<?xml version="1.0"?>
<!--
 This file is part of FlightGear, the free flight simulator
 http://www.flightgear.org/

 Copyright (C) 2009 Torsten Dreyer, Torsten (at) t3r _dot_ de

 This program is free software; you can redistribute it and/or
 modify it under the terms of the GNU General Public License as
 published by the Free Software Foundation; either version 2 of the
 License, or (at your option) any later version.

 This program is distributed in the hope that it will be useful, but
 WITHOUT ANY WARRANTY; without even the implied warranty of
 MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE.  See the GNU
 General Public License for more details.
-->
<!-- 
    This is the JSBSim config file for a PA34-200T SenecaII.
    The aerodynamics sections was generated by datcom using
    as much real input as available.
    
    Changes from datcom.xml
    
    - function attribute NAME must be lowercase
    - missing function Delta_lift_due_to_flap_deflection in axis LIFT
    - missing function Lift_due_to_Elevator_Deflection in axis LIFT
-->
<?xml-stylesheet href="JSBSim.xsl" type="application/xml"?>
<fdm_config xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
    xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd" name="SenecaII"
    version="2.0" release="BETA">

    <fileheader>
        <author>Torsten Dreyer with a little help from DATCOM+</author>
        <filecreationdate>2006-01-16</filecreationdate>
        <description>Model for a PA34-200T Seneca II</description>
        <reference title="Seneca II JSBSim FlightModel"/>
    </fileheader>

