<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="c172" version="2.0" release="BETA"
    xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
    xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

    <fileheader>
        <author> Unknown </author>
        <filecreationdate> 2002-01-01 </filecreationdate>
        <version> $Id: c172p.xml,v 1.25 2009/12/09 14:43:30 jmt Exp $ </version>
        <description> Cessna C-172 </description>
    </fileheader>

    <metrics>
        <wingarea unit="FT2"> 174 </wingarea>
        <wingspan unit="FT"> 35.8 </wingspan>
        <chord unit="FT"> 4.9 </chord>
        <htailarea unit="FT2"> 21.9 </htailarea>
        <htailarm unit="FT"> 15.7 </htailarm>
        <vtailarea unit="FT2"> 16.5 </vtailarea>
        <vtailarm unit="FT"> 0 </vtailarm>
        <location name="AERORP" unit="IN">
            <x> 43.2 </x>
            <y> 0 </y>
            <z> 59.4 </z>
        </location>
        <location name="EYEPOINT" unit="IN">
            <x> 37 </x>
            <y> 0 </y>
            <z> 48 </z>
        </location>
        <location name="VRP" unit="IN">
            <x> 42.6 </x>
            <y> 0 </y>
            <z> 38.5 </z>
        </location>
    </metrics>

    <mass_balance>
        <ixx unit="SLUG*FT2"> 948 </ixx>
        <iyy unit="SLUG*FT2"> 1346 </iyy>
        <izz unit="SLUG*FT2"> 1967 </izz>
        <ixy unit="SLUG*FT2"> -0 </ixy>
        <ixz unit="SLUG*FT2"> -0 </ixz>
        <iyz unit="SLUG*FT2"> -0 </iyz>
        <emptywt unit="LBS"> 1500 </emptywt>
        <location name="CG" unit="IN">
            <x> 41 </x>
            <y> 0 </y>
            <z> 36.5 </z>
        </location>
        <pointmass name="Pilot">
            <weight unit="LBS"> 180 </weight>
            <location name="POINTMASS" unit="IN">
                <x> 36 </x>
                <y> -14 </y>
                <z> 24 </z>
            </location>
        </pointmass>
        <pointmass name="Co-Pilot">
            <weight unit="LBS"> 0 </weight>
            <location name="POINTMASS" unit="IN">
                <x> 36 </x>
                <y> 14 </y>
                <z> 24 </z>
            </location>
        </pointmass>
        <pointmass name="Left Passenger">
            <weight unit="LBS"> 0 </weight>
            <location name="POINTMASS" unit="IN">
                <x> 70 </x>
                <y> -14 </y>
                <z> 24 </z>
            </location>
        </pointmass>
        <pointmass name="Right Passenger">
            <weight unit="LBS"> 0 </weight>
            <location name="POINTMASS" unit="IN">
                <x> 70 </x>
                <y> 14 </y>
                <z> 24 </z>
            </location>
        </pointmass>
        <pointmass name="Baggage">
            <weight unit="LBS"> 0 </weight>
            <location name="POINTMASS" unit="IN">
                <x> 95 </x>
                <y>  0 </y>
                <z> 24 </z>
            </location>
        </pointmass>
    </mass_balance>

