<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance" name="CH750" version="2.0" release="ALPHA" xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">
	<fileheader>
		<author> Aeromatic v 3.3.10 </author>
		<filecreationdate> 18 Apr 2019 </filecreationdate>
		<version>$Revision: 1.80 $</version>
		<description> Models a CH750. </description>
	</fileheader>
	<!--
  File:     CH750.xml
  Inputs:
    name:          CH750
    type:          Single engine Glider, Small Commuter
    stall speed:   38.00kts
    max weight:    1320.00 lb
    length:        21.83 ft
    wing: 
     span:         29.83 ft
     area:         144.00 sq-ft
     mean chord:   4.83 ft
     aspect ratio: 5.50:1
     taper ratio:  1.00:1
     incidence:    2.00 degrees
     dihedral:     0.00 degrees
     sweep:        0.00 degrees

    no. engines:   1
    engine type:   Piston Engine
    engine layout: forward fuselage

    gear type:     tricycle
    steering type: steering
    retractable?:  no

  Outputs:
    wing loading:       9.17 lb/sq-ft
     - thickness ratio: 11.45%
    payload:            349.64 lbs
    CL-alpha:           4.71 per radian
    CL-0:               0.40
    CL-max:             1.88
    CD-0:               0.02
    K:                  0.04
    Mcrit:              0.70

    min. turn radius    70.58 ft
    max. turn rate:     1.00 deg/s
-->
	<metrics>
		<wingarea unit="FT2">   144.00 </wingarea>
		<wingspan unit="FT">    29.83 </wingspan>
		<wing_incidence unit="DEG"> 2.00 </wing_incidence>
		<chord unit="FT">     4.83 </chord>
		<htailarea unit="FT2">    22.20 </htailarea>
		<htailarm unit="FT">    15.00 </htailarm>
		<vtailarea unit="FT2">   15.00 </vtailarea>
		<vtailarm unit="FT">    15.00 </vtailarm>
		<location name="AERORP" unit="M">
			<x>    0.33 </x>
			<y>     0.00 </y>
			<z>    0.66 </z>
		</location>
		<location name="EYEPOINT" unit="M">
			<x>    0.7 </x>
			<y>   -0.2 </y>
			<z>    0.3</z>
		</location>
		<location name="VRP" unit="IN">
			<x>     0.0 </x>
			<y>     0.0 </y>
			<z>     0.0 </z>
		</location>
	</metrics>
	<mass_balance>
		<ixx unit="SLUG*FT2">    380 </ixx>
		<iyy unit="SLUG*FT2">    250 </iyy>
		<izz unit="SLUG*FT2">    650 </izz>
		<emptywt unit="LBS">    775.00 </emptywt>
		<!--CG range: 19%-34% MAC
		~0.15 - ~0.389 m-->
		<location name="CG" unit="M">
			<!--for empty aircraft-->
			<x>    0.25 </x>
			<y>     0.00 </y>
			<z>    0.0 </z>
		</location>
		<pointmass name="Pilot">
			<weight unit="KG"> 80 </weight>
			<location name="POINTMASS" unit="M">
				<x>    0.5 </x>
				<y>   -0.2 </y>
				<z>    0.3</z>
			</location>
		</pointmass>
		<pointmass name="Copilot">
			<weight unit="KG"> 80 </weight>
			<location name="POINTMASS" unit="M">
				<x>    0.5 </x>
				<y>    0.2 </y>
				<z>    0.3</z>
			</location>
		</pointmass>
		<pointmass name="Baggage">
			<weight unit="KG"> 10 </weight>
			<location name="POINTMASS" unit="M">
				<x>    1.1 </x>
				<y>    0.0 </y>
				<z>    0.0</z>
			</location>
		</pointmass>
	</mass_balance>
	<propulsion>
		<engine file="Rotax912ULS">
			<location unit="M">
				<x>    -0.90 </x>
				<y>     0.00 </y>
				<z>     0.00 </z>
			</location>
			<orient unit="DEG">
				<pitch>     0.00 </pitch>
				<roll>     0.00 </roll>
				<yaw>     0.00 </yaw>
			</orient>
			<feed> 0 </feed>
			<thruster file="zenith">
				<sense> 1 </sense>
				<location unit="M">
					<x>    -1.4 </x>
					<y>     0.00 </y>
					<z>     0.00 </z>
				</location>
				<orient unit="DEG">
					<pitch>     0.00 </pitch>
					<roll>     0.00 </roll>
					<yaw>     0.00 </yaw>
				</orient>
			</thruster>
		</engine>
		<tank type="FUEL" number="0">
			<location unit="M">
				<x>    0.33 </x>
				<y>     -0.5 </y>
				<z>    0.66 </z>
			</location>
			<capacity unit="LBS"> 72 </capacity>
			<contents unit="LBS"> 40 </contents>
		</tank>
		<tank type="FUEL" number="1">
			<location unit="M">
				<x>    0.33 </x>
				<y>     0.5 </y>
				<z>    0.66 </z>
			</location>
			<capacity unit="LBS"> 72 </capacity>
			<contents unit="LBS"> 40 </contents>
		</tank>
	</propulsion>
	<ground_reactions>
		<contact type="BOGEY" name="NOSE">
