<?xml version="1.0"?>
<?xml-stylesheet href="JSBSim.xsl" type="application/xml"?>
<fdm_config name="an24" version="2.0" release="ALPHA">

    <fileheader>
        <author> Aeromatic v 0.95 </author>
        <filecreationdate> 2013-08-31 </filecreationdate>
        <description>
Models        </description>
        <version> $Revision: 1.15 $ </version>
    </fileheader>

    <metrics>
        <wingarea unit="M2"> 74.98 </wingarea>
        <wingspan unit="M"> 29.2 </wingspan>
        <chord unit="M"> 2.813 </chord>
        <wing_incidence unit="DEG"> 3 </wing_incidence>
        <htailarea unit="M2"> 17.23 </htailarea>
        <htailarm unit="M"> 12.249 </htailarm>
        <vtailarea unit="M2"> 13.28 </vtailarea>
        <vtailarm unit="M"> 11.297 </vtailarm>
        <location name="AERORP" unit="M">
            <x> 8.86337 </x>
            <y> 0 </y>
            <z> 0.73 </z> <!-- 1.392 -->
        </location>
        <location name="EYEPOINT" unit="M">
            <x> 2.1 </x>
            <y> -0.48 </y>
            <z> 1.1 </z>
        </location>
        <location name="VRP" unit="M">
            <x> 8.5 </x>
            <y> 0 </y>
            <z> 0 </z>
        </location>
    </metrics>

    <mass_balance>
    <!--    <ixx unit="SLUG*FT2">214809</ixx>
        <iyy unit="SLUG*FT2">166865</iyy>
        <izz unit="SLUG*FT2">377779</izz> -->
        <ixx unit="SLUG*FT2">400000</ixx>
        <iyy unit="SLUG*FT2">250000</iyy>
        <izz unit="SLUG*FT2">500000</izz>
        <ixz unit="KG*M2">0</ixz>
        <iyz unit="KG*M2">0</iyz>
        <ixy unit="KG*M2">0</ixy>
        <emptywt unit="KG">13250</emptywt>
        <location name="CG" unit="M">
            <x>9.446</x>
            <y>0</y>
            <z>0.73</z>
        </location>
        <pointmass name="2 pilots">
            <weight unit="KG">160</weight>
            <location unit="M">
                <x>2.74</x>
                <y>0</y>
                <z>0.38</z>
            </location>
        </pointmass>
        <pointmass name="Cabin crew">
            <weight unit="KG">80</weight>
            <location unit="M">
                <x>16.2</x>
                <y>0</y>
                <z>0.1</z>
            </location>
        </pointmass>
        <pointmass name="Engine oil">
            <weight unit="KG">95</weight>
            <location unit="M">
                <x>6.91</x>
                <y>0</y>
                <z>0.57</z>
            </location>
        </pointmass>
        <pointmass name="Toilet water">
            <weight unit="KG">26</weight>
            <location unit="M">
                <x>15.9</x>
                <y>0</y>
                <z>1.2</z>
            </location>
        </pointmass>
        <pointmass name="Oxygen cistern in cabin">
            <weight unit="KG">3</weight>
            <location unit="M">
                <x>17.2</x>
                <y>0</y>
                <z>0.65</z>
            </location>
        </pointmass>
        <pointmass name="Oxygen cistern in cockpit">
            <weight unit="KG">3</weight>
            <location unit="M">
                <x>3.28</x>
                <y>0</y>
                <z>0.4</z>
            </location>
        </pointmass>
        <pointmass name="Toilet chemicals">
            <weight unit="KG">6</weight>
            <location unit="M">
                <x>16.6</x>
                <y>0</y>
                <z>-0.45</z>
            </location>
        </pointmass>
        <pointmass name="Buffet">
            <weight unit="KG">40</weight>
            <location unit="M">
                <x>16.1</x>
                <y>0</y>
                <z>-0.35</z>
            </location>
        </pointmass>
        <pointmass name="Passangers row 1">
            <weight unit="KG">300</weight>
            <location unit="M">
                <x>6.61</x>
                <y>0</y>
                <z>-0.06</z>
            </location>
        </pointmass>
        <pointmass name="Passangers row 2">
            <weight unit="KG">300</weight>
            <location unit="M">
                <x>7.33</x>
                <y>0</y>
                <z>-0.06</z>
            </location>
        </pointmass>
        <pointmass name="Passangers row 3">
            <weight unit="KG">300</weight>
            <location unit="M">
                <x>8.05</x>
                <y>0</y>
                <z>-0.06</z>
            </location>
        </pointmass>
        <pointmass name="Passangers row 4">
            <weight unit="KG">300</weight>
            <location unit="M">
                <x>8.77</x>
                <y>0</y>
                <z>-0.06</z>
            </location>
        </pointmass>
        <pointmass name="Passangers row 5">
            <weight unit="KG">300</weight>
            <location unit="M">
                <x>9.49</x>
                <y>0</y>
                <z>-0.06</z>
            </location>
        </pointmass>
        <pointmass name="Passangers row 6">
            <weight unit="KG">300</weight>
            <location unit="M">
                <x>10.21</x>
                <y>0</y>
                <z>-0.06</z>
            </location>
        </pointmass>
        <pointmass name="Passangers row 7">
            <weight unit="KG">300</weight>
            <location unit="M">
                <x>10.93</x>
                <y>0</y>
                <z>-0.06</z>
            </location>
        </pointmass>
        <pointmass name="Passangers row 8">
            <weight unit="KG">300</weight>
            <location unit="M">
                <x>11.65</x>
                <y>0</y>
                <z>-0.06</z>
            </location>
        </pointmass>
        <pointmass name="Passangers row 9">
            <weight unit="KG">300</weight>
            <location unit="M">
                <x>12.37</x>
                <y>0</y>
                <z>-0.06</z>
            </location>
        </pointmass>
        <pointmass name="Passangers row 10">
            <weight unit="KG">300</weight>
            <location unit="M">
                <x>13.09</x>
                <y>0</y>
                <z>-0.06</z>
            </location>
        </pointmass>
        <pointmass name="Passangers row 11">
            <weight unit="KG">300</weight>
            <location unit="M">
                <x>13.81</x>
                <y>0</y>
                <z>-0.06</z>
            </location>
        </pointmass>
        <pointmass name="Passangers row 12">
            <weight unit="KG">300</weight>
            <location unit="M">
                <x>14.53</x>
                <y>0</y>
                <z>-0.06</z>
            </location>
        </pointmass>
        <pointmass name="Passangers row 13">
            <weight unit="KG">150</weight>
            <location unit="M">
                <x>15.25</x>
                <y>0</y>
                <z>-0.06</z>
            </location>
        </pointmass>
        <pointmass name="Baggage room 1 left">
            <weight unit="KG">700</weight>
            <location unit="M">
                <x>5.02</x>
                <y>-0.7</y>
                <z>0.3</z>
            </location>
        </pointmass>
        <pointmass name="Baggage room 1 right">
            <weight unit="KG">250</weight>
            <location unit="M">
                <x>5.34</x>
                <y>0.7</y>
                <z>0.3</z>
            </location>
        </pointmass>
        <pointmass name="Baggage room 2">
            <weight unit="KG">260</weight>
            <location unit="M">
                <x>18</x>
                <y>0</y>
                <z>0.4</z>
            </location>
        </pointmass>
        <pointmass name="Baggage room 3">
            <weight unit="KG">0</weight>
            <location unit="M">
                <x>19.28</x>
                <y>0</y>
                <z>0.6</z>
            </location>
        </pointmass>
        <pointmass name="Ballast for gear weight shift">
            <weight unit="KG">500</weight>
            <location unit="M">
                <x>9.446</x>
                <y>0</y>
                <z>0.73</z>
            </location>
        </pointmass>
    </mass_balance>

