<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="General Dynamics F-22A" version="2.0" release="PRODUCTION"
    xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
    xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

    <fileheader>
        <author>Brian Mills </author>
        <filecreationdate>2009-05-24</filecreationdate>
        <version>$Revision: 1.38 $</version>
        <description>Models an F-22A Raptor</description>
        <license>
            <licenseName>GPL (General Public License)</licenseName>
            <licenseURL>http://www.gnu.org/licenses/gpl.html</licenseURL>
        </license>
        <note>
            This model was created using data that is, or has been, publically
            available by means of technical reports, textbooks, image graphs or
            published code. This aircraft description file is in no way related
            to the manufacturer of the real aircraft.
            Neither the name of (any of) the authors nor the names of (any of) the
            manufacturers may be used to endorse or promote products derived from
            this file.
    
            The data is provided ''as is'' and any express or implied
            warranties, including, but not limitted to the implied warranties of
            merchantability and fitness for a particular purpose are disclaimed.
        </note>
    </fileheader>
    
    <metrics>
        <wingarea unit="FT2"> 840.0 </wingarea>
        <wingspan unit="FT"> 44.49 </wingspan>
        <chord unit="FT"> 23.06 </chord>
        <htailarea unit="FT2"> 238.9 </htailarea>
        <htailarm unit="FT"> 18.66 </htailarm>
        <vtailarea unit="FT2"> 158.2 </vtailarea>
        <vtailarm unit="FT"> 0 </vtailarm>
        <location name="AERORP" unit="IN">
            <x> 417.6 </x>
            <y> 0 </y>
            <z> 0 </z>
        </location>
        <location name="EYEPOINT" unit="IN">
            <x> 148.8 </x>
            <y> 0 </y>
            <z> 38 </z>
        </location>
        <location name="VRP" unit="IN">
            <x> 100 </x>
            <y> 0 </y>
            <z> 0 </z>
        </location>
    </metrics>

    <mass_balance>
        <ixx unit="SLUG*FT2"> 56005 </ixx>
        <iyy unit="SLUG*FT2"> 280766 </iyy>
        <izz unit="SLUG*FT2"> 354090 </izz>
        <ixz unit="SLUG*FT2"> 713 </ixz>
        <emptywt unit="LBS"> 43430 </emptywt>
        <location name="CG" unit="IN">
            <x> 445.7 </x>
            <y> 0 </y>
            <z> -18.6 </z>
        </location>
        <pointmass name="Pilot">
            <weight unit="LBS"> 230 </weight>
            <location name="POINTMASS" unit="IN">
                <x> 148.8 </x>
                <y> 0 </y>
                <z> 20 </z>
            </location>
        </pointmass>
    </mass_balance>
    
    <ground_reactions>
        <contact type="BOGEY" name="NOSE_LG">
            <location unit="IN">
                <x> 96.7 </x>
                <y> 0 </y>
                <z> -89.3 </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"> 18603.4 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 6201.1 </damping_coeff>
            <max_steer unit="DEG"> 80 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable>1</retractable>
        </contact>
        <contact type="BOGEY" name="LEFT_MLG">
            <location unit="IN">
                <x> 468.8 </x>
                <y> -48 </y>
                <z> -89.3 </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"> 82011.2 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 22402.2 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> LEFT </brake_group>
            <retractable>1</retractable>
        </contact>
        <contact type="BOGEY" name="RIGHT_MLG">
            <location unit="IN">
                <x> 468.8 </x>
                <y> 48 </y>
                <z> -89.3 </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"> 82011.2 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 22402.2 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> RIGHT </brake_group>
            <retractable>1</retractable>
        </contact>
    </ground_reactions>