    <ground_reactions>
        <contact type="BOGEY" name="NOSE">
            <location unit="IN">
                <x> -6.8 </x>
                <y> 0 </y>
                <z> -19.5</z>
            </location>
            <static_friction> 0.8 </static_friction>
            <dynamic_friction> 0.5 </dynamic_friction>
            <rolling_friction> 0.02 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 1800 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 600 </damping_coeff>
            <max_steer unit="DEG"> 10 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable>0</retractable>
        </contact>
        <contact type="BOGEY" name="LEFT_MAIN">
            <location unit="IN">
                <x> 58.2 </x>
                <y> -43 </y>
                <z> -15.5 </z>
            </location>
            <static_friction> 0.8 </static_friction>
            <dynamic_friction> 0.5 </dynamic_friction>
            <rolling_friction> 0.02 </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>0</retractable>
        </contact>
        <contact type="BOGEY" name="RIGHT_MAIN">
            <location unit="IN">
                <x> 58.2 </x>
                <y> 43 </y>
                <z> -15.5 </z>
            </location>
            <static_friction> 0.8 </static_friction>
            <dynamic_friction> 0.5 </dynamic_friction>
            <rolling_friction> 0.02 </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>0</retractable>
        </contact>
        <contact type="BOGEY" name="TAIL_SKID">
            <location unit="IN">
                <x> 188 </x>
                <y> 0 </y>
                <z> 8 </z>
            </location>
            <static_friction> 0.2 </static_friction>
            <dynamic_friction> 0.2 </dynamic_friction>
            <rolling_friction> 0.2 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 20000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 1000 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable>0</retractable>
        </contact>
        <contact type="BOGEY" name="LEFT_TIP">
            <location unit="IN">
                <x> 43.2 </x>
                <y> -214.8 </y>
                <z> 59.4 </z>
            </location>
            <static_friction> 0.2 </static_friction>
            <dynamic_friction> 0.2 </dynamic_friction>
            <rolling_friction> 0.2 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable>0</retractable>
        </contact>
        <contact type="BOGEY" name="RIGHT_TIP">
            <location unit="IN">
                <x> 43.2 </x>
                <y> 214.8 </y>
                <z> 59.4 </z>
            </location>
            <static_friction> 0.2 </static_friction>
            <dynamic_friction> 0.2 </dynamic_friction>
            <rolling_friction> 0.2 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable>0</retractable>
        </contact>
    </ground_reactions>
    <propulsion>
        <engine file="eng_io320">
            <location unit="IN">
                <x> -19.7 </x>
                <y> 0 </y>
                <z> 26.6 </z>
            </location>
            <orient unit="DEG">
                <roll> 0.0 </roll>
                <pitch> 0 </pitch>
                <yaw> 0 </yaw>
            </orient>
            <feed>0</feed>
            <feed>1</feed>
            <thruster file="prop_75in2f">
                <location unit="IN">
                    <x> -37.7 </x>
                    <y> 0 </y>
                    <z> 26.6 </z>
                </location>
                <orient unit="DEG">
                    <roll> 0.0 </roll>
                    <pitch> 0.0 </pitch>
                    <yaw> 0.0 </yaw>
                </orient>
                <sense> 1 </sense>
                <p_factor> 5 </p_factor>
            </thruster>
        </engine>
        <tank type="FUEL">    <!-- Tank number 0 -->
            <location unit="IN">
                <x> 56 </x>
                <y> -112 </y>
                <z> 59.4 </z>
            </location>
            <capacity unit="LBS"> 185 </capacity>
            <contents unit="LBS"> 100 </contents>
        </tank>
        <tank type="FUEL">    <!-- Tank number 1 -->
            <location unit="IN">
                <x> 56 </x>
                <y> 112 </y>
                <z> 59.4 </z>
            </location>
            <capacity unit="LBS"> 185 </capacity>
            <contents unit="LBS"> 100 </contents>
        </tank>
    </propulsion>
    <flight_control name="FCS: c172">
        <channel name="Pitch">
            <summer name="Pitch Trim Sum">
                <input>fcs/elevator-cmd-norm</input>
                <input>fcs/pitch-trim-cmd-norm</input>
                <clipto>
                    <min>-1</min>
                    <max>1</max>
                </clipto>
            </summer>

            <aerosurface_scale name="Elevator Control">
                <input>fcs/pitch-trim-sum</input>
                <gain>0.01745</gain>
                <range>
                    <min>-28</min>
                    <max>23</max>
                </range>
                <output>fcs/elevator-pos-rad</output>
            </aerosurface_scale>