    <ground_reactions>
        <contact type="BOGEY" name="NOSE">
            <location unit="M">
                <x> 2.42 </x>
                <y> 0 </y>
                <z> -1.91 </z>
            </location>
            <static_friction> 0.6 </static_friction>
            <dynamic_friction> 0.5 </dynamic_friction>
            <rolling_friction> 0.02 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 15000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 6000 </damping_coeff>
            <damping_coeff_rebound unit="LBS/FT/SEC">9000</damping_coeff_rebound>
            <max_steer unit="DEG"> 45 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable> 1 </retractable>
        </contact>
        <contact type="BOGEY" name="LEFT_MAIN">
            <location unit="M">
                <x> 10.27 </x>
                <y> -3.95 </y>
                <z> -1.91 </z>
            </location>
            <static_friction> 0.6 </static_friction>
            <dynamic_friction> 0.5 </dynamic_friction>
            <rolling_friction> 0.02 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 27300 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 5000 </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> 10.27 </x>
                <y> 3.95 </y>
                <z> -1.91 </z>
            </location>
            <static_friction> 0.6 </static_friction>
            <dynamic_friction> 0.5 </dynamic_friction>
            <rolling_friction> 0.02 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 27300 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 5000 </damping_coeff>
            <max_steer unit="DEG"> 0 </max_steer>
            <brake_group> RIGHT </brake_group>
            <retractable> 1 </retractable>
        </contact>
        <contact type="STRUCTURE" name="LEFT_WING">
            <location unit="M">
                <x> 10.27 </x>
                <y> -14.1 </y>
                <z> 1.214 </z>
            </location>
            <static_friction> 1 </static_friction>
            <dynamic_friction> 1 </dynamic_friction>
            <rolling_friction> 0 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 20000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 5000 </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> 10.27 </x>
                <y> 14.1 </y>
                <z> 1.214 </z>
            </location>
            <static_friction> 1 </static_friction>
            <dynamic_friction> 1 </dynamic_friction>
            <rolling_friction> 0 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 20000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 5000 </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> 14.1 </x>
                <y> 0 </y>
                <z> -1.05 </z>
            </location>
            <static_friction> 1 </static_friction>
            <dynamic_friction> 1 </dynamic_friction>
            <rolling_friction> 0 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 20000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 5000 </damping_coeff>
            <max_steer unit="DEG"> 0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable> 0 </retractable>
        </contact>
        <contact type="STRUCTURE" name="NOSE">
            <location unit="M">
                <x> 0 </x>
                <y> 0 </y>
                <z> 0 </z>
            </location>
            <static_friction> 1 </static_friction>
            <dynamic_friction> 1 </dynamic_friction>
            <rolling_friction> 0 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 20000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 5000 </damping_coeff>
            <max_steer unit="DEG"> 0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable> 0 </retractable>
        </contact>
        <contact type="STRUCTURE" name="FUSELAGE_FRONT">
            <location unit="M">
                <x> 5 </x>
                <y> 0 </y>
                <z> -1.05 </z>
            </location>
            <static_friction> 1 </static_friction>
            <dynamic_friction> 1 </dynamic_friction>
            <rolling_friction> 0 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 20000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 5000 </damping_coeff>
            <max_steer unit="DEG"> 0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable> 0 </retractable>
        </contact>
    </ground_reactions>