    <!-- **********************************************************************
        METRICS
        ********************************************************************** -->
    <metrics>
        <wingarea unit="FT2"> 208.7000 </wingarea>
        <wingspan unit="FT"> 38.9060 </wingspan>
        <chord unit="FT"> 5.1800 </chord>
        <htailarea unit="FT2"> 37.1800 </htailarea>
        <htailarm unit="FT"> 15.1 </htailarm>
        <!--
            <htailarm unit="FT">         3.3575  </htailarm>
        -->
        <vtailarea unit="FT2"> 28.5957 </vtailarea>
        <vtailarm unit="FT"> 8.7165 </vtailarm>
        <!-- 
            the aerodynamic reference point, common point for 
            aerodynamic forces (lift and drag) 
        -->
        <location name="AERORP" unit="IN">
            <x> -49.5 </x>
            <y> 0 </y>
            <z> 45.4</z>
        </location>
        <!-- the eyepoint of the pilot (left or right eye?) -->
        <location name="EYEPOINT" unit="IN">
            <x>-45.3 </x>
            <y>-11.0 </y>
            <z> 69.0 </z>
        </location>
        <!-- the visual reference point of the 3d model -->
        <location name="VRP" unit="IN">
            <x> 0.0 </x>
            <y> 0.0 </y>
            <z> 0.0 </z>
        </location>
    </metrics>
    <!-- **********************************************************************
        MASS_BALANCE
        ********************************************************************** -->
    <mass_balance>
        <ixx unit="SLUG*FT2"> 5596 </ixx>
        <iyy unit="SLUG*FT2"> 5334 </iyy>
        <izz unit="SLUG*FT2"> 11945 </izz>
        <ixz unit="SLUG*FT2"> 0 </ixz>
        <emptywt unit="LBS"> 3300 </emptywt>
        <!-- the center of gravity -->
        <location name="CG" unit="IN">
            <x>-61.0 </x>
            <y> 0.0 </y>
            <z> 45.3 </z>
        </location>
        <pointmass name="Pilot">
            <weight unit="LBS"> 150.0 </weight>
            <location name="POINTMASS" unit="IN">
                <x> -51.5 </x>
                <y> -11 </y>
                <z> 50.5 </z>
            </location>
        </pointmass>
        <pointmass name="Co Pilot">
            <weight unit="LBS"> 150.0 </weight>
            <location name="POINTMASS" unit="IN">
                <x> -51.5 </x>
                <y> 11 </y>
                <z> 50.5 </z>
            </location>
        </pointmass>
        <pointmass name="Middle Left Pax">
            <weight unit="LBS"> 0.0 </weight>
            <location name="POINTMASS" unit="IN">
                <x> -20.0 </x>
                <y> -11 </y>
                <z> 50.5 </z>
            </location>
        </pointmass>
        <pointmass name="Middle Right Pax">
            <weight unit="LBS"> 0.0 </weight>
            <location name="POINTMASS" unit="IN">
                <x> -20.0 </x>
                <y> 11 </y>
                <z> 50.5 </z>
            </location>
        </pointmass>
        <pointmass name="Rear Left Pax">
            <weight unit="LBS"> 0.0 </weight>
            <location name="POINTMASS" unit="IN">
                <x> 9.5  </x>
                <y> -11 </y>
                <z> 50.5 </z>
            </location>
        </pointmass>
        <pointmass name="Rear Right Pax">
            <weight unit="LBS"> 0.0 </weight>
            <location name="POINTMASS" unit="IN">
                <x> 9.5 </x>
                <y> 11 </y>
                <z> 50.5 </z>
            </location>
        </pointmass>
        <pointmass name="Nose Baggage">
            <weight unit="LBS"> 0.0 </weight>
            <location name="POINTMASS" unit="IN">
                <x> -123.6 </x>
                <y> 0 </y>
                <z> 35.3 </z>
            </location>
        </pointmass>
        <pointmass name="Aft Baggage">
            <weight unit="LBS"> 20.0 </weight>
            <location name="POINTMASS" unit="IN">
                <x> 39.3 </x>
                <y> 0 </y>
                <z> 35.3 </z>
            </location>
        </pointmass>
    </mass_balance>
    <!-- **********************************************************************
        UNDERCARRIAGE
        ********************************************************************** -->
    <ground_reactions>
        <contact type="BOGEY" name="NOSE">
            <location unit="IN">
                <x>-116.5</x>
                <y>0</y>
                <z>-1.5</z>
            </location>
            <static_friction> 0.82 </static_friction>
            <dynamic_friction> 0.5 </dynamic_friction>
            <rolling_friction> 0.03 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 5400 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 1600 </damping_coeff>
            <!-- todo: check this -->
            <max_steer unit="DEG"> 10 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable>1</retractable>
        </contact>
        <contact type="BOGEY" name="LEFT_MAIN">
            <location unit="IN">
                <x>-32.8</x>
                <y>-59.1</y>
                <z>-1.5</z>
            </location>
            <static_friction> 1.95</static_friction>
            <dynamic_friction> 0.7 </dynamic_friction>
            <rolling_friction> 0.03 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 5400 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 1600 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> LEFT </brake_group>
            <retractable>1</retractable>
        </contact>
        <contact type="BOGEY" name="RIGHT_MAIN">
            <location unit="IN">
                <x>-32.8</x>
                <y>59.1</y>
                <z>-1.5</z>
            </location>
            <static_friction> 1.95</static_friction>
            <dynamic_friction> 0.7 </dynamic_friction>
            <rolling_friction> 0.03 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 5400 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 1600 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> RIGHT </brake_group>
            <retractable>1</retractable>
        </contact>
        <contact type="STRUCTURE" name="TAIL_SKID">
            <location unit="IN">
                <x> 154 </x>
                <y> 0 </y>
                <z>42.76 </z>
            </location>
            <static_friction> 0.2 </static_friction>
            <dynamic_friction> 0.2 </dynamic_friction>
            <spring_coeff unit="LBS/FT"> 20000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 1000 </damping_coeff>
        </contact>
        <contact type="STRUCTURE" name="NOSE">
            <location unit="IN">
                <x> -164.7 </x>
                <y> 0 </y>
                <z> 43.2 </z>
            </location>
            <static_friction> 0.2 </static_friction>
            <dynamic_friction> 0.2 </dynamic_friction>
            <spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
        </contact>
        <contact type="STRUCTURE" name="LEFT_WING">
            <location unit="IN">
                <x> -39.7 </x>
                <y> -229.1 </y>
                <z> 55.2 </z>
            </location>
            <static_friction> 0.2 </static_friction>
            <dynamic_friction> 0.2 </dynamic_friction>
            <spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
        </contact>
        <contact type="STRUCTURE" name="RIGHT_WING">
            <location unit="IN">
                <x> -39.7 </x>
                <y> 229.1 </y>
                <z> 55.2 </z>
            </location>
            <static_friction> 0.2 </static_friction>
            <dynamic_friction> 0.2 </dynamic_friction>
            <spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
        </contact>
        <contact type="STRUCTURE" name="VERTICAL_TAIL">
            <location unit="IN">
                <x> 145.7 </x>
                <y> 0.0 </y>
                <z> 121.2 </z>
            </location>
            <static_friction> 0.2 </static_friction>
            <dynamic_friction> 0.2 </dynamic_friction>
            <spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
        </contact>
        <contact type="STRUCTURE" name="CABIN_TOP">
            <location unit="IN">
                <x> -53.9 </x>
                <y> 0.0 </y>
                <z> 77.6 </z>
            </location>
            <static_friction> 0.2 </static_friction>
            <dynamic_friction> 0.2 </dynamic_friction>
            <spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
        </contact>
    </ground_reactions>
    <!-- **********************************************************************
        PROPULSION
        ********************************************************************** -->
    <propulsion>
        <!-- left engine -->
        <engine file="tsio360eb">
            <location unit="IN">
                <x>-107.9 </x>
                <y> -71.6 </y>
                <z> 51.6 </z>
            </location>
            <orient unit="DEG">
                <roll> 0.00 </roll>
                <pitch> 0.00 </pitch>
                <yaw> 0.00 </yaw>
            </orient>
            <feed>2</feed>
            <thruster file="bhc-c2yf-2">
                <!-- turning clockwise viewed from cockpit -->
                <location unit="IN">
                    <x>-107.9 </x>
                    <y> -71.6 </y>
                    <z> 51.6 </z>
                </location>
                <orient unit="DEG">
                    <roll> 0.00 </roll>
                    <pitch> 0.00 </pitch>
                    <yaw> 0.00 </yaw>
                </orient>
                <sense>1</sense>
            </thruster>
        </engine>
        <!-- right engine -->
        <engine file="tsio360eb">
            <location unit="IN">
                <x>-107.9 </x>
                <y> 71.6 </y>
                <z> 51.6 </z>
            </location>
            <orient unit="DEG">
                <roll> 0.00 </roll>
                <pitch> 0.00 </pitch>
                <yaw> 0.00 </yaw>
            </orient>
            <feed>3</feed>
            <thruster file="bhc-c2yf-2">
                <!-- turning counterclockwise viewed from cockpit -->
                <location unit="IN">
                    <x>-107.9 </x>
                    <y> 71.6 </y>
                    <z> 51.6 </z>
                </location>
                <orient unit="DEG">
                    <roll> 0.00 </roll>
                    <pitch> 0.00 </pitch>
                    <yaw> 0.00 </yaw>
                </orient>
                <sense>-1</sense>
            </thruster>
        </engine>
        <!-- 
            two tanks, one each wing
            64gal/61.5 usable each side are longrange tanks
        -->
        <tank type="FUEL">
            <!-- Tank Number 0 (left wing) -->
            <location unit="IN">
                <x>-31.5</x>
                <y>-75.4</y>
                <z>34.3</z>
            </location>
            <radius unit="IN">13.3</radius>
            <capacity unit="LBS">384</capacity>
            <contents unit="LBS">294</contents>
            <type>AVGAS</type>
            <priority>0</priority>
        </tank>
        <tank type="FUEL">
            <!-- Tank Number 1 (right wing) -->
            <location unit="IN">
                <x>-31.5</x>
                <y>75.4</y>
                <z>34.3</z>
            </location>
            <radius unit="IN">13.3</radius>
            <capacity unit="LBS">384</capacity>
            <contents unit="LBS">294</contents>
            <type>AVGAS</type>
            <priority>0</priority>
        </tank>
        <tank type="FUEL">
            <!-- Pseudo Tank Number 2 (left wing) -->
            <location unit="IN">
                <x>-31.5</x>
                <y>-75.4</y>
                <z>34.3</z>
            </location>
            <capacity unit="LBS">0.1</capacity>
            <contents unit="LBS">0.0</contents>
            <type>AVGAS</type>
        </tank>
        <tank type="FUEL">
            <!-- Pseudo Tank Number 3 (right wing) -->
            <location unit="IN">
                <x>-31.5</x>
                <y>75.4</y>
                <z>34.3</z>
            </location>
            <capacity unit="LBS">0.1</capacity>
            <contents unit="LBS">0.0</contents>
            <type>AVGAS</type>
        </tank>
    </propulsion>
    <!-- **********************************************************************
        FLIGHT CONTROLS
        ********************************************************************** -->
    <flight_control name="SenecaII">
        <!--       
            Elevator
        -->
        <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>
                <output>fcs/elevator-pos-norm</output>
            </summer>