			<location unit="M">
				<x>   -0.81742 </x>
				<y>     0.00 </y>
				<z>   -1.14392</z>
			</location>
			<static_friction>  0.80 </static_friction>
			<dynamic_friction> 0.50 </dynamic_friction>
			<rolling_friction> 0.02 </rolling_friction>
			<spring_coeff unit="LBS/FT">     2000.00 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC"> 500.00 </damping_coeff>
			<max_steer unit="DEG"> 45.00 </max_steer>
			<brake_group> NONE </brake_group>
			<retractable> 0 </retractable>
		</contact>
		<contact type="BOGEY" name="LEFT_MAIN">
			<location unit="M">
				<x>    0.55224 </x>
				<y>   -0.88853 </y>
				<z>  -1.238 </z>
			</location>
			<static_friction>  0.80 </static_friction>
			<dynamic_friction> 0.50 </dynamic_friction>
			<rolling_friction> 0.02 </rolling_friction>
			<spring_coeff unit="LBS/FT">     1220.00 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC"> 460.00 </damping_coeff>
			<max_steer unit="DEG">0</max_steer>
			<brake_group> LEFT </brake_group>
			<retractable> 0 </retractable>
		</contact>
		<contact type="BOGEY" name="RIGHT_MAIN">
			<location unit="M">
				<x>    0.55224 </x>
				<y>   0.88853 </y>
				<z>  -1.238 </z>
			</location>
			<static_friction>  0.80 </static_friction>
			<dynamic_friction> 0.50 </dynamic_friction>
			<rolling_friction> 0.02 </rolling_friction>
			<spring_coeff unit="LBS/FT">     1220.00 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC"> 460.00 </damping_coeff>
			<max_steer unit="DEG">0</max_steer>
			<brake_group> RIGHT </brake_group>
			<retractable> 0 </retractable>
		</contact>
		<contact type="STRUCTURE" name="LEFT_WING">
			<location unit="M">
				<x>   0.3 </x>
				<y>  -4.3 </y>
				<z>  0.64 </z>
			</location>
			<static_friction>  1 </static_friction>
			<dynamic_friction> 1 </dynamic_friction>
			<spring_coeff unit="LBS/FT">      500.00 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC"> 300.00 </damping_coeff>
		</contact>
		<contact type="STRUCTURE" name="RIGHT_WING">
			<location unit="M">
				<x>   0.3 </x>
				<y>  4.3 </y>
				<z>  0.64 </z>
			</location>
			<static_friction>  1 </static_friction>
			<dynamic_friction> 1 </dynamic_friction>
			<spring_coeff unit="LBS/FT">      500.00 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC"> 300.00 </damping_coeff>
		</contact>
		<contact type="STRUCTURE" name="TAIL">
			<location unit="M">
				<x>   4.8 </x>
				<y>  0.0 </y>
				<z>  0.26 </z>
			</location>
			<static_friction>  1 </static_friction>
			<dynamic_friction> 1 </dynamic_friction>
			<spring_coeff unit="LBS/FT">      500.00 </spring_coeff>
			<damping_coeff unit="LBS/FT/SEC"> 300.00 </damping_coeff>
		</contact>
	</ground_reactions>
	<flight_control name="FCS: CH750">
		<channel name="Pitch">
			<!--Adapted from Octal450's IDG-PA28-->
			<fcs_function name="fcs/elevator-trim-offset">
				<function>
					<product>
						<property>fcs/pitch-trim-cmd-norm</property>
						<value>0.75</value>
						<table>
							<independentVar lookup="row">fcs/elevator-cmd-norm</independentVar>
							<tableData>
								-1  0
								0  1
								1  0
							</tableData>
						</table>
					</product>
				</function>
			</fcs_function>
			<summer name="Pitch Trim Sum">
				<input>fcs/elevator-cmd-norm</input>
				<input>fcs/elevator-trim-offset</input>
				<clipto>
					<min> -1 </min>
					<max>  1 </max>
				</clipto>
			</summer>
			<aerosurface_scale name="Elevator Control">
				<input>fcs/pitch-trim-sum</input>
				<range>
					<min> -0.35 </min>
					<max>  0.35 </max>
				</range>
				<output>fcs/elevator-pos-rad</output>
			</aerosurface_scale>
			<aerosurface_scale name="Elevator Normalization">
				<input>fcs/elevator-pos-rad</input>
				<domain>
					<min> -0.35 </min>
					<max>  0.35 </max>
				</domain>
				<range>
					<min> -1 </min>
					<max>  1 </max>
				</range>
				<output>fcs/elevator-pos-norm</output>
			</aerosurface_scale>
		</channel>
		<channel name="Yaw">
			<summer name="Rudder Command Sum">
				<input>fcs/rudder-cmd-norm</input>
				<input>fcs/yaw-trim-cmd-norm</input>
				<clipto>
					<min> -1 </min>
					<max>  1 </max>
				</clipto>
			</summer>