    <propulsion>
        <engine file="ai24">
            <location unit="M">
                <x> 5.94 </x>
                <y> -3.95 </y>
                <z> 1.185 </z>
            </location>
            <orient unit="DEG">
                <roll> 0 </roll>
                <pitch> 0 </pitch>
                <yaw> 0 </yaw>
            </orient>
            <feed>2</feed>
            <feed>1</feed>
            <feed>0</feed>
            <feed>3</feed>
            <feed>4</feed>
            <feed>5</feed>
            <thruster file="prop_av72">
                <sense>-1</sense>
                <location unit="M">
                    <x> 5.94 </x>
                    <y> -3.95 </y>
                    <z> 1.185 </z>
                </location>
                <orient unit="DEG">
                    <roll> 0 </roll>
                    <pitch> 1 </pitch>
                    <yaw> 0 </yaw>
                </orient>
            </thruster>
        </engine>
        <engine file="ai24">
            <location unit="M">
                <x> 5.94 </x>
                <y> 3.95 </y>
                <z> 1.185 </z>
            </location>
            <orient unit="DEG">
                <roll> 0 </roll>
                <pitch> 0 </pitch>
                <yaw> 0 </yaw>
            </orient>
            <feed>3</feed>
            <feed>4</feed>
            <feed>5</feed>
            <feed>2</feed>
            <feed>1</feed>
            <feed>0</feed>
            <thruster file="prop_av72">
                <sense>-1</sense>
              <location unit="M">
                    <x> 5.94 </x>
                    <y> 3.95 </y>
                    <z> 1.185 </z>
                </location>
                <orient unit="DEG">
                    <roll> 0 </roll>
                    <pitch> 1 </pitch>
                    <yaw> 0 </yaw>
                </orient>
            </thruster>
        </engine>
        <engine file="gtd-16">
          <location unit="M">
                <x> 5.94 </x>
                <y> 3.95 </y>
                <z> 1.185 </z>
          </location>
          <orient unit="DEG">
            <roll> 0 </roll>
            <pitch> 0 </pitch>
            <yaw> 0 </yaw>
          </orient>
          <feed>3</feed>
          <feed>4</feed>
          <feed>5</feed>
          <feed>0</feed>
          <feed>1</feed>
          <feed>2</feed>
          <thruster file="direct">
            <location unit="M">
                <x> 5.94 </x>
                <y> 3.95 </y>
                <z> 1.185 </z>
            </location>
            <orient unit="DEG">
              <roll> 0 </roll>
              <pitch> 0 </pitch>
              <yaw> 90 </yaw>
            </orient>
          </thruster>
        </engine>

        <tank type="FUEL">
            <location unit="M">
                <x> 9.65 </x>
                <y> -1.4 </y>
                <z> 1.523 </z>
            </location>
            <drain_location unit="M">
                <x> 9.696</x>
                <y> -1.4 </y>
                <z> 1.207 </z>
            </drain_location>
            <capacity unit="KG">275</capacity>
            <contents unit="KG">275</contents>
            <priority>1</priority>
        </tank>
        <tank type="FUEL">
            <location unit="M">
                <x> 9.65 </x>
                <y> -3 </y>
                <z> 1.523 </z>
            </location>
            <drain_location unit="M">
                <x> 9.696</x>
                <y> -3 </y>
                <z> 1.207 </z>
            </drain_location>
            <capacity unit="KG">275</capacity>
            <contents unit="KG">275</contents>
            <priority>1</priority>
        </tank>
        <tank type="FUEL">
            <location unit="M">
                <x> 9.84 </x>
                <y> -7.45 </y>
                <z> 1.466 </z>
            </location>
            <drain_location unit="M">
                <x> 9.84</x>
                <y> -7.45 </y>
                <z> 1.22 </z>
            </drain_location>
            <capacity unit="KG">1425</capacity>
            <contents unit="KG">390</contents>
            <priority>1</priority>
        </tank>
        <tank type="FUEL">
            <location unit="M">
                <x> 9.84 </x>
                <y> 7.45 </y>
                <z> 1.466 </z>
            </location>
            <drain_location unit="M">
                <x> 9.84</x>
                <y> 7.45 </y>
                <z> 1.22 </z>
            </drain_location>
            <capacity unit="KG">1425</capacity>
            <contents unit="KG">390</contents>
            <priority>1</priority>
        </tank>
        <tank type="FUEL">
            <location unit="M">
                <x> 9.65 </x>
                <y> 3 </y>
                <z> 1.523 </z>
            </location>
            <drain_location unit="M">
                <x> 9.696</x>
                <y> 3 </y>
                <z> 1.207 </z>
            </drain_location>
            <capacity unit="KG">275</capacity>
            <contents unit="KG">275</contents>
            <priority>1</priority>
        </tank>
        <tank type="FUEL">
            <location unit="M">
                <x> 9.65 </x>
                <y> 1.4 </y>
                <z> 1.523 </z>
            </location>
            <drain_location unit="M">
                <x> 9.696</x>
                <y> 1.4 </y>
                <z> 1.207 </z>
            </drain_location>
            <capacity unit="KG">275</capacity>
            <contents unit="KG">275</contents>
            <priority>1</priority>
        </tank>

    </propulsion>

    <flight_control name="FCS: an24">

        <channel name="exhaust thrust left">
          <fcs_function name="aero/function/left-engine-exhaust-thrust">
                <function>
                    <product>
                        <property>propulsion/engine[0]/fuel-flow-rate-pps</property>
                        <value>3.1441</value>
                        <sum>
                          <value>178</value>
                          <product>
                            <value>-0.5144</value>
                            <property>velocities/ve-kts</property>
                          </product>
                        </sum>
                        <value>2.2026</value>
                    </product>
                </function>
                <output> external_reactions/exhaust-thrust-left/magnitude </output>
            </fcs_function>
        </channel>

        <channel name="exhaust thrust right">
          <fcs_function name="aero/function/right-engine-exhaust-thrust">
                <function>
                    <product>
                        <property>propulsion/engine[1]/fuel-flow-rate-pps</property>
                        <value>3.1441</value>
                        <sum>
                          <value>178</value>
                          <product>
                            <value>-0.5144</value>
                            <property>velocities/ve-kts</property>
                          </product>
                        </sum>
                        <value>2.2026</value>
                    </product>
                </function>
                <output> external_reactions/exhaust-thrust-right/magnitude </output>
            </fcs_function>
        </channel>

        <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>-0.52</min>
                <max>0.26</max>
              </range>
              <output>fcs/elevator-pos-rad</output>
            </aerosurface_scale>

