-parking > 0
            </test>
            <output>fcs/right-brake-cmd-norm</output>
          </switch>
          
        </channel>

        <channel name="Steering">

          <fcs_function name="gear/steering-free-cmd-norm">
            <function>
              <sum>
                <property>gear/steering-cmd-norm</property>
                <product>
                  <property>gear/unit[0]/wheel-speed-fps</property>
                  <sum>
                    <property>gear/unit[0]/side_friction_coeff</property>
                    <property>gear/unit[0]/rolling_friction_coeff</property>
                  </sum>
                  <property>gear/unit[0]/compression-ft</property>
                  <value>0.01</value>
                </product>
              </sum>
            </function>
            <clipto>
              <min>-1</min>
              <max>1</max>
            </clipto>
          </fcs_function>

          <fcs_function name="gear/rudder-cmd-scaled">
            <function>
              <product>
                <property>fcs/rudder-cmd-norm</property>
                <value>0.015873</value>
                <property>gear/steering</property>
              </product>
            </function>
          </fcs_function>

          <switch name="gear/steering-cmd-norm">
            <test value="0">
              gear/unit[0]/WOW == 0
              gear/steering-cmd-norm lt 0.25
              gear/steering-cmd-norm gt -0.25
            </test>
            <test value="gear/steering-cmd-norm">
              gear/unit[0]/WOW == 0
            </test>
            <test value="-gear/rudder-cmd-scaled">
              gear/nose-wheel-steering == 1
              systems/electrical-ok == 1
              hs/hs2-busters-ok == 1
            </test>
            <default value="gear/steering-free-cmd-norm"/>
          </switch>

          <switch name="gear/steering-cmd-norm">
            <test value="hydraulics/tiller/autopush-cmd">
              external_reactions/tractor/connected == 1
            </test>
            <default value="gear/steering-cmd-norm"/>
          </switch>

          <kinematic name="gear/steer-pos-deg">
            <input>gear/steering-cmd-norm</input>
            <traverse>
              <setting>
                <position>-63</position>
                <time>0</time>
              </setting>
              <setting>
                <position>63</position>
                <time>3</time>
              </setting>
            </traverse>
          </kinematic>

          <!-- <output> in <kinematic> doesn't seem to work here. -->
          <pure_gain name="gear/steer-pos-deg-workaround">
            <input>gear/steer-pos-deg</input>
            <gain>1</gain>
            <output>fcs/steer-pos-deg</output>
          </pure_gain>

        </channel>

        <channel name="Landing Gear Weight Shift">

          <fcs_function name="aero/function/weight-shift-gears">
                <function>
                  <sum>
                    <product>
                        <property>gear/gear-pos-norm</property>
                        <value>-192.91</value>
                    </product>
                    <value>1243.30</value>
                  </sum>
                </function>
                <output> inertia/pointmass-location-X-inches[11] </output>
            </fcs_function>

        </channel>

    </flight_control>
    
    <system file="fdm_globals"/>
    <system file="fuel"/>
    <system file="engines"/>
    <system file="hydrosystems"/>
    <system file="instrumentation"/>
    <system file="nvu"/>
    <autopilot file="Systems/absu154"/>

    
    <aerodynamics>
 <!--Kg/(Newton per hour)-->
      
<function name="propulsion/fuel-cft"> 
	<product>
          <quotient>
	    <product>
	      <property>propulsion/engine[0]/fuel-flow-rate-gph</property>
	      <value>0.702</value>
	    </product>
           <property>propulsion/engine[0]/thrust-lbs</property>
	  </quotient>
	  <value>1.0</value>
	</product>
</function>
      
      
      <function name="aero/function/CAX">
	<product>
          <difference>
	    <product>
              <property>inertia/cg-x-in</property>
              <value>0.0254</value>
	    </product>
	    <value>24.04</value>
	  </difference>
	  <value>18.9215</value>
	</product>
      </function>