    <propulsion>
        <engine file="F119-PW-1">
            <location unit="IN">
                <x> 684.131 </x>
                <y> -20 </y>
                <z> 0 </z>
            </location>
            <orient unit="DEG">
                <roll> 0.0 </roll>
                <pitch> 0 </pitch>
                <yaw> 0 </yaw>
            </orient>
            <feed>0</feed>
            <feed>1</feed>
            <thruster file="direct">
                <location unit="IN">
                    <x> 684.131 </x>
                    <y>-20 </y>
                    <z> 0 </z>
                </location>
                <orient unit="DEG">
                    <roll> 0.0 </roll>
                    <pitch> 0.0 </pitch>
                    <yaw> 0.0 </yaw>
                </orient>
            </thruster>
        </engine>
        <engine file="F119-PW-1">
            <location unit="IN">
                <x> 684.131 </x>
                <y> 20 </y>
                <z> 0 </z>
            </location>
            <orient unit="DEG">
                <roll> 0.0 </roll>
                <pitch> 0 </pitch>
                <yaw> 0 </yaw>
            </orient>
            <feed>0</feed>
            <feed>1</feed>
            <thruster file="direct">
                <location unit="IN">
                    <x> 684.131 </x>
                    <y> 20 </y>
                    <z> 0 </z>
                </location>
                <orient unit="DEG">
                    <roll> 0.0 </roll>
                    <pitch> 0.0 </pitch>
                    <yaw> 0.0 </yaw>
                </orient>
            </thruster>
        </engine>
        <tank type="FUEL">
            <location unit="IN">
                <x> 446.478 </x>
                <y> -36 </y>
                <z> -18.6033 </z>
            </location>
            <capacity unit="LBS"> 9350 </capacity>
            <contents unit="LBS"> 9350 </contents>
        </tank>
        <tank type="FUEL">
            <location unit="IN">
                <x> 446.478 </x>
                <y> 36 </y>
                <z> -18.6033 </z>
            </location>
            <capacity unit="LBS"> 9350 </capacity>
            <contents unit="LBS"> 9350 </contents>
        </tank>
    </propulsion>

    <flight_control name="F-22 FC">

        <!-- Declare some interface properties -->
<!--        <property>fcs/alpha-norm</property>
        <property>fcs/tvc-pos-norm</property>
        <property>fcs/tvc-pos-rad</property>
        <property>fcs/thrust-norm</property>        
        <property>fcs/lef-pos-rad</property>
        <property>fcs/lef-pos-norm</property>
        <property>fcs/throttle-override</property>
        <property>fcs/speedbrake-aileron</property>
        <property>fcs/speedbrake-aileron-right</property>
        <property>fcs/speedbrake-rudder</property>
        <property>fcs/speedbrake-flap</property>
        <property>fcs/yaw-rate-integrator</property>
        <property>fcs/pitch-rate-integrator</property>
        <property>fcs/tvc-inhibit</property> -->

        <channel name="Lateral">

            <!-- Normalize the u-velocity to m/s-->
            <pure_gain name="fcs/u-velocity-norm">
                <input>velocities/u-fps</input>
                <gain>0.3048</gain>
            </pure_gain>

            <summer name="fcs/aileron-cmd-limiter">
                <input>fcs/aileron-cmd-norm</input>
                <input>fcs/roll-trim-cmd-norm</input>
                <clipto>
                    <min>-1</min>
                    <max>1</max>
                </clipto>
            </summer>
            
            <!-- Stick filter -->
            <lag_filter name="fcs/roll-cmd-filter">
                <input>fcs/aileron-cmd-limiter</input>
                <c1>10</c1>
                </lag_filter>