            <aerosurface_scale name="Elevator Position Normalized">
                <input>fcs/elevator-pos-deg</input>
                <domain>
                    <min>-28</min>
                    <max>23</max>
                </domain>
                <range>
                    <min>-1</min>
                    <max>1</max>
                </range>
                <output>fcs/elevator-pos-norm</output>
            </aerosurface_scale>
        </channel>
        <channel name="Roll">
            <summer name="Roll Trim Sum">
                <input>fcs/aileron-cmd-norm</input>
                <input>fcs/roll-trim-cmd-norm</input>
                <clipto>
                    <min>-1</min>
                    <max>1</max>
                </clipto>
            </summer>

            <aerosurface_scale name="Left Aileron Control">
                <input>fcs/roll-trim-sum</input>
                <gain>0.01745</gain>
                <range>
                    <min>-20</min>
                    <max>15</max>
                </range>
                <output>fcs/left-aileron-pos-rad</output>
            </aerosurface_scale>

            <aerosurface_scale name="Left Aileron Position Normalized">
                <input>fcs/left-aileron-pos-deg</input>
                <domain>
                    <min>-20</min>
                    <max>15</max>
                </domain>
                <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>-20</min>
                    <max>15</max>
                </range>
                <output>fcs/right-aileron-pos-rad</output>
            </aerosurface_scale>

            <aerosurface_scale name="Right Aileron Position Normalized">
                <input>fcs/right-aileron-pos-deg</input>
                <domain>
                    <min>-15</min>
                    <max>20</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="Yaw Trim Sum">
                <input>fcs/rudder-cmd-norm</input>
                <input>fcs/yaw-trim-cmd-norm</input>
                <clipto>
                    <min>-1</min>
                    <max>1</max>
                </clipto>
            </summer>

            <aerosurface_scale name="Rudder Control">
                <input>fcs/yaw-trim-sum</input>
                <gain>0.01745</gain>
                <range>
                    <min>-16</min>
                    <max>16</max>
                </range>
                <output>fcs/rudder-pos-rad</output>
            </aerosurface_scale>

            <aerosurface_scale name="Rudder Position Normalized">
                <input>fcs/rudder-pos-deg</input>
                <domain>
                    <min>-16</min>
                    <max>16</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>10</position>
                        <time>2</time>
                    </setting>
                    <setting>
                        <position>20</position>
                        <time>1</time>
                    </setting>
                    <setting>
                        <position>30</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>30</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>
    </flight_control>
    <aerodynamics>

        <alphalimits unit="RAD">
            <min>-0.087</min>
            <max>0.28</max>
        </alphalimits>

        <hysteresis_limits unit="RAD">
            <min>0.09</min>
            <max>0.36</max>
        </hysteresis_limits>

        <function name="aero/function/kCDge">
            <description>Change_in_drag_due_to_ground_effect</description>
            <product>
                  <table>
                      <independentVar>aero/h_b-mac-ft</independentVar>
                      <tableData>
                          0.0000	0.4800
                          0.1000	0.5150
                          0.1500	0.6290
                          0.2000	0.7090
                          0.3000	0.8150
                          0.4000	0.8820
                          0.5000	0.9280
                          0.6000	0.9620
                          0.7000	0.9880
                          0.8000	1.0000
                          0.9000	1.0000
                          1.0000	1.0000
                          1.1000	1.0000
                      </tableData>
                  </table>
            </product>
        </function>

        <function name="aero/function/kCLge">
            <description>Change_in_lift_due_to_ground_effect</description>
            <product>
                  <table>
                      <independentVar>aero/h_b-mac-ft</independentVar>
                      <tableData>
                          0.0000	1.2030
                          0.1000	1.1270
                          0.1500	1.0900
                          0.2000	1.0730
                          0.3000	1.0460
                          0.4000	1.0550
                          0.5000	1.0190
                          0.6000	1.0130
                          0.7000	1.0080
                          0.8000	1.0060
                          0.9000	1.0030
                          1.0000	1.0020
                          1.1000	1.0000
                      </tableData>
                  </table>
            </product>
        </function>