        <function name="aero/function/auasp">
            <table name="alpha_max">
                <independentVar lookup="row">velocities/mach</independentVar>
                <independentVar lookup="column">fcs/flap-pos-deg</independentVar>
                <tableData>
                               0             15            28            45            
                  0.4           12            13            12            12            
                  0.6           12            13            12            12            
                  0.7           8.8           13            12            12            
                  0.8           7.8           13            12            12            
                  0.85          7.2           13            12            12            
                  0.9           6.6           13            12            12            
                </tableData>
            </table>
        </function>
        <function name="aero/function/cmf">
            <description>Mach and flaps parameter</description>
            <sum>
                <property>fcs/flap-pos-deg</property>
                <product>
                    <property>velocities/mach</property>
                    <value>-1</value>
                </product>
            </sum>
        </function>
        <function name="aero/function/cy">
            <description>Lift due to alpha</description>
            <table name="Cy">
                <independentVar lookup="row">aero/alpha-wing-rad</independentVar>
                <independentVar lookup="column">aero/function/cmf</independentVar>
                <tableData>
                               -0.95         -0.8          -0.5          -0.2           28            45            
                  -0.06981      -0.65         -0.65         -0.65         -0.65         0             0.25          
                  0             -0.22         -0.2          -0.25         -0.25         0.4           0.65          
                  0.04887       0.05          0.1           0.05          0             0.65          0.93          
                  0.08727       0.24          0.36          0.3           0.2           0.87          1.15          
                  0.1658        0.62          0.8           0.78          0.6           1.3           1.58          
                  0.2618        0.78          1             1.19          1.05          1.78          2.08          
                  0.2792        0.78          1.01          1.25          1.11          1.85          2.13          
                  0.2967        0.75          0.95          1.28          1.18          1.9           2.08          
                  0.3316        0.56          0.78          1.25          1.26          1.85          1.7           
                  0.3665        0.3           0.5           1.18          1.3           1.7           1.4           
                  0.384         0.18          0.35          1.1           1.27          1.6           1.3           
                  0.4363        -0.2          -0.1          0.9           1.13          1.3           1             
                </tableData>
            </table>
        </function>
	
        <axis name="LIFT" unit="LBS">
            <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/cy</property>
                </product>
            </function>
            <function name="aero/coefficient/dCLsb">
                <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>-0.65</value>
                </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>0.2</value>
                </product>
            </function>
            <function name="aero/coefficient/dCLg">
                <description>Delta_Lift_due_to_gear</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>gear/gear-pos-norm</property>
                    <value>-0.06</value>
                </product>
            </function>
            <function name="aero/coefficient/CLground">
                <description>Lift near ground</description>
                <product>
                    <table name="Delta lift due ground reaction">
                        <independentVar>position/h-agl-ft</independentVar>
                        <tableData>
                          0             0.13        
                          10            0.1         
                          27            0           
                        </tableData>
                    </table>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                </product>
            </function>
            
        </axis>
        <axis name="DRAG" unit="LBS">
<!--	  
            <function name="aero/coefficient/CDx">
                <description>Drag_due_to_Cy</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <table name="Cx">
                        <independentVar lookup="row">aero/function/cy</independentVar>
                        <independentVar lookup="column">aero/function/cmf</independentVar>
                        <tableData>
                                       -0.95         -0.9          -0.6          -0.2           28            45            
                          -0.25         0.032         0.028         0.025         0.025         0.11          0.2           
                          0             0.04          0.028         0.025         0.022         0.11          0.2           
                          0.25          0.05          0.037         0.027         0.025         0.11          0.2           
                          0.5           0.3           0.07          0.034         0.032         0.113         0.2           
                          0.75          1.7           0.3           0.049         0.05          0.125         0.202         
                          1             2.5           1             0.08          0.095         0.14          0.21          
                          1.05          2.6           1.2           0.1           0.12          0.145         0.212         
                          1.25          2.9           2             0.35          0.27          0.17          0.227         
                          1.5           3             2.5           1             0.6           0.205         0.263         
                          1.7           3             2.5           2             1             0.24          0.3           
                        </tableData>
                    </table>
                </product>
            </function>-->