            <aerosurface_scale name="elevator normalization">
              <input>fcs/elevator-pos-rad</input>
              <domain>
                <min>-0.52</min>
                <max>0.26</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>
              <range>
                <min>-0.419</min>
                <max>0.279</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>-0.279</min>
                <max>0.419</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>-0.419</min>
                <max>0.279</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>-0.279</min>
                <max>0.419</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>-1</min>
                <max>1</max>
              </clipto>
            </summer>

            <aerosurface_scale name="Rudder Control">
              <input>fcs/rudder-command-sum</input>
              <range>
                <min>-0.436</min>
                <max>0.436</max>
              </range>
              <output>fcs/rudder-pos-rad</output>
            </aerosurface_scale>

            <aerosurface_scale name="rudder normalization">
              <input>fcs/rudder-pos-rad</input>
              <domain>
                <min>-0.436</min>
                <max>0.436</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>38</position>
                  <time>15</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>38</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>5</time>
                </setting>
              </traverse>
              <output>gear/gear-pos-norm</output>
            </kinematic>

        </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>104.34</value>
                    </product>
                    <value>267.55</value>
                  </sum>
                </function>
                <output> inertia/pointmass-location-X-inches[25] </output>
            </fcs_function>

        </channel>

      <property value="12.3">fcs/aero/auasp-limit</property>

    </flight_control>

    <system file="throttle-idle-lock"/>
    <system file="prop-governor"/>
    <system file="steering"/>
    <system file="skid-slip-ball"/>
    <system file="gtd-16"/>

       <external_reactions>
    
        <force name="exhaust-thrust-left" frame="BODY">
            <location unit="M">
            <x>  7.5  </x>
            <y>    -4.2 </y>
            <z>    1.185 </z>
            </location>
            <direction>
            <x>    1 </x>
            <y>    0.707 </y>
            <z>    -0.707 </z>
            </direction>
        </force>

        <force name="exhaust-thrust-right" frame="BODY">
            <location unit="M">
            <x>  7.5  </x>
            <y>    4.2 </y>
            <z>    1.185 </z>
            </location>
            <direction>
            <x>    1 </x>
            <y>    -0.707 </y>
            <z>    -0.707 </z>
            </direction>
        </force>
    
    </external_reactions>

    <aerodynamics>
        <function name="aero/function/alpha-stab-deg">
            <description>Alpha angle at stabilzer due to epsilon</description>
            <table>
                <independentVar lookup="row">aero/alpha-wing-rad</independentVar>
                <independentVar lookup="column">fcs/flap-pos-deg</independentVar>
                <tableData>
	0	15	38
-0.1745	-8.25	-9.05	-11.14
-0.1396	-7.56	-8.56	-10.68
-0.1047	-6.79	-7.92	-10.16
-0.0698	-5.95	-7.26	-9.59
-0.0349	-4.93	-6.57	-9
0	-3.92	-5.78	-8.34
0.0349	-2.84	-4.99	-7.64
0.0698	-1.7	-4.13	-6.86
0.1047	-0.38	-3.17	-6.04
0.1396	1.56	-1.99	-5.07
0.1745	3.15	-0.61	-3.95
0.2094	4.77	2.16	-2.59
0.2443	6.4	3.78	1.64
0.2793	8.02	5.4	3.48
0.3142	9.64	7.02	5.32
0.3491	11.27	8.64	7.16            
                </tableData>
            </table>
        </function>
        <function name="aero/function/epsilon-deg">
            <description>Epsilon at stabilizer</description>
            <product>
              <sum>
                <property>aero/alpha-wing-rad</property>
		<product>
			<value>-0.017452007</value>
			<property>aero/function/alpha-stab-deg</property>
                </product>
                <value>-0.052356021</value>		
	      </sum>
             <value>57.3</value>
           </product>
        </function>

        <aero_ref_pt_shift_x>
                 <function name="aero/function/aero-ref-shift">
             <value>0.25</value>
                </function>
        </aero_ref_pt_shift_x>