        <axis name="DRAG">
            <function name="aero/coefficient/CDo">
                <description>Drag_at_zero_lift</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <value>0.027</value>
                </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/kCDge</property>
                      <table>
                          <independentVar>fcs/flap-pos-deg</independentVar>
                          <tableData>
                              0.0000	0.0000
                              10.0000	0.0070
                              20.0000	0.0120
                              30.0000	0.0180
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/CDwbh">
                <description>Drag_due_to_alpha</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/function/kCDge</property>
                      <table>
                          <independentVar lookup="row">aero/alpha-rad</independentVar>
                          <independentVar lookup="column">fcs/flap-pos-deg</independentVar>
                          <tableData>
                                0.0000	10.0000	20.0000	30.0000
                              -0.0873	0.0041	0.0000	0.0005	0.0014
                              -0.0698	0.0013	0.0004	0.0025	0.0041
                              -0.0524	0.0001	0.0023	0.0059	0.0084
                              -0.0349	0.0003	0.0057	0.0108	0.0141
                              -0.0175	0.0020	0.0105	0.0172	0.0212
                              0.0000	0.0052	0.0168	0.0251	0.0299
                              0.0175	0.0099	0.0248	0.0346	0.0402
                              0.0349	0.0162	0.0342	0.0457	0.0521
                              0.0524	0.0240	0.0452	0.0583	0.0655
                              0.0698	0.0334	0.0577	0.0724	0.0804
                              0.0873	0.0442	0.0718	0.0881	0.0968
                              0.1047	0.0566	0.0874	0.1053	0.1148
                              0.1222	0.0706	0.1045	0.1240	0.1343
                              0.1396	0.0860	0.1232	0.1442	0.1554
                              0.1571	0.0962	0.1353	0.1573	0.1690
                              0.1745	0.1069	0.1479	0.1708	0.1830
                              0.1920	0.1180	0.1610	0.1849	0.1975
                              0.2094	0.1298	0.1746	0.1995	0.2126
                              0.2269	0.1424	0.1892	0.2151	0.2286
                              0.2443	0.1565	0.2054	0.2323	0.2464
                              0.2618	0.1727	0.2240	0.2521	0.2667
                              0.2793	0.1782	0.2302	0.2587	0.2735
                              0.2967	0.1716	0.2227	0.2507	0.2653
                              0.3142	0.1618	0.2115	0.2388	0.2531
                              0.3316	0.1475	0.1951	0.2214	0.2351
                              0.3491	0.1097	0.1512	0.1744	0.1866
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/CDDe">
                <description>Drag_due_to_Elevator_Deflection</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/mag-elevator-pos-rad</property>
                    <value>0.0000</value>
                </product>
            </function>
            <function name="aero/coefficient/CDbeta">
                <description>Drag_due_to_sideslip</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/mag-beta-rad</property>
                    <value>0.1700</value>
                </product>
            </function>
        </axis>

        <axis name="SIDE">
            <function name="aero/coefficient/CYb">
                <description>Side_force_due_to_beta</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                      <table>
                          <independentVar lookup="row">aero/beta-rad</independentVar>
                          <independentVar lookup="column">fcs/flap-pos-deg</independentVar>
                          <tableData>
                                0.0000	30.0000
                              -0.3490	0.1370	0.1060
                              0.0000	0.0000	0.0000
                              0.3490	-0.1370	-0.1060
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/CYda">
                <description>Side_force_due_to_aileron</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/left-aileron-pos-rad</property>
                    <value>0.0000</value>
                </product>
            </function>
            <function name="aero/coefficient/CYdr">
                <description>Side_force_due_to_rudder</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/rudder-pos-rad</property>
                    <value>0.1870</value>
                </product>
            </function>
            <function name="aero/coefficient/CYp">
                <description>Side_force_due_to_roll_rate</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/bi2vel</property>
                    <property>velocities/p-aero-rad_sec</property>
                      <table>
                          <independentVar lookup="row">aero/alpha-rad</independentVar>
                          <independentVar lookup="column">fcs/flap-pos-deg</independentVar>
                          <tableData>
                                0.0000	30.0000
                              0.0000	-0.0750	-0.1610
                              0.0940	-0.1450	-0.2310
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/CYr">
                <description>Side_force_due_to_yaw_rate</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/bi2vel</property>
                    <property>velocities/r-aero-rad_sec</property>
                      <table>
                          <independentVar lookup="row">aero/alpha-rad</independentVar>
                          <independentVar lookup="column">fcs/flap-pos-deg</independentVar>
                          <tableData>
                                0.0000	30.0000
                              0.0000	0.2140	0.1620
                              0.0940	0.2670	0.2150
                          </tableData>
                      </table>
                </product>
            </function>
        </axis>