			<aerosurface_scale name="Rudder Control">
				<input>fcs/rudder-command-sum</input>
				<range>
					<min> -0.35 </min>
					<max>  0.35 </max>
				</range>
				<output>fcs/rudder-pos-rad</output>
			</aerosurface_scale>
			<aerosurface_scale name="Rudder Normalization">
				<input>fcs/rudder-pos-rad</input>
				<domain>
					<min> -0.35 </min>
					<max>  0.35 </max>
				</domain>
				<range>
					<min> -1 </min>
					<max>  1 </max>
				</range>
				<output>fcs/rudder-pos-norm</output>
			</aerosurface_scale>
		</channel>
		<channel name="Flaperons">
			<!--Adapted from Octal450's IDG-PA28-->
			<fcs_function name="fcs/aileron-trim-offset">
				<function>
					<product>
						<property>fcs/roll-trim-cmd-norm</property>
						<value>0.75</value>
						<table>
							<independentVar lookup="row">fcs/aileron-cmd-norm</independentVar>
							<tableData>
								-1  0
								0  1
								1  0
							</tableData>
						</table>
					</product>
				</function>
			</fcs_function>
			<summer name="Roll Trim Sum">
				<input>fcs/aileron-cmd-norm</input>
				<input>fcs/aileron-trim-offset</input>
				<clipto>
					<min> -1 </min>
					<max>  1 </max>
				</clipto>
			</summer>
			
			<fcs_function name="fcs/left-flaperon-pos-deg">
				<function>
					<sum>
						<table>
							<independentVar>/controls/flight/flaps</independentVar>
							<tableData>
							0.0	0
							1	15
						</tableData>
						</table>
						<product>
							<property>fcs/aileron-cmd-norm</property>
							<value>15</value>
						</product>
					</sum>
				</function>
			</fcs_function>
			<fcs_function name="fcs/right-flaperon-pos-deg">
				<function>
					<sum>
						<table>
							<independentVar>/controls/flight/flaps</independentVar>
							<tableData>
							0.0	0
							1	15
						</tableData>
						</table>
						<product>
							<property>-fcs/aileron-cmd-norm</property>
							<value>15</value>
						</product>
					</sum>
				</function>
			</fcs_function>
			<aerosurface_scale name="Flaperon L Normalization">
				<input>fcs/left-flaperon-pos-deg</input>
				<domain>
					<min>  -10 </min>
					<max> 16 </max>
				</domain>
				<range>
					<min> -0.625 </min>
					<max> 1 </max>
				</range>
				<output>fcs/left-flaperon-pos-norm</output>
			</aerosurface_scale>
			<aerosurface_scale name="Flaperon R Normalization">
				<input>fcs/right-flaperon-pos-deg</input>
				<domain>
					<min>  -10 </min>
					<max> 16 </max>
				</domain>
				<range>
					<min> -0.625 </min>
					<max> 1 </max>
				</range>
				<output>fcs/right-flaperon-pos-norm</output>
			</aerosurface_scale>
		</channel>
		<channel name="Landing Gear">
			<switch name="fcs/gear-no-wow">
				<default value="1"/>
				<test logic="AND" value="0">
				gear/unit[1]/WOW eq 1
				gear/unit[2]/WOW eq 1
			</test>
			</switch>
		</channel>
		<channel name="Switches">
			<lag_filter name="/controls/engines/engine/master-alt-pos">
				<input>/controls/engines/engine/master-alt</input>
				<c1>20.0</c1>
			</lag_filter>
			<lag_filter name="/controls/engines/engine/master-bat-pos">
				<input>/controls/engines/engine/master-bat</input>
				<c1>20.0</c1>
			</lag_filter>
			<lag_filter name="/controls/switches/radio-master-pos">
				<input>/controls/switches/radio-master</input>
				<c1>20.0</c1>
			</lag_filter>
			<lag_filter name="/controls/switches/landing-light-pos">
				<input>/controls/switches/landing-light</input>
				<c1>20.0</c1>
			</lag_filter>
			<lag_filter name="/controls/switches/strobe-lights-pos">
				<input>/controls/switches/strobe-lights</input>
				<c1>20.0</c1>
			</lag_filter>
			<lag_filter name="/controls/switches/nav-lights-pos">
				<input>/controls/switches/nav-lights</input>
				<c1>20.0</c1>
			</lag_filter>
			<lag_filter name="/controls/switches/fuel-pump-pos">
				<input>/controls/switches/fuel-pump</input>
				<c1>20.0</c1>
			</lag_filter>
		</channel>
		<channel name="General">
			
			<fcs_function name="/ch750stol/door-left-input">
				<function>
					<min>
						<property>/ch750stol/door-left-cmd</property>
						<table>
							<independentVar lookup="row">velocities/vc-kts</independentVar>
							<tableData>
								60  1.00