 <!--           <function name="aero/coefficient/CDx">
                <description>Drag_due_to_alpha</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <table name="Cx">
                        <independentVar lookup="row">aero/alpha-wing-rad</independentVar>
                        <independentVar lookup="column">aero/function/cmf</independentVar>
                        <tableData>
                          -1             -0.95         -0.85       -0.7          -0.2           28            45
		-4.0	 -0.06981	0.08		0.048	  0.045		0.04		0.122		0.203
		0.0	  0		0.05		0.03	  0.028		0.025		0.114		0.2
		2.8	  0.04887	0.044		0.026	  0.025		0.022		0.118		0.207
		5.0	  0.08727	0.05		0.03	  0.03		0.025		0.133		0.225
		9.0	  0.1658	0.08		0.048	  0.045		0.04		0.172		0.266
		15.0	  0.2618	0.2		0.1	  0.097		0.091		0.25		0.35
		16.0	  0.2792	0.222		0.12	  0.111		0.106		0.26		0.36
		17.0	  0.2967	0.24		0.14	  0.120		0.115		0.27		0.37
		19.0	  0.3316	0.29		0.17	  0.145		0.14		0.29		0.39
		21.0	  0.3665	0.36		0.21	  0.18		0.174		0.31		0.41
		22.0	  0.384		0.4		0.24	  0.197		0.19		0.32		0.42
		25.0	  0.4363	0.5		0.3	  0.25		0.24   		0.38		0.48
                        </tableData>
                    </table>
                </product>
            </function>
 -->
 
 
            <function name="aero/coefficient/CDx">
                <description>Drag_due_to_alpha</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <table name="Cx">
                        <independentVar lookup="row">aero/alpha-wing-rad</independentVar>
                        <independentVar lookup="column">aero/function/cmf</independentVar>
                        <tableData>
                                       -0.95         -0.85       -0.7          -0.2           28            45
			 -0.06981	0.08		0.048	  0.045		0.04		0.122		0.203
			  0		0.05		0.03	  0.028		0.025		0.114		0.2
			  0.04887	0.044		0.026	  0.025		0.022		0.118		0.207
			  0.08727	0.05		0.03	  0.03		0.025		0.133		0.225
			  0.1658	0.08		0.048	  0.045		0.04		0.172		0.266
			  0.2618	0.2		0.1	  0.097		0.091		0.25		0.35
			  0.2792	0.222		0.12	  0.111		0.106		0.26		0.36
			  0.2967	0.24		0.14	  0.120		0.115		0.27		0.37
			  0.3316	0.29		0.17	  0.145		0.14		0.29		0.39
			  0.3665	0.36		0.21	  0.18		0.174		0.31		0.41
			  0.384		0.4		0.24	  0.197		0.19		0.32		0.42
			  0.4363	0.5		0.3	  0.25		0.24   		0.38		0.48
                        </tableData>
                    </table>
		    <value>0.92</value>
                </product>
            </function>
 
 
 