            <aerosurface_scale name="Elevator Control">
                <input>fcs/pitch-trim-sum</input>
                <gain>0.01745</gain>
                <range>
                    <min>-28</min>
                    <max>23</max>
                </range>
                <output>fcs/elevator-pos-rad</output>
            </aerosurface_scale>
        </channel>
        <!--   
            Aileron
        -->
        <channel name="Roll">
            <summer name="Roll Trim Sum">
                <input>fcs/aileron-cmd-norm</input>
                <input>fcs/roll-trim-cmd-norm</input>
                <clipto>
                    <min>-1</min>
                    <max>1</max>
                </clipto>
            </summer>
            <aerosurface_scale name="Left Aileron Control">
                <input>fcs/roll-trim-sum</input>
                <gain>0.01745</gain>
                <range>
                    <min>-30</min>
                    <max>15</max>
                </range>
                <output>fcs/left-aileron-pos-rad</output>
            </aerosurface_scale>
            <aerosurface_scale name="Left Aileron Norm">
                <input>fcs/roll-trim-sum</input>
                <range>
                    <min>-1</min>
                    <max>1</max>
                </range>
                <output>fcs/left-aileron-pos-norm</output>
            </aerosurface_scale>
            <aerosurface_scale name="Right Aileron Control">
                <input>-fcs/roll-trim-sum</input>
                <gain>0.01745</gain>
                <range>
                    <min>-30</min>
                    <max>15</max>
                </range>
                <output>fcs/right-aileron-pos-rad</output>
            </aerosurface_scale>
            <aerosurface_scale name="Right Aileron Norm">
                <input>-fcs/roll-trim-sum</input>
                <range>
                    <min>-1</min>
                    <max>1</max>
                </range>
                <output>fcs/right-aileron-pos-norm</output>
            </aerosurface_scale>
        </channel>
        <!--
            Rudder
        -->
        <channel name="Yaw">
            <summer name="Yaw Trim Sum">
                <input>fcs/rudder-cmd-norm</input>
                <input>fcs/yaw-trim-cmd-norm</input>
                <clipto>
                    <min>-1</min>
                    <max>1</max>
                </clipto>
                <output>fcs/rudder-pos-norm</output>
            </summer>
            <aerosurface_scale name="Rudder Control">
                <input>fcs/yaw-trim-sum</input>
                <gain>0.01745</gain>
                <range>
                    <min>-27</min>
                    <max>27</max>
                </range>
                <output>fcs/rudder-pos-rad</output>
            </aerosurface_scale>
        </channel>
        <!--
            Flaps
        -->
        <channel name="Flaps">
<!--
            <kinematic name="Flaps Control">
                <input>fcs/flap-cmd-norm</input>
                <traverse>
                    <setting>
                        <position>0</position>
                        <time>0</time>
                    </setting>
                    <setting>
                        <position>1</position>
                        <time>1</time>
                    </setting>
                </traverse>
                <output>fcs/flap-pos-norm</output>
            </kinematic>
            <aerosurface_scale name="Flap Pos Degi">
                <input>fcs/flap-pos-norm</input>
                <range>
                    <min>0</min>
                    <max>40</max>
                </range>
            </aerosurface_scale>
            <aerosurface_scale name="Flap Pos Rad">
                <input>fcs/flap-pos-norm</input>
                <gain>0.01745</gain>
                <range>
                    <min>0</min>
                    <max>40</max>
                </range>
            </aerosurface_scale>
-->
            <kinematic name="Flaps Control">
                <input>fcs/flap-cmd-norm</input>
                <traverse>
                    <setting>
                        <position>0</position>
                        <time>0</time>
                    </setting>
                    <setting>
                        <position>10</position>
                        <time>1</time>
                    </setting>
                    <setting>
                        <position>25</position>
                        <time>1</time>
                    </setting>
                    <setting>
                        <position>40</position>
                        <time>1</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>40</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>
        <!--
            Gear
        -->
        <property value="0">gear/gear-cmd-emergency-norm</property>
        <property value="1">gear/serviceable</property>
        <channel name="Landing Gear">
            <!-- force gear down on ground. Squad switch is on left main gear -->
            <!-- from here on 0 means "gear down" and 1 means "gear up" 
                 to have gear down on program start. This is required by the current
                 actuator implementation which does not allow the setting of an
                 initial value for the output, but defaults to 0 (zero) :-(
              -->
            <switch name="gear switch">
              <default value="1"/>
              <test logic="OR" value="0">
                gear/unit[1]/WOW == 1
                gear/gear-cmd-norm == 1
              </test>
            </switch>

            <switch name="gear target position">
              <default value="fcs/gear-target-position"/>
              <test logic="AND" value="fcs/gear-switch">
                gear/serviceable == 1
              </test>
            </switch>

            <!-- create a input property fcs/gear-emergency-extend -->
            <switch name="gear emergency extend">
              <default value="1"/>
              <test value="0">
                gear/gear-cmd-emergency-norm == 1
              </test>
            </switch>

            <!-- normal actuators driven by gear switch -->
            <actuator name="gear/unit[0]/actuator">
                <input>fcs/gear-target-position</input>
                <rate_limit>0.1</rate_limit>
                <output>gear/unit[0]/actuator-pos-inverted</output>
                <clipto>
                  <min>-1</min>
                  <max>0</max>
                </clipto>
                <bias>-1.0</bias>
            </actuator>

            <pure_gain name="gear/unit[0]/target-actuator-pos-norm">
                <input>gear/unit[0]/actuator-pos-inverted</input>
                <gain>-1.0</gain>
            </pure_gain>

            <!-- nose gear does not fully retract above 125kias
                 (max gear retract speed is 109kias) -->
            <switch name="gear/unit[0]/actuator-pos-norm">
              <default value="gear/unit[0]/target-actuator-pos-norm"/>
              <test value="gear/unit[0]/actuator-pos-norm">
                fcs/gear-switch == 0
                gear/unit[0]/target-actuator-pos-norm lt 0.8
                gear/unit[0]/target-actuator-pos-norm gt 0.1
                velocities/ve-kts gt 125
              </test>
            </switch>

            <actuator name="gear/unit[1]/actuator">
                <input>fcs/gear-target-position</input>
                <rate_limit>0.13</rate_limit>
                <output>gear/unit[1]/actuator-pos-inverted</output>
                <clipto>
                  <min>-1</min>
                  <max>0</max>
                </clipto>
                <bias>-1.0</bias>
            </actuator>

            <pure_gain name="gear/unit[1]/actuator-pos-norm">
                <input>gear/unit[1]/actuator-pos-inverted</input>
                <gain>-1.0</gain>
            </pure_gain>

            <actuator name="gear/unit[2]/actuator">
                <input>fcs/gear-target-position</input>
                <rate_limit>0.15</rate_limit>
                <output>gear/unit[2]/actuator-pos-inverted</output>
                <clipto>
                  <min>-1</min>
                  <max>0</max>
                </clipto>
                <bias>-1.0</bias>
            </actuator>