								80  0.05
							</tableData>
						</table>
					</min>
				</function>
			</fcs_function>
			
			<lag_filter name="/ch750stol/door-left-norm">
				<input>/ch750stol/door-left-input</input>
				<c1>2.0</c1>
			</lag_filter>
			
			<fcs_function name="/ch750stol/door-right-input">
				<function>
					<min>
						<property>/ch750stol/door-right-cmd</property>
						<table>
							<independentVar lookup="row">velocities/vc-kts</independentVar>
							<tableData>
								60  1.00
								80  0.05
							</tableData>
						</table>
					</min>
				</function>
			</fcs_function>
			
			<lag_filter name="/ch750stol/door-right-norm">
				<input>/ch750stol/door-right-input</input>
				<c1>2.0</c1>
			</lag_filter>
		
		</channel>
	</flight_control>
	<aerodynamics>
		<function name="aero/function/kCDge">
			<description>Change_in_drag_due_to_ground_effect</description>
			<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>
		</function>
		<function name="aero/function/kCLge">
			<description>Change_in_lift_due_to_ground_effect</description>
			<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    1.0280
                      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>
		</function>
		<function name="aero/vel-propwash-fps">
			<description> propeller induced velocity </description>
			<property>propulsion/engine/prop-induced-velocity_fps</property>
		</function>
		<function name="aero/qbar-propwash-psf">
			<description> q bar due to the propeller induced velocity </description>
			<product>
				<property>aero/vel-propwash-fps</property>
				<property>aero/vel-propwash-fps</property>
				<property>atmosphere/rho-slugs_ft3</property>
				<value>0.5</value>
			</product>
		</function>
		<function name="aero/velocity-induced-fps">
			<description> velocity including the propulsion induced velocity.</description>
			<sum>
				<property>velocities/u-aero-fps</property>
				<property>propulsion/engine/prop-induced-velocity_fps</property>
			</sum>
		</function>
		<function name="aero/qbar-induced-psf">
			<description> q bar including the propulsion induced velocity.</description>
			<product>
				<property>aero/velocity-induced-fps</property>
				<property>aero/velocity-induced-fps</property>
				<property>atmosphere/rho-slugs_ft3</property>
				<value>0.5</value>
			</product>
		</function>
		<axis name="LIFT">
			<function name="aero/force/Lift_propwash">
				<description>Delta lift due to propeller induced velocity</description>
				<product>
					<property>propulsion/engine[0]/thrust-coefficient</property>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<table>
						<independentVar lookup="row">aero/alpha-rad</independentVar>
						<independentVar lookup="column">fcs/flap-pos-deg</independentVar>
						<tableData>
                     0.0     60.0
              -0.21  0.000   0.000
               0.00  0.069   0.185
               0.34  0.329   0.877
               0.67  0.000   0.000
            </tableData>
					</table>
				</product>
			</function>
			<!-- Lift above 0.85 and below -0.85 is generalised -->
			<function name="aero/force/Lift_alpha">
				<description>Lift due to alpha</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>aero/function/kCLge</property>
					<table>
						<independentVar lookup="row">aero/alpha-rad</independentVar>
						<tableData>
              -1.57  0.0000
              -1.22 -0.5692
              -1.05 -0.7668
              -0.88 -0.8855
              -0.68 -0.5919
              -0.40 -1.4798
               0.00  0.3953
               0.31  1.8751
               0.60  0.9872
               0.88  1.1145
               1.05  0.9652
               1.22  0.7164
               1.57  0.0000
            </tableData>
					</table>
				</product>
			</function>
			<function name="aero/force/Lift_pitch_rate">
				<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> 3.8262 </value>
				</product>
			</function>
			<function name="aero/force/Lift_alpha_rate">
				<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> 2.0406 </value>
				</product>
			</function>
			<function name="aero/force/Lift_elevator">