        <axis name="LIFT">
            <function name="aero/coefficient/CLwbh">
                <description>Lift_due_to_alpha</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/function/kCLge</property>
                      <table>
                          <independentVar lookup="row">aero/alpha-rad</independentVar>
                          <independentVar lookup="column">aero/stall-hyst-norm</independentVar>
                          <tableData>
                                0.0000	1.0000
                              -0.0900	-0.2200	-0.2200
                              0.0000	0.2500	0.2500
                              0.0900	0.7300	0.7300
                              0.1000	0.8300	0.7800
                              0.1200	0.9200	0.7900
                              0.1400	1.0200	0.8100
                              0.1600	1.0800	0.8200
                              0.1700	1.1300	0.8300
                              0.1900	1.1900	0.8500
                              0.2100	1.2500	0.8600
                              0.2400	1.3500	0.8800
                              0.2600	1.4400	0.9000
                              0.2800	1.4700	0.9200
                              0.3000	1.4300	0.9500
                              0.3200	1.3800	0.9900
                              0.3400	1.3000	1.0500
                              0.3600	1.1500	1.1500
                          </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/kCLge</property>
                      <table>
                          <independentVar>fcs/flap-pos-deg</independentVar>
                          <tableData>
                              0.0000	0.0000
                              10.0000	0.2000
                              20.0000	0.3000
                              30.0000	0.3500
                          </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>0.4300</value>
                </product>
            </function>
            <function name="aero/coefficient/CLadot">
                <description>Lift_due_to_alpha_rate</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/alphadot-rad_sec</property>
                    <property>aero/ci2vel</property>
                    <value>1.7000</value>
                </product>
            </function>
            <function name="aero/coefficient/CLq">
                <description>Lift_due_to_pitch_rate</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>velocities/q-aero-rad_sec</property>
                    <property>aero/ci2vel</property>
                    <value>3.9000</value>
                </product>
            </function>
        </axis>

        <axis name="ROLL">
            <function name="aero/coefficient/Clb">
                <description>Roll_moment_due_to_beta</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                      <table>
                          <independentVar>aero/beta-rad</independentVar>
                          <tableData>
                              -0.3490	0.0322
                              0.0000	0.0000
                              0.3490	-0.0322
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/Clp">
                <description>Roll_moment_due_to_roll_rate_(roll_damping)</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>aero/bi2vel</property>
                    <property>velocities/p-aero-rad_sec</property>
                    <value>-0.4840</value>
                </product>
            </function>
            <function name="aero/coefficient/Clr">
                <description>Roll_moment_due_to_yaw_rate</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>aero/bi2vel</property>
                    <property>velocities/r-aero-rad_sec</property>
                      <table>
                          <independentVar lookup="row">aero/alpha-rad</independentVar>
                          <independentVar lookup="column">fcs/flap-pos-deg</independentVar>
                          <tableData>
                                0.0000	30.0000
                              0.0000	0.0798	0.1246
                              0.0940	0.1869	0.2317
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/ClDa">
                <description>Roll_moment_due_to_aileron</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>fcs/left-aileron-pos-rad</property>
                    <value>0.2290</value>
                </product>
            </function>
            <function name="aero/coefficient/Cldr">
                <description>Roll_moment_due_to_rudder</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>fcs/rudder-pos-rad</property>
                    <value>0.0147</value>
                </product>
            </function>
        </axis>