            <function name="aero/coefficient/CDgear">
                <description>Drag_due_to_gear</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>gear/gear-pos-norm</property>
                    <table name="Gear drag due to mach">
                        <independentVar>velocities/mach</independentVar>
                        <tableData>
                          0.2    0.0155
                          0.3    0.0157
                          0.4    0.0164
                          0.5    0.0176
                          0.6    0.0197
                          0.7    0.0233
                          0.8    0.0301
                          0.9    0.0468
                        </tableData>
                    </table>
                </product>
            </function>
            <function name="aero/coefficient/CDsb">
                <description>Drag_due_to_speedbrakes</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/speedbrake-pos-norm</property>
                    <value>0.019</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>
                    <table>
                        <independentVar>aero/beta-rad</independentVar>
                        <tableData>
                          -1.57         1.23        
                          -0.26         0.05        
                          0             0           
                          0.26          0.05        
                          1.57          1.23        
                        </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>
		    <abs>
		      <property>fcs/elevator-pos-norm</property>
		    </abs>
                    <value>0.01</value>
                </product>
            </function>
            <function name="aero/coefficient/CDground">
                <description>Drag near ground</description>
                <product>
                    <table name="Delta drag due ground reaction">
                        <independentVar>position/h-agl-ft</independentVar>
                        <tableData>
                          0             -0.01       
                          10            -0.008      
                          27            0           
                        </tableData>
                    </table>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                </product>
            </function>
        </axis>
        <axis name="SIDE" unit="LBS">
            <function name="aero/coefficient/CYb">
                <description>Side_force_due_to_beta</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/beta-rad</property>
                    <table name="side force due flaps">
                        <independentVar>fcs/flap-pos-deg</independentVar>
                        <tableData>
                          0             -0.859      
                          28            -1.031      
                          45            -1.146      
                        </tableData>
                    </table>
                </product>
            </function>
            <function name="aero/coefficient/CYr">
                <description>Side_force_due_rudder</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/rudder-pos-rad</property>
                    <value>-0.1776</value>
                </product>
            </function>
        </axis>
        <axis name="ROLL" unit="LBS*FT">
            <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>
                    <property>aero/beta-rad</property>
                    <table name="Roll due beta">
                        <independentVar lookup="row">aero/alpha-wing-rad</independentVar>
                        <independentVar lookup="column">fcs/flap-pos-deg</independentVar>
                        <tableData>
                                       0             28            45            
                          0             -0.00135      -0.003        -0.0034       
                          0.08727       -0.0017       -0.0033       -0.00375      
                          0.17453       -0.0019       -0.0036       -0.004        
                          0.2678        -0.0025       -0.0037       -0.0048       
                        </tableData>
                    </table>
                </product>
            </function>
            <function name="aero/coefficient/Clp">
                <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>-0.5</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>0.15</value>
                </product>
            </function>
            <function name="aero/coefficient/Clda">
                <description>Roll_moment_due_to_aileron</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>fcs/left-aileron-pos-rad</property>
                    <table>
                        <independentVar>velocities/mach</independentVar>
                        <tableData>
                          0.15          0.0659      
                          0.5           0.0595      
                          1             0.03438     
                        </tableData>
                    </table>
                    <value>1.4</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>-0.01719</value>
                </product>
            </function>
        </axis>
        <axis name="PITCH" unit="LBS*FT">
            <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>
                    <table name="Ma">
                        <independentVar lookup="row">aero/alpha-wing-rad</independentVar>
                        <independentVar lookup="column">fcs/flap-pos-deg</independentVar>
                        <tableData>
                                       0             15            28            45            
                          -0.06981      0.275         0.15          0             -0.14         
                          0             0.183         0.05          -0.08         -0.213        
                          0.06981       0.08          -0.05         -0.18         -0.29         
                          0.2618        -0.16         -0.27         -0.375        -0.453        
                          0.349         -0.212        -0.325        -0.425        -0.45         
                          0.3665        -0.21         -0.32         -0.412        -0.452        
                          0.384         -0.19         -0.3          -0.4          -0.425        
                        </tableData>
                    </table>
		    <value>1.25</value>
                </product>
            </function>
            <function name="aero/coefficient/Cmcg">
                <description>Pitch_moment_due_to_CG_position</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                    <property>aero/function/cy</property>
                    <product>
                        <sum>
                            <description>CG due 25%MAC</description>
                            <property>inertia/cg-x-in</property>
                            <value>-998.43</value>
                        </sum>
                        <value>0.012</value><!--0.0048-->
                    </product>
                    <value>1</value>
                </product>
            </function>
            <function name="aero/coefficient/Cmde">
                <description>Pitch_moment_due_to_elevator</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                    <table name="mme">
                        <independentVar>velocities/mach</independentVar>
                        <tableData>
                          0.4           1           
                          0.5           1           
                          0.7           1           
                          0.786         0.97        
                          0.87          0.8461      
                          0.9           0.7692      
                          0.95          0.5384      
                        </tableData>
                    </table>
                    <table name="cyh">
                        <independentVar lookup="row">fcs/elevator-pos-rad</independentVar>
                        <independentVar lookup="column">velocities/mach</independentVar>
                        <tableData>
                                       0             2             
                          -0.524        -1            -0.5          
                          -0.349        -0.85         -0.49         
                          -0.174        -0.5         -0.4          
                          0             0             0             
                          0.174         0.5          0.4           
                          0.349         0.85          0.49          
                          0.524         1             0.5           
                        </tableData>
                    </table>
                    <value>-0.7</value><!--0.48-->
                </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>-15</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>-4</value>
                </product>
            </function>
            <function name="aero/coefficient/Cstab">
                <description>Pitch moment due to stabilizer position</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                    <table name="mms">
                        <independentVar>velocities/mach</independentVar>
                        <tableData>
                          0.4           1           
                          0.7           1.083       
                          0.87          1.2083      
                          0.9           1.25        
                          0.95          1.1875      
                        </tableData>
                    </table>
                    <table name="cys">
                        <independentVar lookup="row">fcs/stabilizer-pos-rad</independentVar>
                        <independentVar lookup="column">velocities/mach</independentVar>
                        <tableData>
                                       0             2             
                          -0.524        3.2           1.6           
                          -0.349        3.2           1.6           
                          -0.174        2.08          1.28          
                          0             0             0             
                          0.174         -2.08         -1.28         
                          0.349         -3.2          -1.6          
                          0.524         -3.2          -1.6          
                        </tableData>
                    </table>
                    <value>-0.47</value>
                </product>
            </function>
        </axis>
        <axis name="YAW" unit="LBS*FT">
            <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>
                    <table name="Yaw moment due flaps and Mach">
                        <independentVar lookup="row">fcs/flap-pos-deg</independentVar>
                        <independentVar lookup="column">velocities/mach</independentVar>
                        <tableData>
                                       0.1           0.9           
                          0             -0.15         -0.218        
                          28            -0.2          -0.2934       
                          45            -0.24         -0.3518       
                        </tableData>
                    </table>
                    <value>-1</value>
                </product>
            </function>
            <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>-0.15</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>-0.0745</value>
                </product>
            </function>
        </axis>
    </aerodynamics>
    