				<description>Lift due to Elevator Deflection</description>
				<product>
					<property>aero/qbar-induced-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>fcs/elevator-pos-rad</property>
					<value> 0.4135 </value>
				</product>
			</function>
			<function name="aero/force/Lift_flaperons">
				<description>Delta Lift due to flaperons</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<sum>
						<property>fcs/left-flaperon-pos-deg</property>
						<property>fcs/right-flaperon-pos-deg</property>
					</sum>
					<value> 0.016 </value>
				</product>
			</function>
		</axis>
		<axis name="DRAG">
			<!-- CD0 is based on fuselage, wing, horizontal- en vertical tail -->
			<!-- Antennas, struts and wires are not taken into account        -->
			<!-- CD for gear (fixed and retractable) is defined below         -->
			<function name="aero/force/Drag_minimum">
				<description>Minimum drag</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>aero/function/kCDge</property>
					<value> 0.0217 </value>
				</product>
			</function>
			<function name="aero/force/Drag_alpha">
				<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>
						<tableData>
             -1.57    1.4095
             -0.31    0.0721
              0.00    0.0000
              0.31    0.0721
              1.57    1.4095
            </tableData>
					</table>
				</product>
			</function>
			<function name="aero/force/Drag_induced">
				<description>Induced drag</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>aero/cl-squared</property>
					<property>aero/function/kCDge</property>
					<value> 0.0617 </value>
				</product>
			</function>
			<function name="aero/force/Drag_mach">
				<description>Drag due to mach</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<table>
						<independentVar lookup="row">velocities/mach</independentVar>
						<tableData>
                0.00    0.0000
                0.70    0.0000
                1.10    0.0230
                1.80    0.0150
            </tableData>
					</table>
				</product>
			</function>
			<function name="aero/force/Drag_beta">
				<description>Drag due to sideslip</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<table>
						<independentVar lookup="row">aero/beta-rad</independentVar>
						<tableData>
              -1.57    1.2300
              -0.26    0.0500
               0.00    0.0000
               0.26    0.0500
               1.57    1.2300
            </tableData>
					</table>
				</product>
			</function>
			<function name="aero/force/Drag_elevator">
				<description>Drag due to Elevator Deflection</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<abs>
						<property>fcs/elevator-pos-rad</property>
					</abs>
					<value> 0.0400 </value>
				</product>
			</function>
			<function name="aero/force/Drag_gear">
				<description>Drag due to gear</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<value> 0.0040 </value>
				</product>
			</function>
			<function name="aero/force/Drag_flaperons">
				<description>Drag due to flaps</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<sum>
						<property>fcs/left-flaperon-pos-deg</property>
						<property>fcs/right-flaperon-pos-deg</property>
					</sum>
					<value> 0.0012 </value>
				</product>
			</function>
		</axis>
		<axis name="SIDE">
			<function name="aero/force/Side_beta">
				<description>Side force due to beta</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>aero/beta-rad</property>
					<value> -0.4754 </value>
				</product>
			</function>
			<function name="aero/force/Side_roll_rate">
				<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/Re</independentVar>
						<tableData>
                 1975389   0.3400
                 2172928   0.0290
                 2963084   0.0129
                 3971136   0.0072
             </tableData>
					</table>
				</product>
			</function>
			<function name="aero/force/Side_yaw_rate">
				<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>
					<value> 0.4780 </value>
				</product>
			</function>
			<function name="aero/force/Side_rudder">
				<description>Side force due to rudder</description>
				<product>