            <pure_gain name="gear/unit[2]/actuator-pos-norm">
                <input>gear/unit[2]/actuator-pos-inverted</input>
                <gain>-1.0</gain>
            </pure_gain>

            <!-- "gravity" actuator for emergency extension -->
            <actuator name="Gear Emergency Actuator">
                <input>fcs/gear-emergency-extend</input>
                <rate_limit>0.2</rate_limit>
                <output>gear/emergency-pos-inverted</output>
                <clipto>
                  <min>-1</min>
                  <max>0</max>
                </clipto>
                <bias>-1.0</bias>
            </actuator>

            <pure_gain name="gear/emergency-pos-norm">
                <input>gear/emergency-pos-inverted</input>
                <gain>-1.0</gain>
            </pure_gain>

            <!-- now add up the gear positions -->
            <summer name="Nose Gear Sum">
                <input>gear/emergency-pos-norm</input>
                <input>gear/unit[0]/actuator-pos-norm</input>
                <clipto>
                    <min>0</min>
                    <max>1</max>
                </clipto>
                <output>gear/unit[0]/pos-norm</output>
            </summer>
            <summer name="Left Gear Sum">
                <input>gear/emergency-pos-norm</input>
                <input>gear/unit[1]/actuator-pos-norm</input>
                <clipto>
                    <min>0</min>
                    <max>1</max>
                </clipto>
                <output>gear/unit[1]/pos-norm</output>
            </summer>
            <summer name="Right Gear Sum">
                <input>gear/emergency-pos-norm</input>
                <input>gear/unit[2]/actuator-pos-norm</input>
                <clipto>
                    <min>0</min>
                    <max>1</max>
                </clipto>
                <output>gear/unit[2]/pos-norm</output>
            </summer>

        </channel>
        <!--
            Cowl Flaps 
        -->
        <channel name="Cowl Flaps">
            <kinematic name="Left Cowl Flaps">
                <input>/controls/engines/engine[0]/cowl-flaps-norm</input>
                <traverse>
                    <setting>
                        <position>0</position>
                        <time>0</time>
                    </setting>
                    <setting>
                        <position>1</position>
                        <time>1</time>
                    </setting>
                </traverse>
                <output>propulsion/engine[0]/cowl-flaps-norm</output>
            </kinematic>
            <aerosurface_scale name="Left Cooling Factor">
                <input>propulsion/engine[0]/cowl-flaps-norm</input>
                <gain>1.0</gain>
                <zero_centered>false</zero_centered>
                <domain>
                  <min>0</min>
                  <max>1</max>
                </domain>
                <range>
                    <min>0.48</min>
                    <max>0.75</max>
                </range>
                <output>propulsion/engine[0]/cooling-factor</output>
            </aerosurface_scale>
            <kinematic name="Right Cowl Flaps">
                <input>/controls/engines/engine[1]/cowl-flaps-norm</input>
                <traverse>
                    <setting>
                        <position>0</position>
                        <time>0</time>
                    </setting>
                    <setting>
                        <position>1</position>
                        <time>1</time>
                    </setting>
                </traverse>
                <output>propulsion/engine[1]/cowl-flaps-norm</output>
            </kinematic>
            <aerosurface_scale name="Right Cooling Factor">
                <input>propulsion/engine[1]/cowl-flaps-norm</input>
                <gain>1.0</gain>
                <zero_centered>false</zero_centered>
                <domain>
                  <min>0</min>
                  <max>1</max>
                </domain>
                <range>
                    <min>0.48</min>
                    <max>0.75</max>
                </range>
                <output>propulsion/engine[1]/cooling-factor</output>
            </aerosurface_scale>
        </channel>
    </flight_control>

    <system file="property-helpers"/>
    <system file="prop-governor"/>

    <!-- **********************************************************************
        AERODYNAMICS
        ********************************************************************** -->
    <aerodynamics>
        <property value="0.0">ice/wing</property>
        <alphalimits unit="DEG">
            <min>-5.0</min>
            <max>14.0</max>
        </alphalimits>

        <hysteresis_limits unit="DEG">
            <min> 5.0</min>
            <max>20.0</max>
        </hysteresis_limits>

        <!-- ************************************** 
            ASSUMPTIONS AND LIMITATIONS
            
            There is no interaction between deflected surfaces modeled
            so there is no change in elevator effects with the flaps
            deflected, for example.
            
            Terms known to be missing from DATCOM:
            Power effects
            Ground effects
            Cyr, CyDr, Cyda, ClDr, Cndr
            
            ************************************** -->

        <!-- don't use ground effect for now -->
        <function name="aero/function/ground-effect-factor-lift">
            <description>Change in lift due to ground effect factor.</description>
            <!--
            <table>
                <independentVar>aero/h_b-mac-ft</independentVar>
                <tableData> 0.0 1.203 0.1 1.127 0.15 1.090 0.2 1.073 0.3 1.046 0.4 1.055 0.5 1.019
                    0.6 1.013 0.7 1.008 0.8 1.006 0.9 1.003 1.0 1.002 1.1 1.0 </tableData>
            </table>
            -->
            <sum>
                <value>1</value>
            </sum>
        </function>

        <function name="aero/function/ground-effect-factor-drag">
            <description>Change in drag due to ground effect</description>
            <!--
            <table>
                <independentVar>aero/h_b-mac-ft</independentVar>
                <tableData> 0.0 0.480 0.1 0.515 0.15 0.629 0.2 0.709 0.3 0.815 0.4 0.882 0.5 0.928
                    0.6 0.962 0.7 0.988 0.8 1.0 0.9 1.0 1.0 1.0 1.1 1.0 </tableData>
            </table>
            -->
            <sum>
                <value>1</value>
            </sum>
        </function>

        <!-- ********************************************************************** -->
        <axis name="LIFT">
            <function name="aero/coefficient/CLwbh">
                <description>
                    Lift due to alpha
                    Increase in CL decreases Period and damping,Dutch Roll damping.
                    CL is low for landing
                </description>
                <product>
                    <property>aero/function/ground-effect-factor-lift</property>
                    <property>aero/qbar-area</property>
                    <table>
                        <independentVar>aero/alpha-rad</independentVar>
                        <tableData>
                            -0.1396 -0.3311
                            -0.1047 -0.1556
                            -0.0698 0.0181
                            -0.0349 0.1954
                            0.0000 0.3791
                            0.0349 0.5681
                            0.0698 0.7608
                            0.1047 0.9581
                            0.1396 1.1345
                            0.1745 1.2837
                            0.2094 1.4059
                            0.2443 1.4945
                            0.2618 1.5090
                            0.2793 1.5027
                            0.2827 1.5009
                            0.2862 1.4963
                            0.2897 1.4520
                            0.2932 1.4086
                            0.2967 1.3652
                            0.3002 1.3326
                        </tableData>
                    </table>
                </product>
            </function>