        <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>
		-0.5		-0.15		0		15		38            
-0.17453293	-1.02052	-0.813949	-0.813949	-0.644044	0.030347
-0.15707963	-0.910132	-0.724111	-0.724111	-0.531228	0.144148
-0.13962634	-0.79974	-0.634274	-0.634274	-0.418412	0.25795
-0.12217305	-0.689348	-0.544436	-0.544436	-0.305597	0.371751
-0.10471976	-0.578955	-0.454598	-0.454598	-0.192781	0.485552
-0.08726646	-0.468563	-0.36476	-0.36476	-0.0799652	0.599353
-0.06981317	-0.358171	-0.274923	-0.274923	0.0328506	0.713155
-0.05235988	-0.247779	-0.185085	-0.185085	0.145666	0.826956
-0.03490659	-0.137387	-0.0952473	-0.0952473	0.258482	0.939772
-0.01745329	-0.0269949	-0.00540958	-0.00540958	0.3672		1.04817
0		0.0833972	0.0844281	0.0844281	0.474402	1.15657
0.01745329	0.193789	0.174266	0.174266	0.581605	1.26497
0.03490659	0.304181	0.264104	0.264104	0.688807	1.37338
0.05235988	0.411746	0.35231		0.35231		0.797637	1.48178
0.06981317	0.515116	0.439643	0.439643	0.906849	1.58847
0.08726646	0.618008	0.526976	0.526976	1.01367		1.68901
0.10471976	0.711172	0.614309	0.614309	1.11783		1.78954
0.12217305	0.804336	0.701642	0.701642	1.22161		1.89008
0.13962634	0.889681	0.789492	0.789492	1.3193		1.98426
0.15707963	0.964795	0.877895	0.877895	1.41699		2.07217
0.17453293	1.02289		0.966116	0.966116	1.51113		2.16045
0.19198622	1.07382		1.05146		1.05146		1.60474		2.24933
0.20943951	1.10754		1.13607		1.13607		1.68765		2.32932
0.2268928	1.12338		1.2123		1.2123		1.76424		2.39788
0.2443461	1.07692		1.28478		1.28478		1.83275		2.45259
0.26179939	1.01575		1.35417		1.35417		1.89319		2.49714
0.27925268	0.986436	1.4207		1.4207		1.94253		2.51038
0.29670597	0.974535	1.48364		1.48364		1.9808		2.50333
0.31415927	0.962634	1.52374		1.52374		1.99619		2.4897
0.33161256	0.95708		1.52946		1.52946		1.9826		2.47608
0.34906585	0.952507	1.48065		1.48065		1.96631		2.46245           
                </tableData>
            </table>
        </function>
        <function name="aero/function/cx">
            <description>Drag due to alpha and flaps</description>
            <table name="Cx">
                <independentVar lookup="row">aero/alpha-wing-rad</independentVar>
                <independentVar lookup="column">aero/function/cmf</independentVar>
                <tableData>
		-0.5	-0.15	0	15	38
-0.17453293	0.045	0.037	0.037	0.06	0.11
-0.15707963	0.0435	0.0355	0.0355	0.055	0.105
-0.13962634	0.042	0.034	0.034	0.05	0.1
-0.12217305	0.0405	0.032	0.032	0.047	0.10235
-0.10471976	0.039	0.03	0.03	0.044	0.1047
-0.08726646	0.038	0.029	0.029	0.0419	0.116
-0.06981317	0.037	0.028	0.028	0.0398	0.1273
-0.05235988	0.036	0.0275	0.0275	0.0389	0.1289
-0.03490659	0.035	0.027	0.027	0.038	0.1305
-0.01745329	0.03415	0.0263	0.0263	0.0389	0.13665
0		0.0333	0.0256	0.0256	0.0398	0.1428
0.01745329	0.03355	0.025	0.025	0.04365	0.15035
0.03490659	0.0338	0.0244	0.0244	0.0475	0.1579
0.05235988	0.036	0.02655	0.02655	0.053	0.16625
0.06981317	0.0382	0.0287	0.0287	0.0585	0.1746
0.08726646	0.04315	0.0323	0.0323	0.066	0.1867
0.10471976	0.0481	0.0359	0.0359	0.0735	0.1988
0.12217305	0.057	0.0411	0.0411	0.0832	0.21345
0.13962634	0.0659	0.0463	0.0463	0.0929	0.2281
0.15707963	0.08295	0.05335	0.05335	0.10455	0.2442
0.17453293	0.1	0.0604	0.0604	0.1162	0.2603
0.19198622	0.125	0.06935	0.06935	0.1331	0.2758
0.20943951	0.15	0.0783	0.0783	0.15	0.2913
0.2268928	0.175	0.0895	0.0895	0.17	0.308
0.2443461	0.2	0.1007	0.1007	0.19	0.3247
0.26179939	0.225	0.11605	0.11605	0.215	0.3456
0.27925268	0.25	0.1314	0.1314	0.24	0.3665
0.29670597	0.28	0.1487	0.1487	0.265	0.3927
0.31415927	0.31	0.166	0.166	0.29	0.4189
0.33161256	0.345	0.193	0.193	0.315	0.45555
0.34906585	0.38	0.22	0.22	0.34	0.4922   
                </tableData>
            </table>
        </function>
        <function name="aero/function/mz">
            <table name="Mz">
                <independentVar lookup="row">aero/alpha-wing-rad</independentVar>
                <independentVar lookup="column">fcs/flap-pos-deg</independentVar>
                <tableData>
                               0             15            38            
                  -0.172436     0.448704      0.435513      0.38739       
                  -0.147824     0.408455      0.395294      0.348668      
                  -0.140986     0.397274      0.384121      0.337911      
                  -0.00608013   0.176665      0.163677      0.125671      
                  0.000976808   0.16596       0.152146      0.114569      
                  0.0132367     0.147362      0.132112      0.0930775     
                  0.046209      0.0973444     0.0847434     0.0352788     
                  0.0765166     0.0565805     0.0412023     -0.0178489    
                  0.109469      0.0122594     -0.00456033   -0.0756126    
                  0.123543      -0.00483209   -0.0241057    -0.100284     
                  0.13971       -0.0244656    -0.0465579    -0.130835     
                  0.167167      -0.0476138    -0.0846888    -0.182721     
                  0.187927      -0.0773428    -0.113518     -0.221949     
                  0.241451      -0.153997     -0.181147     -0.323097     