            <!-- Limit roll rate command in radians based on altitude, mach and AoA-->
            <fcs_function name="fcs/roll-cmd-limit">
                <function>
                    <table>
                        <independentVar lookup="column">velocities/mach</independentVar>
                        <independentVar lookup="row">aero/alpha-deg</independentVar>
                        <independentVar lookup="table">position/h-sl-ft</independentVar>
                        <tableData breakPoint="0">
                                   0      0.2    0.4    0.6    0.8    1.0    1.2    1.4    1.6
                            -90    0.6    0.6    0.6    0.6    0.6    0.6    0.6    0.6    0.6
                            -25    0.6    0.6    0.6    0.6    0.6    0.6    0.6    0.6    0.6
                            -20    0.6    0.85   1      1      1      1      1      1      1
                            -15    0.6    0.85   1.5    1.5    1.5    1.5    1.5    1.5    1.5
                            -10    0.6    1      2.5    3.14   3.14   3.14   3.14   2.617  2.1
                              0    0.6    1.5    2.5    3.66   4      4      3.14   2.617  2.1
                             10    0.6    1      2.5    3.14   3.14   3.14   3.14   2.617  2.1
                             15    0.6    0.85   2.5    2.617  2.617  2.617  2.617  2.617  2.1
                             20    0.6    0.85   2.1    2.1    2.1    2.1    2.1    2.1    2.1
                             25    0.6    0.85   1.5    1.5    1.5    1.5    1.5    1.5    1.5
                             30    0.6    0.85   1.3    1.3    1.3    1.3    1.3    1.3    1.3
                             35    0.6    0.85   1      1      1      1      1      1      1
                             40    0.4    0.4    0.4    0.4    0.4    0.4    0.4    0.4    0.4
                             45    0.4    0.4    0.4    0.4    0.4    0.4    0.4    0.4    0.4
                            180    0.4    0.4    0.4    0.4    0.4    0.4    0.4    0.4    0.4
                        </tableData>
                        <tableData breakPoint="30000">
                                   0      0.2    0.4    0.6    0.8    1.0    1.2    1.4    1.6    
                            -90    0.6    0.6    0.6    0.6    0.6    0.6    0.6    0.6    0.6
                            -25    0.6    0.6    0.6    0.6    0.6    0.6    0.6    0.6    0.6
                            -20    0.6    0.85   1      1      1      1      1      1      1
                            -15    0.6    0.85   1.5    1.5    1.5    1.5    1.5    1.5    1.5
                            -10    0.6    0.85   2.5    3.14   3.14   3.14   3.14   2.617  2.1
                              0    0.6    0.85   2.5    3.66   4      4      3.14   2.617  2.1
                             10    0.6    0.85   2.5    3.14   3.14   3.14   3.14   2.617  2.1
                             15    0.6    0.85   2.5    2.617  2.617  2.617  2.617  2.617  2.1    
                             20    0.6    0.85   2.1    2.1    2.1    2.1    2.1    2.1    2.1
                             25    0.6    0.85   1.5    1.5    1.5    1.5    1.5    1.5    1.5
                             30    0.6    0.85   1.3    1.3    1.3    1.3    1.3    1.3    1.3
                             35    0.6    0.85   1      1      1      1      1      1      1
                             40    0.4    0.4    0.4    0.4    0.4    0.4    0.4    0.4    0.4
                             45    0.4    0.4    0.4    0.4    0.4    0.4    0.4    0.4    0.4
                            180    0.4    0.4    0.4    0.4    0.4    0.4    0.4    0.4    0.4
                        </tableData>
                        <tableData breakPoint="70000">
                                   0      0.2    0.4    0.6    0.8    1.0    1.2    1.4    1.6    
                            -90    0.6    0.6    0.6    0.6    0.6    0.6    0.6    0.6    0.6
                            -25    0.6    0.6    0.6    0.6    0.6    0.6    0.6    0.6    0.6
                            -20    0.6    0.85   1      1      1      1      1      1      1
                            -15    0.6    0.85   1      1.25   1.5    1.5    1.5    1.5    1.5
                            -10    0.6    0.85   1.5    1.5    2      2.25   2.25   2.25   2
                              0    0.6    0.85   1.5    2      2.5    2.5    2.75   2.75   2.5
                             10    0.6    0.85   1.5    1.5    2      2.25   2.25   2.25   2
                             15    0.6    0.85   1.5    2      2      2      2      2      2    
                             20    0.6    0.85   1      1.25   1.5    2      2      2      2
                             25    0.6    0.85   1      1.25   1.5    1.5    1.5    1.5    1.5
                             30    0.6    0.85   1      1      1.3    1.3    1.3    1.3    1.3
                             35    0.6    0.85   1      1      1      1      1      1      1
                             40    0.4    0.4    0.4    0.4    0.4    0.4    0.4    0.4    0.4
                             45    0.4    0.4    0.4    0.4    0.4    0.4    0.4    0.4    0.4
                            180    0.4    0.4    0.4    0.4    0.4    0.4    0.4    0.4    0.4
                        </tableData>
                    </table>
                </function>
            </fcs_function>