            <function name="aero/coefficient/CLDf">
                <description>Delta_lift_due_to_flap_deflection</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/function/ground-effect-factor-lift</property>
                    <table>
                        <independentVar>fcs/flap-pos-deg</independentVar>
                        <tableData>
                            0    0.0
                            10  0.05
                            25  0.13
                            40  0.21
                        </tableData>
                    </table>
                </product>
            </function>
            <!--
            <function name="aero/coefficient/CLDe">
              <description>Lift_due_to_Elevator_Deflection</description>
              <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>fcs/elevator-pos-rad</property>
                <value>0.8100</value>
              </product>
            </function>
            -->
            <function name="aero/coefficient/CLq">
                <description>
                    Basic Lift Coefficient due to pitch rate(per radian)
                </description>
                <product>
                    <property>aero/qbar-area</property>
                    <!-- added manually -->
                    <property>velocities/q-rad_sec</property>
                    <property>aero/ci2vel</property>
                    <!-- end added -->
                    <table>
                        <independentVar>aero/alpha-rad</independentVar>
                        <tableData>
                            <!-- using PA28 data instead -->
                            -0.1750   10.6900
                            -0.1400   2.3540
                            -0.1050   2.4200
                            -0.0700   2.5400
                            -0.0350   2.6670
                            0.0000    2.6940
                            0.0350    2.6110
                            0.0700    2.5380
                            0.1050    2.4310
                            0.1400    2.1760
                            0.1750    1.7560
                            0.2090    1.3520
                            0.2440    0.9840
                            0.2790    0.4320
                            0.3140    -0.0930
                            0.3490    -0.2710
                        </tableData>
                    </table>
                </product>
            </function>

            <function name="aero/coefficient/CLad">
                <description>
                    Basic Lift Coefficient due to AOA rate(per radian)
                    Important contributor to Short-Period damping
                    For low Cla, aircraft must land at high alpha
                </description>
                <product>
                    <property>aero/qbar-area</property>
                    <!-- added manually -->
                    <property>aero/alphadot-rad_sec</property>
                    <property>aero/ci2vel</property>
                    <!-- end added -->
                    <table>
                        <independentVar>aero/alpha-rad</independentVar>
                        <tableData>
                            -.1396         2.920    
                            -.1047         2.931    
                            -.6981E-01     2.995    
                            -.3491E-01     3.088    
                            .000         3.158    
                            .3491E-01     3.172    
                            .5236E-01     3.159    
                            .6981E-01     3.150    
                            .8727E-01     3.110    
                            .1047         3.018    
                            .1222         2.792    
                            .1396         2.454    
                            .1571         2.237    
                            .1745         2.080    
                            .1920         1.862    
                            .2094         1.589    
                            .2443         .4655    
                            .2793        -2.190    
                            .3142        -4.362    
                        </tableData>
                    </table>
                </product>
            </function>

            <function name="aero/coefficient/CLicew">
                <description>Lift_decrease_due_to_ice_on_wing</description>
                <product>
                    <property>aero/qbar-area</property>
                    <table>
                        <independentVar>ice/wing</independentVar>
                        <tableData>
                            0.0      0
                            0.5      -0.1
                            1.0      -0.3
                            2.0      -1.5
                        </tableData>
                    </table>
                </product>
            </function>

        </axis>
        <!-- ********************************************************************** -->
        <axis name="DRAG">
            <function name="aero/coefficient/CD">
                <description>
                    Basic Drag Coefficient
                    Sense: Always positive.
                    Main contributor to Phugoid damping: Greater Cd, Better damping
                </description>
                <product>
                    <property>aero/function/ground-effect-factor-drag</property>
                    <property>aero/qbar-area</property>
                    <table>
                        <independentVar>aero/alpha-rad</independentVar>
                        <tableData>
                            -0.1396 0.036
                            -0.1047 0.028
                            -0.0698 0.025
                            -0.0349 0.027
                            0.0000 0.036
                            0.0349 0.052
                            0.0698 0.075
                            0.1047 0.105
                            0.1396 0.136
                            0.1745 0.169
                            0.2094 0.198
                            0.2443 0.226
                            0.2618 0.229
                            0.2793 0.234
                            0.2827 0.225
                            0.2862 0.217
                            0.2897 0.209
                            0.2932 0.201
                            0.2967 0.195
                            0.3002 0.192
                        </tableData>
                    </table>
                </product>
            </function>

            <function name="aero/coefficient/CDDf">
                <description>Delta_drag_due_to_flap_deflection</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/function/ground-effect-factor-drag</property>
                    <table>
                        <independentVar>fcs/flap-pos-deg</independentVar>
                        <tableData>
                            0.0000    0.0000
                            10.0000   0.00497
                            20.0000   0.01455
                            40.0000   0.05857
                        </tableData>
                    </table>
                </product>
            </function>

            <function name="aero/coefficient/CDi">
                <description>
                    AILERONS: Piper PA34-200T Seneca-II Aircraft                               
                    Induced drag due to flap deflection
                </description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/function/ground-effect-factor-drag</property>
                    <table>
                        <independentVar lookup="row">aero/alpha-rad</independentVar>
                        <independentVar lookup="column">fcs/flap-pos-deg</independentVar>
                        <tableData>
                              0 10 20 40
                            -0.1396  -0.0000 -0.0037 -0.0026 0.0014
                            -0.1047  -0.0000 -0.0019 0.0017 0.0071
                            -0.0698  -0.0000 -0.0001 0.0059 0.0129
                            -0.0349  -0.0000 0.0017 0.0102 0.0186
                             0.0000  0.0000 0.0036 0.0145 0.0244
                             0.0349  0.0000 0.0054 0.0188 0.0301
                             0.0698  0.0000 0.0072 0.0231 0.0358
                             0.1047  0.0000 0.0090 0.0273 0.0416
                             0.1396  0.0000 0.0108 0.0316 0.0473
                             0.1745  0.0000 0.0126 0.0359 0.0531
                             0.2094  0.0000 0.0145 0.0402 0.0588
                             0.2443  0.0000 0.0163 0.0444 0.0646
                             0.2618  0.0000 0.0172 0.0466 0.0674
                             0.2793  0.0000 0.0181 0.0487 0.0703
                             0.2827  0.0000 0.0183 0.0491 0.0709
                             0.2862  0.0000 0.0185 0.0496 0.0714
                             0.2897  0.0000 0.0186 0.0500 0.0720
                             0.2932  0.0000 0.0188 0.0504 0.0726
                             0.2967  0.0000 0.0190 0.0509 0.0732
                             0.3002  0.0000 0.0192 0.0513 0.0737
                        </tableData>
                    </table>
                </product>
            </function>