                  0.243411      -0.157068     -0.183624     -0.326801     
                  0.268276      -0.196021     -0.215042     -0.392682     
                  0.282789      -0.218756     -0.233378     -0.436261     
                  0.287641      -0.226355     -0.248046     -0.450827     
                  0.28962       -0.229457     -0.254033     -0.455172     
                  0.30907       -0.271944     -0.312844     -0.497848     
                  0.309709      -0.273338     -0.315223     -0.499248     
                  0.314445      -0.283688     -0.332889     -0.506354     
                  0.330347      -0.338396     -0.392182     -0.530201     
                  0.346507      -0.393996     -0.452441     -0.543446     
                  0.34682       -0.395071     -0.453606     -0.543702     
                  0.347691      -0.398066     -0.456852     -0.544061     
                  0.453744      -0.762942     -0.852304     -0.587767     
                </tableData>
            </table>
        </function>
        <function name="aero/function/cx_delta_ground">
            <description>Delta Cx due to ground effect</description>
            <table>
                <independentVar lookup="row">aero/function/cy</independentVar>
                <independentVar lookup="column">fcs/flap-pos-deg</independentVar>
                <tableData>
                               0             15            38            
                  0             0             0             0             
                  0.2           0             -0.0045       -0.0041       
                  0.5           0             -0.0129       -0.0124       
                  0.8           0             -0.0262       -0.0217       
                  1             0             -0.0343       -0.0293       
                  1.5           0             -0.0558       -0.0517       
                  2             0             -0.0595       -0.0786       
                  2.5           0             -0.0595       -0.1189       
                  3             0             -0.0595       -0.1189       
                </tableData>
            </table>
        </function>
        <function name="aero/function/cy_delta_ground">
            <description>Delta Cy due to ground effect</description>
            <table>
                <independentVar lookup="row">aero/alpha-wing-rad</independentVar>
                <independentVar lookup="column">fcs/flap-pos-deg</independentVar>
                <tableData>
                               0             15            38            
                  -0.1047       0             0.04          0.1103        
                  -0.0349       0             0.0417        0.1748        
                  0.0698        0             0.1399        0.1925        
                  0.1047        0             0.1252        0.1576        
                  0.1396        0             0.1461        0.0996        
                  0.1745        0             0.1556        0.0735        
                  0.2443        0             0.166         0.05          
                  0.2793        0             0.1328        0.05          
                  0.3142        0             0.1017        0.05          
                  0.3491        0             0.05          0.05          
                </tableData>
            </table>
        </function>
        <function name="aero/function/my">
            <description>my due to beta and rudder angle</description>
            <table>
                <independentVar lookup="row">aero/beta-rad</independentVar>
                <independentVar lookup="column">fcs/rudder-pos-rad</independentVar>
                <tableData>
	-0.436	-0.349	-0.175	0	0.175	0.349	0.436
-0.4414757983	-0.03979	-0.04984	-0.06994	-0.08931	-0.10868	-0.12878	-0.13883
-0.4389311083	-0.03935	-0.04941	-0.06953	-0.08896	-0.10839	-0.12851	-0.13857
-0.4385471358	-0.03929	-0.04935	-0.06947	-0.08891	-0.10835	-0.12847	-0.13853
-0.4378734387	-0.03918	-0.04924	-0.06936	-0.08882	-0.10828	-0.1284	-0.13846
-0.4117633131	-0.03476	-0.04489	-0.06516	-0.0853	-0.10544	-0.12571	-0.13584
-0.3910462549	-0.03126	-0.04145	-0.06183	-0.0825	-0.10317	-0.12355	-0.13374
-0.3857753606	-0.03036	-0.04057	-0.06099	-0.08179	-0.10259	-0.12301	-0.13322
-0.3698178152	-0.02644	-0.0371	-0.05842	-0.07964	-0.10086	-0.12218	-0.13284
-0.3504830578	-0.02167	-0.03288	-0.05531	-0.0753	-0.09529	-0.11772	-0.12893
-0.3234025291	-0.01582	-0.02699	-0.04933	-0.06922	-0.08911	-0.11145	-0.12262
-0.3216606905	-0.01539	-0.02657	-0.04894	-0.06883	-0.08872	-0.11109	-0.12227
-0.312312707	-0.01303	-0.02431	-0.04688	-0.06652	-0.08616	-0.10873	-0.12001
-0.3099914191	-0.01245	-0.02375	-0.04636	-0.06595	-0.08554	-0.10815	-0.11945
-0.285511431	-0.00731	-0.01784	-0.03891	-0.05989	-0.08087	-0.10194	-0.11247
-0.2704736742	-0.00415	-0.01421	-0.03434	-0.05566	-0.07698	-0.09711	-0.10717
-0.2314079695	0.00423	-0.00477	-0.02276	-0.04467	-0.06658	-0.08457	-0.09357
-0.2301548231	0.00445	-0.0045	-0.02239	-0.04432	-0.06625	-0.08414	-0.09309