        <axis name="PITCH">
            <function name="aero/coefficient/Cmo">
                <description>Pitching_moment_at_zero_alpha</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                    <value>0.1000</value>
                </product>
            </function>
            <function name="aero/coefficient/Cmalpha">
                <description>Pitch_moment_due_to_alpha</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                    <property>aero/alpha-rad</property>
                    <value>-1.8000</value>
                </product>
            </function>
            <function name="aero/coefficient/Cmq">
                <description>Pitch_moment_due_to_pitch_rate</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                    <property>aero/ci2vel</property>
                    <property>velocities/q-aero-rad_sec</property>
                    <value>-12.4000</value>
                </product>
            </function>
            <function name="aero/coefficient/Cmadot">
                <description>Pitch_moment_due_to_alpha_rate</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                    <property>aero/ci2vel</property>
                    <property>aero/alphadot-rad_sec</property>
                    <value>-7.2700</value>
                </product>
            </function>
            <function name="aero/coefficient/Cmde">
                <description>Pitch_moment_due_to_elevator_deflection</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                    <property>fcs/elevator-pos-rad</property>
                    <value>-1.1220</value>
                </product>
            </function>
            <function name="aero/coefficient/Cmdf">
                <description>Delta_pitching_moment_due_to_flap_deflection</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                      <table>
                          <independentVar>fcs/flap-pos-deg</independentVar>
                          <tableData>
                              0.0000	0.0000
                              10.0000	-0.0654
                              20.0000	-0.0981
                              30.0000	-0.1140
                          </tableData>
                      </table>
                </product>
            </function>
        </axis>

        <axis name="YAW">
            <function name="aero/coefficient/Cnb">
                <description>Yaw_moment_due_to_beta</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                      <table>
                          <independentVar>aero/beta-rad</independentVar>
                          <tableData>
                              -0.3490	-0.0205
                              0.0000	0.0000
                              0.3490	0.0205
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/Cnp">
                <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>-0.0278</value>
                </product>
            </function>
            <function name="aero/coefficient/Cnr">
                <description>Yaw_moment_due_to_yaw_rate</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>aero/bi2vel</property>
                    <property>velocities/r-aero-rad_sec</property>
                    <value>-0.0937</value>
                </product>
            </function>
            <function name="aero/coefficient/Cnda">
                <description>Yaw_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>-0.0053</value>
                </product>
            </function>
            <function name="aero/coefficient/Cndr">
                <description>Yaw_moment_due_to_rudder</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>fcs/rudder-pos-rad</property>
                    <value>-0.0430</value>
                </product>
            </function>
        </axis>
    </aerodynamics>
<!--
    <output name="JSBout172C.csv" type="CSV" rate="60">
      <property> aero/qbar-psf </property>
      <property> accelerations/udot-ft_sec2 </property>
      <property> accelerations/vdot-ft_sec2 </property>
      <property> accelerations/wdot-ft_sec2 </property>
      <property> accelerations/a-pilot-x-ft_sec2 </property>
      <property> accelerations/a-pilot-y-ft_sec2 </property>
      <property> accelerations/a-pilot-z-ft_sec2 </property>
      <property> accelerations/n-pilot-x-norm    </property>
      <property> accelerations/n-pilot-y-norm    </property>
      <property> accelerations/n-pilot-z-norm    </property>
      <rates> ON </rates>
      <velocities> ON </velocities>
      <forces> ON </forces>
      <moments> ON </moments>
      <position> ON </position>
      <fcs> OFF </fcs>
      <propulsion> OFF </propulsion>
      <aerosurfaces> OFF </aerosurfaces>
      <fcs> OFF </fcs>
      <ground_reactions> OFF </ground_reactions>
    </output>
-->
</fdm_config>