            <function name="aero/coefficient/CDgear">
                <description>Drag_due_to_landing_gear</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/function/ground-effect-factor-drag</property>
                    <product>
                      <sum>
                        <property>gear/unit[0]/pos-norm</property>
                        <property>gear/unit[1]/pos-norm</property>
                        <property>gear/unit[2]/pos-norm</property>
                      </sum>
                      <value>0.33</value>
                    </product>
                    <value>0.009</value>
                </product>
            </function>

            <function name="aero/coefficient/CDcowl">
                <description>Drag_due_to_cowl_flaps</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/function/ground-effect-factor-drag</property>
                    <product> <!-- (left+right)/2 -->
                      <sum>
                        <property>propulsion/engine[0]/cowl-flaps-norm</property>
                        <property>propulsion/engine[1]/cowl-flaps-norm</property>
                      </sum>
                      <value>0.5</value>
                    </product>
                    <value>0.0082</value>
                </product>
            </function>

            <function name="aero/coefficient/CDicew">
                <description>Drag_due_to_ice_on_wing</description>
                <product>
                    <property>aero/qbar-area</property>
                    <table>
                        <independentVar>ice/wing</independentVar>
                        <tableData>
                            0.0      0
                            0.5      0.004
                            1.0      0.010
                            2.0      0.100
                        </tableData>
                    </table>
                </product>
            </function>

            <function name="aero/coefficient/CDbeta">
                <description>Drag_due_to_sideslip</description>
                <product>
                    <property>aero/qbar-area</property>
                    <property>aero/mag-beta-rad</property>
                    <value>0.1700</value>
                </product>
            </function>


        </axis>
        <!-- ********************************************************************** -->
        <axis name="SIDE">


            <function name="aero/coefficient/Cyb">
                <description>
                    Side Force coefficient due to Sideslip(per radian)
                    Contributes to damping of Dutch Roll mode
                </description>
                <product>
                    <property>aero/qbar-area</property>
                    <property>aero/beta-rad</property>
                    <value>-0.5661</value>
                </product>
            </function>

            <function name="aero/coefficient/Cyp">
                <description>
                    Side Force Coefficient due to Roll Rate(per radian)
                </description>
                <product>
                    <property>aero/qbar-area</property>
                    <property>velocities/p-aero-rad_sec</property>
                    <table>
                        <independentVar>aero/alpha-rad</independentVar>
                        <tableData>
                            -.1396        -.2470    
                            -.1047        -.2052    
                            -.6981E-01    -.1637    
                            -.3491E-01    -.1207    
                            .000        -.7658E-01
                            .3491E-01    -.3150E-01
                            .5236E-01    -.8672E-02
                            .6981E-01     .1432E-01
                            .8727E-01     .3745E-01
                            .1047         .6154E-01
                            .1222         .8543E-01
                            .1396         .1070    
                            .1571         .1271    
                            .1745         .1462    
                            .1920         .1641    
                            .2094         .1809    
                            .2443         .2180    
                            .2793         .1374    
                            .3142         .7334E-01
                        </tableData>
                    </table>
                </product>
            </function>


            <!-- *************************
                Not calculated by DATCOM+
                ************************* -->

            <function name="aero/coefficient/Cyr">
                <description>
                    Side Force due to Yaw Rate(DATCOM does not calculate)
                    Effect is small
                </description>
                <product>
                    <property>velocities/r-aero-rad_sec</property>
                    <value>    .000    </value>
                </product>
            </function>


            <!-- *************************
                Not calculated by DATCOM+
                ************************* -->

            <function name="aero/coefficient/CyDr">
                <description>
                    Side Force due to rudder(DATCOM does not calculate)
                </description>
                <product>
                    <property>fcs/rudder-pos-rad</property>
                    <value>    .000    </value>
                </product>
            </function>


            <!-- *************************
                Not calculated by DATCOM+
                ************************* -->

            <function name="aero/coefficient/CyDa">
                <description>
                    Side Force due to aileron(DATCOM does not calculate)
                    Usually neglected
                </description>
                <product>
                    <property>fcs/left-aileron-pos-rad</property>
                    <value>    .000    </value>
                </product>
            </function>

        </axis>
        <!-- ********************************************************************** -->
        <axis name="ROLL">


            <function name="aero/coefficient/Clb">
                <description>
                    Roll Moment coefficient due to Beta(per radian)
                    Decrease of Clb to small negative value improves Dutch Roll Damping
                    High Positive value leads to excessive spiral instability
                </description>
                <product>
                    <property>aero/qbar-area</property>
                    <property>aero/beta-rad</property>
                    <table>
                        <independentVar>aero/alpha-rad</independentVar>
                        <tableData>
                            -.1396        -.5399E-01
                            -.1047        -.7348E-01
                            -.6981E-01    -.9225E-01
                            -.3491E-01    -.1102    
                            .000        -.1285    
                            .3491E-01    -.1476    
                            .5236E-01    -.1573    
                            .6981E-01    -.1673    
                            .8727E-01    -.1774    
                            .1047        -.1877    
                            .1222        -.1982    
                            .1396        -.2087    
                            .1571        -.2193    
                            .1745        -.2289    
                            .1920        -.2371    
                            .2094        -.2443    
                            .2443        -.2555    
                            .2793        -.2625    
                            .3142        -.2592    
                        </tableData>
                    </table>
                </product>
            </function>

            <function name="aero/coefficient/Clp">
                <description>
                    Roll Moment coefficient due to roll rate(per radian)
                    Clp alone determines damping-in-roll characteristics
                </description>
                <product>
                    <property>aero/qbar-area</property>
                    <property>metrics/bw-ft</property>
                    <property>aero/bi2vel</property>
                    <property>velocities/p-aero-rad_sec</property>
                    <table>
                        <independentVar>aero/alpha-rad</independentVar>
                        <tableData>
                            -.1396        -.5384    
                            -.1047        -.5169    
                            -.6981E-01    -.4975    
                            -.3491E-01    -.4961    
                            .000        -.5123    
                            .3491E-01    -.5285    
                            .5236E-01    -.5353    
                            .6981E-01    -.5410    
                            .8727E-01    -.5457    
                            .1047        -.5495    
                            .1222        -.5523    
                            .1396        -.5541    
                            .1571        -.5169    
                            .1745        -.4502    
                            .1920        -.4024    
                            .2094        -.3615    
                            .2443        -.2671    
                            .2793        -.8737E-01
                            .3142         .1723    
                        </tableData>
                    </table>
                </product>
            </function>