					<property>aero/qbar-induced-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>fcs/rudder-pos-rad</property>
					<value> 0.1465 </value>
				</product>
			</function>
		</axis>
		<axis name="PITCH">
			<function name="aero/moment/Pitch_propwash">
				<description>Pitch moment due to propeller induced velocity</description>
				<product>
					<property>propulsion/engine[0]/thrust-coefficient</property>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<table>
						<independentVar lookup="row">aero/alpha-rad</independentVar>
						<independentVar lookup="column">fcs/flap-pos-deg</independentVar>
						<tableData>
                     0.0     60.0
              -0.01  0.000   0.000
               0.00 -0.033  -0.088
               0.34 -0.157  -0.420
               0.44  0.000   0.000
            </tableData>
					</table>
				</product>
			</function>
			<function name="aero/moment/Pitch_alpha">
				<description>Pitch moment due to alpha</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/cbarw-ft</property>
					<property>aero/alpha-rad</property>
					<value> -0.5000 </value>
				</product>
			</function>
			<function name="aero/moment/Pitch_elevator">
				<description>Pitch moment due to elevator</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/cbarw-ft</property>
					<property>fcs/elevator-pos-rad</property>
					<table>
						<independentVar lookup="row">velocities/mach</independentVar>
						<tableData>
              0.0    -1.3000
              2.0    -0.2750
            </tableData>
					</table>
				</product>
			</function>
			<function name="aero/moment/Pitch_damp">
				<description>Pitch moment due to pitch rate</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/cbarw-ft</property>
					<property>aero/ci2vel</property>
					<property>velocities/q-aero-rad_sec</property>
					<value> -12.0000 </value>
				</product>
			</function>
			<function name="aero/moment/Pitch_alphadot">
				<description>Pitch moment due to alpha rate</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/cbarw-ft</property>
					<property>aero/ci2vel</property>
					<property>aero/alphadot-rad_sec</property>
					<value> -7.0000 </value>
				</product>
			</function>
		</axis>
		<axis name="ROLL">
			<function name="aero/moment/Roll_differential_propwash">
				<description>Roll moment due to differential propwash</description>
				<product>
					<property>propulsion/engine[0]/thrust-coefficient</property>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>aero/alpha-rad</property>
					<value> 0.1243 </value>
				</product>
			</function>
			<function name="aero/moment/Roll_beta">
				<description>Roll moment due to beta</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>aero/beta-rad</property>
					<property>fcs/gear-no-wow</property>
					<table>
						<independentVar lookup="row">aero/alpha-rad</independentVar>
						<independentVar lookup="column">aero/Re</independentVar>
						<tableData>
                          1975389  2172928  2963084  3971136
                 -0.0349  -0.5845  -0.0649  -0.0380  -0.0285
                  0.3491  -0.5845  -0.0649  -0.0380  -0.0285
             </tableData>
					</table>
				</product>
			</function>
			<function name="aero/moment/Roll_damp">
				<description>Roll moment due to roll rate</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>aero/bi2vel</property>
					<property>velocities/p-aero-rad_sec</property>
					<value> -0.5841 </value>
				</product>
			</function>
			<function name="aero/moment/Roll_yaw">
				<description>Roll moment due to yaw rate</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>aero/bi2vel</property>
					<property>velocities/r-aero-rad_sec</property>
					<table>
						<independentVar lookup="row">aero/alpha-rad</independentVar>
						<independentVar lookup="column">aero/Re</independentVar>
						<tableData>
                          1975389  2172928  2963084  3971136
                 -0.0349   0.0417   0.0417   0.0417   0.0417
                  0.3491   4.6716   0.4936   0.4936   0.4936
             </tableData>
					</table>
				</product>
			</function>
			<function name="aero/moment/Roll_left_flaperon">