-0.2298720798	0.0045	-0.00444	-0.02231	-0.04424	-0.06617	-0.08404	-0.09298
-0.2229954825	0.00593	-0.00293	-0.02065	-0.04231	-0.06397	-0.08169	-0.09055
-0.1915394134	0.01245	0.00395	-0.01305	-0.03443	-0.05581	-0.07281	-0.08131
-0.1835562774	0.01419	0.0057	-0.01127	-0.03243	-0.05359	-0.07056	-0.07905
-0.167939944	0.01757	0.00912	-0.00777	-0.02878	-0.04979	-0.06668	-0.07513
-0.1543275975	0.01981	0.01163	-0.00472	-0.0256	-0.04648	-0.06283	-0.07101
-0.1320971643	0.02361	0.01572	-0.00006	-0.0204	-0.04074	-0.05652	-0.06441
-0.1229610638	0.02519	0.01741	0.00186	-0.01868	-0.03922	-0.05477	-0.06255
-0.117666433	0.02609	0.01838	0.00297	-0.01768	-0.03833	-0.05374	-0.06145
-0.1160408333	0.02629	0.01863	0.00331	-0.01737	-0.03805	-0.05337	-0.06103
-0.0799921048	0.03159	0.02422	0.00948	-0.01058	-0.03064	-0.04538	-0.05275
-0.0763509989	0.03217	0.02479	0.01003	-0.0099	-0.02983	-0.04459	-0.05197
-0.0718134919	0.03288	0.02549	0.01072	-0.00918	-0.02908	-0.04385	-0.05124
-0.0472446666	0.03587	0.02872	0.01443	-0.00529	-0.02501	-0.0393	-0.04645
-0.0431860779	0.03646	0.02926	0.01487	-0.00465	-0.02417	-0.03856	-0.04576
-0.0412709282	0.03673	0.02951	0.01508	-0.00435	-0.02378	-0.03821	-0.04543
-0.0392276712	0.03692	0.02971	0.0153	-0.00403	-0.02336	-0.03777	-0.04498
-0.0028504892	0.04041	0.03335	0.01923	-0.00029	-0.01981	-0.03393	-0.04099
-0.0014697871	0.04055	0.03349	0.01938	-0.00015	-0.01968	-0.03379	-0.04085
-0.0009575889	0.04059	0.03354	0.01944	-0.0001	-0.01964	-0.03374	-0.04079
0	0.04068	0.03363	0.01954	0	-0.01954	-0.03363	-0.04068
0.0009575889	0.04079	0.03374	0.01964	0.0001	-0.01944	-0.03354	-0.04059
0.0014697871	0.04085	0.03379	0.01968	0.00015	-0.01938	-0.03349	-0.04055
0.0028504892	0.04099	0.03393	0.01981	0.00029	-0.01923	-0.03335	-0.04041
0.0392276712	0.04498	0.03777	0.02336	0.00403	-0.0153	-0.02971	-0.03692
0.0412709282	0.04543	0.03821	0.02378	0.00435	-0.01508	-0.02951	-0.03673
0.0431860779	0.04576	0.03856	0.02417	0.00465	-0.01487	-0.02926	-0.03646
0.0472446666	0.04645	0.0393	0.02501	0.00529	-0.01443	-0.02872	-0.03587
0.0718134919	0.05124	0.04385	0.02908	0.00918	-0.01072	-0.02549	-0.03288
0.0763509989	0.05197	0.04459	0.02983	0.0099	-0.01003	-0.02479	-0.03217
0.0799921048	0.05275	0.04538	0.03064	0.01058	-0.00948	-0.02422	-0.03159
0.1160408333	0.06103	0.05337	0.03805	0.01737	-0.00331	-0.01863	-0.02629
0.117666433	0.06145	0.05374	0.03833	0.01768	-0.00297	-0.01838	-0.02609
0.1229610638	0.06255	0.05477	0.03922	0.01868	-0.00186	-0.01741	-0.02519
0.1320971643	0.06441	0.05652	0.04074	0.0204	0.00006	-0.01572	-0.02361
0.1543275975	0.07101	0.06283	0.04648	0.0256	0.00472	-0.01163	-0.01981
0.167939944	0.07513	0.06668	0.04979	0.02878	0.00777	-0.00912	-0.01757
0.1835562774	0.07905	0.07056	0.05359	0.03243	0.01127	-0.0057	-0.01419
0.1915394134	0.08131	0.07281	0.05581	0.03443	0.01305	-0.00395	-0.01245
0.2229954825	0.09055	0.08169	0.06397	0.04231	0.02065	0.00293	-0.00593
0.2298720798	0.09298	0.08404	0.06617	0.04424	0.02231	0.00444	-0.0045
0.2301548231	0.09309	0.08414	0.06625	0.04432	0.02239	0.0045	-0.00445
0.2314079695	0.09357	0.08457	0.06658	0.04467	0.02276	0.00477	-0.00423
0.2704736742	0.10717	0.09711	0.07698	0.05566	0.03434	0.01421	0.00415
0.285511431	0.11247	0.10194	0.08087	0.05989	0.03891	0.01784	0.00731
0.3099914191	0.11945	0.10815	0.08554	0.06595	0.04636	0.02375	0.01245
0.312312707	0.12001	0.10873	0.08616	0.06652	0.04688	0.02431	0.01303
0.3216606905	0.12227	0.11109	0.08872	0.06883	0.04894	0.02657	0.01539
0.3234025291	0.12262	0.11145	0.08911	0.06922	0.04933	0.02699	0.01582
0.3504830578	0.12893	0.11772	0.09529	0.0753	0.05531	0.03288	0.02167
0.3698178152	0.13284	0.12218	0.10086	0.07964	0.05842	0.0371	0.02644
0.3857753606	0.13322	0.12301	0.10259	0.08179	0.06099	0.04057	0.03036
0.3910462549	0.13374	0.12355	0.10317	0.0825	0.06183	0.04145	0.03126
0.4117633131	0.13584	0.12571	0.10544	0.0853	0.06516	0.04489	0.03476
0.4378734387	0.13846	0.1284	0.10828	0.08882	0.06936	0.04924	0.03918
0.4385471358	0.13853	0.12847	0.10835	0.08891	0.06947	0.04935	0.03929
0.4389311083	0.13857	0.12851	0.10839	0.08896	0.06953	0.04941	0.03935
0.4414757983	0.13883	0.12878	0.10868	0.08931	0.06994	0.04984	0.03979
                </tableData>
            </table>
        </function>
        <function name="aero/function/K"> <!-- aerodynamic quality or Lift to Drag ratio -->
            <quotient>                    
                  <sum>
                    <property>aero/force/Lift_alpha</property>
                    <property>aero/force/Lift_elevator</property>
                    <property>aero/force/Lift_alpha_ground</property>
                  </sum>
                  <sum>
                    <property>aero/force/Drag_basic</property>
                    <property>aero/force/Drag_gear</property>
                    <property>aero/force/Drag_beta</property>
                    <property>aero/force/Drag_rudder</property>
                    <property>aero/force/Drag_ailerons</property>
                    <property>aero/force/Drag_elevator</property>
                    <property>aero/force/Drag_ground</property>
                  </sum>
		    </quotient>
        </function>