            <function name="aero/coefficient/Clr">
                <description>
                    Roll Moment coefficient due to yaw rate(per radian)
                    Considerable effect on Spiral mode. Large 
                    positive values leads to strong sprial instability.
                </description>
                <product>
                    <property>aero/qbar-area</property>
                    <property>metrics/bw-ft</property>
                    <property>aero/bi2vel</property>
                    <property>velocities/r-aero-rad_sec</property>
                    <table>
                        <independentVar>aero/alpha-rad</independentVar>
                        <tableData>
                            -.1396        -.9274E-01
                            -.1047        -.4843E-01
                            -.6981E-01    -.5939E-02
                            -.3491E-01     .3496E-01
                            .000         .7723E-01
                            .3491E-01     .1210    
                            .5236E-01     .1434    
                            .6981E-01     .1659    
                            .8727E-01     .1887    
                            .1047         .2115    
                            .1222         .2345    
                            .1396         .2574    
                            .1571         .2803    
                            .1745         .2996    
                            .1920         .3161    
                            .2094         .3307    
                            .2443         .3536    
                            .2793         .3668    
                            .3142         .3558    
                        </tableData>
                    </table>
                </product>
            </function>

            <function name="aero/coefficient/ClDa">
                <description>
                    AILERONS: Piper PA34-200T Seneca-II Aircraft                               
                    Roll moment coefficient due to aileron deflection
                </description>
                <product>
                    <property>aero/qbar-area</property>
                    <property>metrics/bw-ft</property>
                    <table>
                        <independentVar>fcs/left-aileron-pos-rad</independentVar>
                        <tableData>
                            -.9774        -.5724E-01
                            -.6981        -.5060E-01
                            -.3491        -.3507E-01
                            -.1745        -.1754E-01
                            .000          .000    
                            .1745         .1754E-01
                            .3491         .3507E-01
                            .6981         .5060E-01
                            .9774         .5724E-01
                        </tableData>
                    </table>
                </product>
            </function>


            <!-- *************************
                Not calculated by DATCOM+
                ************************* -->

            <function name="aero/coefficient/ClDr">
                <description>
                    Roll moment due to rudder(DATCOM does not calculate)
                    Usually insignificant in dynamic stability considerations
                    but is ued in autopilot work
                </description>
                <product>
                    <property>metrics/bw-ft</property>
                    <property>fcs/rudder-pos-rad</property>
                    <value>    .000    </value>
                </product>
            </function>

        </axis>

        <!-- ********************************************************************** -->

        <axis name="PITCH">
            <function name="aero/coefficient/Cmde">
                <description>Pitch_moment_due_to_elevator_deflection</description>
                <product>
                    <property>aero/qbar-area</property>
                    <property>metrics/cbarw-ft</property>
                    <property>fcs/elevator-pos-rad</property>
                    <value>-1.6030</value>
                </product>
            </function>

            <function name="aero/coefficient/Cm_basic">
                <description>
                    Basic_Pitch_moment_coefficient
                </description>
                <product>
                    <property>aero/qbar-area</property>
                    <property>metrics/cbarw-ft</property>
                    <table>
                        <independentVar>aero/alpha-rad</independentVar>
                        <tableData>
                            -.1396         .2798    
                            -.1047         .2087    
                            -.6981E-01     .1415    
                            -.3491E-01     .7671E-01
                            .000         .1523E-01
                            .3491E-01    -.4476E-01
                            .5236E-01    -.7368E-01
                            .6981E-01    -.1026    
                            .8727E-01    -.1318    
                            .1047        -.1617    
                            .1222        -.1911    
                            .1396        -.2214    
                            .1571        -.2535    
                            .1745        -.2854    
                            .1920        -.3192    
                            .2094        -.3536    
                            .2443        -.3536    
                            .2793        -.3536    
                            .3142        -.3536    
                        </tableData>
                    </table>
                </product>
            </function>

            <function name="aero/coefficient/Cmq">
                <description>
                    Pitch moment coefficient due to pitch rate(per radian)
                    Pitch Damping Derivative
                    Very important to Short Period damping of oscillations.
                </description>
                <product>
                    <property>aero/qbar-area</property>
                    <property>metrics/cbarw-ft</property>
                    <property>aero/ci2vel</property>
                    <property>velocities/q-aero-rad_sec</property>
                    <value>-21.17</value>
                </product>
            </function>

            <function name="aero/coefficient/Cmff">
                <description>Delta_pitch_due_to_flap_deflection</description>
                <product>
                    <property>aero/qbar-area</property>
                    <property>metrics/cbarw-ft</property>
                    <table>
                        <independentVar>fcs/flap-pos-deg</independentVar>
                        <!-- datcom values
                        <tableData>
                            0.0000    0.0000
                            10.0000   0.1161
                            25.0000   0.2771
                            40.0000   0.3719
                        </tableData>
                        -->
                        <!-- experimental data -->
                        <tableData>
                            0   0.0
                            10 0.0
                            25 0.0
                            40 0.0
                        </tableData>
                    </table>
                </product>
            </function>

            <function name="aero/coefficient/Cmadot">
                <description>
                    Pitch moment coefficient due to AOA rate(per radian)
                    Negitive Cmad increase Short Period damping
                </description>
                <product>
                    <property>aero/qbar-area</property>
                    <property>metrics/cbarw-ft</property>
                    <property>aero/ci2vel</property>
                    <property>aero/alphadot-rad_sec</property>
                    <table>
                        <independentVar>aero/alpha-rad</independentVar>
                        <tableData>
                            -.1396        -9.126    
                            -.1047        -9.158    
                            -.6981E-01    -9.358    
                            -.3491E-01    -9.650    
                            .000        -9.868    
                            .3491E-01    -9.912    
                            .5236E-01    -9.873    
                            .6981E-01    -9.844    
                            .8727E-01    -9.718    
                            .1047        -9.432    
                            .1222        -8.725    
                            .1396        -7.670    
                            .1571        -6.989    
                            .1745        -6.500    
                            .1920        -5.820    
                            .2094        -4.965    
                            .2443        -1.454    
                            .2793         6.844    
                            .3142         13.63    
                        </tableData>
                    </table>
                </product>
            </function>
        </axis>
        <!-- ********************************************************************** -->
        <axis name="YAW">