            <!-- Calculate the normalized commanded roll rate absolutely limited to +230 deg/s -230 deg/s--> 
            <pure_gain name="fcs/roll-rate-cmd">
                <input>fcs/roll-cmd-filter</input>
                <gain>fcs/roll-cmd-limit</gain>
                  <clipto>
                    <min>-4</min>
                    <max>4</max>
                </clipto>
            </pure_gain>

            <deadband name="fcs/roll-windup-trigger">
                <input>fcs/roll-rate-integrator</input>
                <width>8</width>
                <clipto>
                    <min>-4</min>
                    <max>4</max>
                </clipto>
            </deadband>            

            <summer name="fcs/roll-rate-error">
                <input>fcs/roll-rate-cmd</input>
                <input>-velocities/p-aero-rad_sec</input>
                <input>-fcs/roll-windup-trigger</input>
            </summer>

            <integrator name="fcs/roll-rate-integrator">
                <!--trigger>fcs/aileron-int-trigger</trigger-->
                <input>fcs/roll-rate-error</input>
                <c1> 1 </c1>
                <clipto>
                    <min>-4</min>
                    <max>4</max>
                </clipto>    
            </integrator>

            <!-- Normalize the v-velocity to m/s-->
            <pure_gain name="fcs/v-velocity-norm">
                <input>velocities/v-fps</input>
                <gain>0.3048</gain>
            </pure_gain>

            <pure_gain name="fcs/rudder-cmd-limiter">
                <input>fcs/rudder-cmd-norm</input>
                <gain> 1.0 </gain>
                <clipto>
                    <min>-1</min>
                    <max>1</max>
                </clipto>
            </pure_gain>

            <!-- Rudder pedal filter -->
            <lag_filter name="fcs/rudder-cmd-filter">
                <input>fcs/rudder-cmd-limiter</input>
                <c1>10</c1>
            </lag_filter>

            <!-- Limit yaw rate command in radians based on mach and altitude -->
            <fcs_function name="fcs/yaw-rate-limit">
                <function>
                    <table>
                        <independentVar lookup="row">velocities/mach</independentVar>
                        <independentVar lookup="column">position/h-sl-ft</independentVar>
                        <tableData>
                                  0      36000
                            0    -0.436     -0.436    
                            0.4  -0.349     -0.349
                            0.8  -0.1745    -0.1745
                            1.0  -0.1       -0.1
                            2.0  -0.1       -0.1
                        </tableData>
                    </table>
                </function>
            </fcs_function>

            <pure_gain name="fcs/yaw-rate-cmd">
                <input>fcs/rudder-cmd-filter</input>
                <gain>fcs/yaw-rate-limit</gain>
            </pure_gain>

            <!-- washout filter to fullfill handling qualities-->
            <washout_filter name="fcs/yaw-rate-filter">
                <input>velocities/r-aero-rad_sec</input>
                <c1> 1.2 </c1>
            </washout_filter>

            <deadband name="fcs/yaw-windup-trigger">
                <input>fcs/yaw-rate-integrator</input>
                <width>0.872</width>
                <clipto>
                    <min>-0.436</min>
                    <max>0.436</max>
                </clipto>
            </deadband>

            <summer name="fcs/yaw-rate-error">
                <input> -fcs/yaw-rate-filter    </input>
                <input> -fcs/yaw-windup-trigger </input>
                <input>  fcs/yaw-rate-cmd       </input>
            </summer>

            <integrator name="fcs/yaw-rate-integrator">
                <!--trigger>fcs/rudder-int-trigger</trigger-->
                <input>fcs/yaw-rate-error</input>
                <c1> 1 </c1>
                <clipto>
                    <min>-0.436</min>
                    <max>0.436</max>
                </clipto>
                <output>fcs/yaw-rate-integrator</output>
            </integrator>
            