				<description>Roll moment due to left flaperon</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>fcs/left-flaperon-pos-norm</property>
					<value> 0.02 </value>
					<!-- (ported from c172p:) the ailerons are less efficient and even create an opposite roll moment close to stall because deflection down makes the wing portion stall-->
					<table>
						<independentVar lookup="row">aero/alpha-deg</independentVar>
						<tableData>
						15    1
						16    0.3
						18   -0.1
						</tableData>
					</table>
				</product>
			</function>
			<function name="aero/moment/Roll_right_flaperon">
				<description>Roll moment due to right flaperon</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>fcs/right-flaperon-pos-norm</property>
					<value> -0.02 </value>
					<!-- (ported from c172p:) the ailerons are less efficient and even create an opposite roll moment close to stall because deflection down makes the wing portion stall-->
					<table>
						<independentVar lookup="row">aero/alpha-deg</independentVar>
						<tableData>
						15    1
						16    0.3
						18   -0.1
						</tableData>
					</table>
				</product>
			</function>
			<function name="aero/moment/Roll_rudder">
				<description>Roll moment due to rudder</description>
				<product>
					<property>aero/qbar-induced-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>fcs/rudder-pos-rad</property>
					<value> 0.0100 </value>
				</product>
			</function>
		</axis>
		<axis name="YAW">
			<!-- Stall initiator -->
			<!--<function name="aero/moment/Yaw_alpha">
       <description>Yaw moment due to alpha</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>aero/alpha-rad</property>
           <property>fcs/gear-no-wow</property>
           <table>
             <independentVar lookup="row">aero/beta-rad</independentVar>
             <independentVar lookup="column">aero/Re</independentVar>
             <tableData>
                          1975389  2172928
                 -0.3491  -1.0000   0.0000
                  0.3491   1.0000   0.0000
             </tableData>
           </table>
       </product>
    </function>-->
			<function name="aero/moment/Yaw_beta">
				<description>Yaw moment due to beta</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>aero/beta-rad</property>
					<value> 0.1149 </value>
				</product>
			</function>
			<function name="aero/moment/Yaw_roll_rate">
				<description>Yaw moment due to roll rate</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>aero/bi2vel</property>
					<property>velocities/p-rad_sec</property>
					<table>
						<independentVar lookup="row">aero/Re</independentVar>
						<tableData>
                 1975389  -0.1710
                 2172928  -0.0146
                 2963084  -0.0065
                 3971136  -0.0036
             </tableData>
					</table>
				</product>
			</function>
			<function name="aero/moment/Yaw_damp">
				<description>Yaw moment due to yaw rate</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>aero/bi2vel</property>
					<property>velocities/r-aero-rad_sec</property>
					<value> -0.1313 </value>
				</product>
			</function>
			<function name="aero/moment/Yaw_rudder">
				<description>Yaw moment due to rudder</description>
				<product>
					<property>aero/qbar-induced-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>fcs/rudder-pos-rad</property>
					<value> -0.078 </value>
				</product>
			</function>
			<function name="aero/moment/Yaw_left_flaperon">
				<description>Yaw moment due to left flaperon</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>fcs/left-flaperon-pos-norm</property>
					<value> 0.010 </value>
				</product>
			</function>
			<function name="aero/moment/Yaw_right_flaperon">
				<description>Yaw moment due to right flaperon</description>
				<product>
					<property>aero/qbar-psf</property>
					<property>metrics/Sw-sqft</property>
					<property>metrics/bw-ft</property>
					<property>fcs/right-flaperon-pos-norm</property>
					<value> -0.010 </value>
				</product>
			</function>
		</axis>
	</aerodynamics>
	<external_reactions>
 </external_reactions>
</fdm_config>