            <function name="aero/coefficient/Cnb">
                <description>
                    Yaw moment coefficient due to sideslip(per radian)
                    Determines Dutch Roll and Spiral characteristics
                    Prevents side-slip and yawing moments
                </description>
                <product>
                    <property>aero/qbar-area</property>
                    <property>metrics/bw-ft</property>
                    <property>aero/beta-rad</property>
                    <table>
                        <independentVar>aero/alpha-rad</independentVar>
                        <tableData>
                            -.1396         .1200    
                            -.1047         .1200    
                            -.6981E-01     .1200    
                            -.3491E-01     .1200    
                            .000         .1200    
                            .3491E-01     .1200    
                            .5236E-01     .1200    
                            .6981E-01     .1200    
                            .8727E-01     .1200    
                            .1047         .1200    
                            .1222         .1200    
                            .1396         .1200    
                            .1571         .1200    
                            .1745         .1200    
                            .1920         .1200    
                            .2094         .1200    
                            .2443         .1200    
                            .2793         .1200    
                            .3142         .1200    
                        </tableData>
                    </table>
                </product>
            </function>
<!--
            <function name="aero/coefficient/Cnp">
                <description>
                    Yaw moment coefficient due to roll rate(per radian)
                    Reduces Dutch Roll damping.
                    positive value desireable.
                </description>
                <product>
                    <property>aero/qbar-area</property>
                    <property>metrics/bw-ft</property>
                    <property>aero/bi2vel</property>
                    <property>velocities/p-aero-rad_sec</property>
                    <table>
                        <independentVar>aero/alpha-rad</independentVar>
                        <tableData>
                            -.1396         .4890E-01
                            -.1047         .3126E-01
                            -.6981E-01     .1374E-01
                            -.3491E-01    -.3595E-02
                            .000        -.2134E-01
                            .3491E-01    -.3939E-01
                            .5236E-01    -.4852E-01
                            .6981E-01    -.5772E-01
                            .8727E-01    -.6699E-01
                            .1047        -.7633E-01
                            .1222        -.8576E-01
                            .1396        -.9525E-01
                            .1571        -.1070    
                            .1745        -.1195    
                            .1920        -.1304    
                            .2094        -.1405    
                            .2443        -.1597    
                            .2793        -.1803    
                            .3142        -.1857    
                        </tableData>
                    </table>
                </product>
            </function>
-->
            <function name="aero/coefficient/Cnr">
                <description>
                    Yaw Moment coefficient due to yaw rate(per radian)
                    Main contributor to damping of Dutch Roll
                </description>
                <product>
                    <property>aero/qbar-area</property>
                    <property>metrics/bw-ft</property>
                    <property>aero/bi2vel</property>
                    <property>velocities/r-aero-rad_sec</property>
                    <table>
                        <independentVar>aero/alpha-rad</independentVar>
                        <tableData>
                            -.1396        -.2353    
                            -.1047        -.2371    
                            -.6981E-01    -.2389    
                            -.3491E-01    -.2404    
                            .000        -.2417    
                            .3491E-01    -.2428    
                            .5236E-01    -.2433    
                            .6981E-01    -.2437    
                            .8727E-01    -.2442    
                            .1047        -.2445    
                            .1222        -.2449    
                            .1396        -.2452    
                            .1571        -.2455    
                            .1745        -.2455    
                            .1920        -.2454    
                            .2094        -.2451    
                            .2443        -.2438    
                            .2793        -.2416    
                            .3142        -.2375    
                        </tableData>
                    </table>
                </product>
            </function>

            <function name="aero/coefficient/CnDa">
                <description>
                    AILERONS: Piper PA34-200T Seneca-II Aircraft                               
                    Yaw Moment coefficient due to plain flap aileron deflection
                </description>
                <product>
                    <property>metrics/bw-ft</property>
                    <table>
                        <independentVar lookup="row">aero/alpha-rad</independentVar>
                        <independentVar lookup="column">fcs/left-aileron-pos-rad                </independentVar>
                        <tableData>
                            -.9774        -.6981        -.3491        -.1745          .000         .1745         .3491         .6981         .9774    
                            -.1396          .000          .000          .000          .000          .000          .000          .000          .000          .000    
                            -.1047          .000          .000          .000          .000          .000          .000          .000          .000          .000    
                            -.6981E-01      .000          .000          .000          .000          .000          .000          .000          .000          .000    
                            -.3491E-01      .000          .000          .000          .000          .000          .000          .000          .000          .000    
                            .000          .000          .000          .000          .000          .000          .000          .000          .000          .000    
                            .3491E-01      .000          .000          .000          .000          .000          .000          .000          .000          .000    
                            .5236E-01      .000          .000          .000          .000          .000          .000          .000          .000          .000    
                            .6981E-01      .000          .000          .000          .000          .000          .000          .000          .000          .000    
                            .8727E-01      .000          .000          .000          .000          .000          .000          .000          .000          .000    
                            .1047          .000          .000          .000          .000          .000          .000          .000          .000          .000    
                            .1222          .000          .000          .000          .000          .000          .000          .000          .000          .000    
                            .1396          .000          .000          .000          .000          .000          .000          .000          .000          .000    
                            .1571          .000          .000          .000          .000          .000          .000          .000          .000          .000    
                            .1745          .000          .000          .000          .000          .000          .000          .000          .000          .000    
                            .1920          .000          .000          .000          .000          .000          .000          .000          .000          .000    
                            .2094          .000          .000          .000          .000          .000          .000          .000          .000          .000    
                            .2443          .000          .000          .000          .000          .000          .000          .000          .000          .000    
                            .2793          .000          .000          .000          .000          .000          .000          .000          .000          .000    
                            .3142          .000          .000          .000          .000          .000          .000          .000          .000          .000    
                        </tableData>
                    </table>
                </product>
            </function>


            <!-- ******************************************************
                CnDr is not calculated by DATCOM+, but a default value
                is supplied.
                ******************************************************-->

            <function name="aero/coefficient/CnDr">
                <description>
                    Yaw Coefficient due to rudder(DATCOM does not calculate)
                    High value for controllablity, low value
                    for good dynamic stability
                </description>
                <product>
                    <property>aero/qbar-area</property>
                    <property>metrics/bw-ft</property>
                    <property>fcs/rudder-pos-rad</property>
                    <value>  -.6000E-01</value>
                </product>
            </function>


        </axis>
        <!-- ********************************************************************** -->
    </aerodynamics>
    <!-- ********************************************************************** -->
<!-- - ->
    <output name="SenecaII.csv" type="CSV" rate="5">
        <simulation> OFF </simulation>
        <atmosphere> OFF </atmosphere>
        <massprops> OFF </massprops>
        <rates> OFF </rates>
        <velocities> OFF </velocities>
        <forces> OFF </forces>
        <moments> OFF </moments>
        <position> OFF </position>
        <propulsion> ON </propulsion>
        <aerosurfaces> OFF </aerosurfaces>
        <fcs> ON </fcs>
        <ground_reactions> OFF </ground_reactions>
        <coefficients> OFF </coefficients>
    </output>
<!- - -->
</fdm_config>