<!--                 End of pre-calculations                   -->
<!--                 Starting to calculate actual forces       -->

        <axis name="LIFT" unit="LBS">
            <function name="aero/force/Lift_alpha">
                <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/force/Lift_elevator">
                <description>Lift due to Elevator Deflection</description>
                <product>
                    <quotient>
                        <property>aero/moment/Pitch_elevator</property>
                        <property>metrics/lh-ft</property>
                    </quotient>
                    <value>-1</value>
                </product>
            </function>
            <function name="aero/force/Lift_alpha_ground">
                <description>Lift due to alpha and ground effect</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/function/cy_delta_ground</property>
                    <table>
                        <independentVar>position/h-agl-ft</independentVar>
                        <tableData>
                          0             1           
                          27            0           
                        </tableData>
                    </table>
                </product>
            </function>
        </axis>
        <axis name="DRAG" unit="LBS">
            <function name="aero/force/Drag_basic">
                <description>Drag at zero lift</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/function/cx</property>
                </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>0.014</value>
                </product>
            </function>
            <function name="aero/force/Drag_beta">
                <description>Drag due to sideslip</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <table>
                        <independentVar>aero/beta-rad</independentVar>
                        <tableData>
                          -1.57         1.23        
                          -0.26         0.05        
                          -0.14         0.018       
                          -0.13         0.014       
                          -0.105        0.008       
                          -0.07         0.004       
                          0             0           
                          0.07          0.004       
                          0.105         0.008       
                          0.13          0.014       
                          0.14          0.018       
                          0.26          0.05        
                          1.57          1.23        
                        </tableData>
                    </table>
                </product>
            </function>
            <function name="aero/force/Drag_rudder">
                <description>Drag due to rudder deflection</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/rudder-pos-rad</property>
                    <property>fcs/rudder-pos-rad</property>
                    <value>0.075</value>
                </product>
            </function>
            <function name="aero/force/Drag_ailerons">
                <description>Drag due to ailerons deflection</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/right-aileron-pos-norm</property>
                    <property>fcs/right-aileron-pos-norm</property>
                    <value>0.01159</value>
                </product>
            </function>
            <function name="aero/force/Drag_elevator">
                <description>Drag due to Elevator Deflection</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/elevator-pos-rad</property>
                    <property>fcs/elevator-pos-rad</property>
                    <value>0.00774</value>
                </product>
            </function>
            <function name="aero/force/Drag_ground">
                <description>Drag reduction due to ground effect</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/function/cx_delta_ground</property>
                    <table>
                        <independentVar>position/h-agl-ft</independentVar>
                        <tableData>
                          0             1           
                          27            0           
                        </tableData>
                    </table>
                </product>
            </function>
        </axis>
        <axis name="SIDE" unit="LBS">
            <function name="aero/force/Side_beta">
                <description>Side force due to beta</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <sum>
                      <product>
                        <property>aero/beta-rad</property>
                        <value>-0.716</value>
                      </product>
                      <product>
                        <property>fcs/rudder-pos-rad</property>
                        <value>0.1145</value>
                      </product>
                    </sum>
                </product>
            </function>
        </axis>
        <axis name="ROLL" unit="LBS*FT">
            <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>-0.0722</value>
                    <!-- stall and spin (1), not implemented yet -->
                    <!--
                    <table> 
                      <independentVar lookup="row">aero/alpha-wing-rad</independentVar>
                      <tableData>
                        0.31     1
                        0.34    50
                      </tableData>
                  </table>
                  -->
                </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>-0.5</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>1</value> <!-- remains for possibility to sign change -->
                    <table>
                      <independentVar lookup="row">aero/alpha-wing-rad</independentVar>
                      <independentVar lookup="column">fcs/flap-pos-deg</independentVar>
                      <tableData>
                               0      38
                      0        0.07   0.33
                      0.087    0.15   0.47
                      0.175    0.21   0.52
                      0.227    0.23   0.51
                    </tableData>
                    </table>
                    <!-- stall and spin (2), not implemented yet -->
                    <!--
                    <table>
                      <independentVar lookup="row">aero/alpha-wing-rad</independentVar>
                      <independentVar lookup="column">velocities/r-aero-rad_sec</independentVar>
                      <tableData>
                               -0.15  -0.1   0    0.1   0.15
                      0.31     1      1     1    1     1
                      0.32     50     20    1    20    50
                    </tableData>
                  </table>
                  -->
                </product>
            </function>
            <function name="aero/moment/Roll_aileron_left">
                <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>0.075</value>
                </product>
            </function>
            <function name="aero/moment/Roll_aileron_right">
                <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/right-aileron-pos-rad</property>
                    <value>0.075</value>
                </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>
            <function name="aero/moment/Roll_anti_engine">
                <description>Reduce roll moment due to engines</description>
                <product>
                    <property>moments/l-prop-lbsft</property>
                    <value>-0.85</value> <!-- Idea - reduce moment according to gear ratio (-0.9175), but it seems to small -->
                </product>
            </function>
        </axis>
        <axis name="PITCH" unit="LBS*FT">
            <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/function/mz</property>
                </product>
            </function>
            <function name="aero/moment/Pitch_gear">
                <description>Pitch moment due to gear retraction</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                    <value>-0.025</value>
                    <property>gear/gear-pos-norm</property>
                </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>velocities/mach</independentVar>
                        <tableData>
                          0             -1.2          
                          2             -1.2       
                        </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>-22</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>-8</value>
                </product>
            </function>
        </axis>
        <axis name="YAW" unit="LBS*FT">
            <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_and_beta">
                <description>Yaw moment due to rudder and beta</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>aero/function/my</property>
                    <value>1</value>
                </product>
            </function>
            <function name="aero/moment/Yaw_aileron_left">
                <description>Adverse yaw</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <abs>
                      <property>fcs/left-aileron-pos-rad</property>
                    </abs>
                    <value>-0.004</value>
                </product>
            </function>
            <function name="aero/moment/Yaw_aileron_right">
                <description>Adverse yaw</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <abs>
                      <property>fcs/right-aileron-pos-rad</property>
                    </abs>
                    <value>0.004</value>
                </product>
            </function>
            <function name="aero/moment/Yaw_roll_rate">
                <description>Yaw 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>-1</value> <!-- remains for possibility to sign change -->
                    <table>
                      <independentVar lookup="row">aero/alpha-wing-rad</independentVar>
                      <independentVar lookup="column">fcs/flap-pos-deg</independentVar>
                      <tableData>
                               0       38
                      0        0.05   -0.02
                      0.056    0.00   -0.07
                      0.112   -0.03   -0.10
                      0.209   -0.07   -0.14
                    </tableData>
                    </table>
                </product>
            </function>
        </axis>
    </aerodynamics>

   <!-- <output name="JSBout.csv" type="CSV" rate="100">
        <simulation> OFF </simulation>
        <atmosphere> OFF </atmosphere>
        <massprops> OFF </massprops>
        <aerosurfaces> OFF </aerosurfaces>
        <rates> OFF </rates>
        <velocities> OFF </velocities>
        <forces> OFF </forces>
        <moments> OFF </moments>
        <position> OFF </position>
        <coefficients> OFF </coefficients>
        <ground_reactions> OFF </ground_reactions>
        <fcs> OFF </fcs>
        <propulsion> OFF </propulsion>
    </output> -->
</fdm_config>