    <external_reactions>
      <force name="tractor" frame="BODY">
	<location unit="IN">
	<x>  -700 </x>
	<y>    0.0 </y>
	<z>  -61.0 </z>
	</location>
	<direction>
	<x>1</x>
	<y>0</y>
	<z>0</z>
	</direction>
      </force>
   </external_reactions>
<!--   
    <output name="tu-fldata.csv" type="CSV" rate="1">
        <simulation> OFF </simulation>
        <atmosphere> OFF </atmosphere>
        <massprops> OFF </massprops>
        <aerosurfaces> ON </aerosurfaces>
        <rates> OFF </rates>
        <velocities> ON </velocities>
        <forces> OFF </forces>
        <moments> OFF </moments>
        <position> ON </position>
        <coefficients> OFF </coefficients>
        <ground_reactions> OFF </ground_reactions>
        <fcs> OFF </fcs>
        <propulsion> ON </propulsion>
	<property>velocities/vc-kts</property>
	<property>velocities/vc-fps</property>
	<property>velocities/mach</property>
	<property>ap/pitch/met-input</property>
	<property>ap/pitch/met</property>
	<property>ap/pitch/gs-k5</property>
	<property>ap/pitch/main-stab-summer</property>
	<property>ap/pitch/latch-out-rad</property>
	<property>debug/gs-epsilon</property>
	<property>debug/h-m</property>
	<property>debug/wp-hdg-corrected</property>
	<property>debug/wp-distance</property>
    </output>-->
    
    <system file="tu154b-misc"/>

  </fdm_config>