            <!-- if yaw rate exceeds limits based on rate and mach, then apply opposite rudder-->
            <fcs_function name="fcs/yaw-rate-override">
                <function>
                    <table>
                        <independentVar lookup="row">velocities/r-aero-rad_sec</independentVar>
                        <independentVar lookup="column">velocities/mach</independentVar>
                        <tableData>
                                    0    0.4    0.8    1.0    2.0
                            -0.440    0.872 0.7    0.35    0.2    0.2 
                            -0.436    0    0.7    0.35    0.2    0.2 
                            -0.360    0    0.7    0.35    0.2    0.2
                            -0.349    0    0    0.35    0.2    0.2
                            -0.180    0    0    0.35    0.2    0.2
                            -0.1745    0    0    0    0.2    0.2
                            -0.11        0    0    0    0.2    0.2
                            -0.1        0    0    0    0    0
                             0        0    0    0    0    0
                             0.1        0    0    0    0    0
                             0.11        0    0    0    -0.2    -0.2
                             0.1745    0    0    0    -0.2    -0.2
                             0.18        0    0    -0.35    -0.2    -0.2
                             0.349        0    0    -0.35    -0.2    -0.2
                             0.36        0    -0.7    -0.35    -0.2    -0.2
                             0.436        0    -0.7    -0.35    -0.2    -0.2
                             0.440        -0.872 -0.7    -0.35    -0.2    -0.2
                        </tableData>
                    </table>
                </function>
            </fcs_function>

            <summer name="fcs/yaw-cmd-summer">
                <input>fcs/yaw-rate-integrator</input>
                <input>fcs/yaw-rate-override</input>
            </summer>

            <!-- LQR Tracker Integral aileron roll-rate control-->
            <fcs_function name="fcs/roll-cmd">
                <function>
                    <product>
                        <sum>
                            <product>
                                <table>
                                    <independentVar lookup="row">velocities/vc-kts</independentVar>
                                    <independentVar lookup="column">position/h-sl-ft</independentVar>
                                    <tableData>
                                              0     33000     50000
                                         160  0.5       0.35      0.3
                                         270  0.5       0.35      0.3
                                         400  0.45      0.4       0.3
                                         500  0.45      0.4       0.35
                                         580  0.5       0.45      0.35
                                        1000  0.5       0.45      0.4
                                    </tableData>
                                </table>
                                <property> fcs/roll-rate-integrator </property>
                                <value> -1 </value>
                                <table>
                                    <independentVar lookup="row">velocities/vc-kts</independentVar>
                                    <independentVar lookup="column">position/h-sl-ft</independentVar>
                                    <tableData>
                                                 0      33000      50000
                                        160    -28.4059   -31.1627   -31.1627
                                        270    -30.9146   -32.6575   -32.6575
                                        330    -35.9146   -32.6575   -32.6575
                                        400    -44.4687   -38.7651   -38.7651
                                        580    -44.2746   -36.5662   -36.5662
                                        700    -39.0735   -34.9842   -34.9842
                                    </tableData>
                                </table>
                            </product>
                            <product>
                                <property> fcs/v-velocity-norm </property>
                                <value> 0 </value>
                                <table>
                                    <independentVar lookup="row">velocities/vc-kts</independentVar>
                                    <independentVar lookup="column">position/h-sl-ft</independentVar>
                                    <tableData>
                                              0       33000      50000
                                        160  -0.0494     -0.0266    -0.0266
                                        270   0.0067     -0.0160    -0.0160
                                        330   0.0067     -0.0160    -0.0160
                                        400  -0.1082     -0.0108    -0.0108
                                        580  -0.0104     -0.0091    -0.0091
                                        700  -0.0095     -0.0118    -0.0118
                                    </tableData>
                                </table>
                            </product>
                            <product>
                                <!--table>
                                    <independentVar lookup="row">velocities/vc-kts</independentVar>
                                    <independentVar lookup="column">position/h-sl-ft</independentVar>
                                    <tableData>
                                              0   33000    50000
                                        160   1       1.5      2
                                        270   1       1.35     1.75
                                        400   1       1.2      1.5
                                        500   1.0     1.1      1.0
                                        580   1.0     1.0      1.0
                                        1000  1.0     1.0      1.0
                                    </tableData>
                                </table-->
                                <property>velocities/p-aero-rad_sec</property>
                                <value>-.35</value>
                                <table>
                                    <independentVar lookup="row">velocities/vc-kts</independentVar>
                                    <independentVar lookup="column">position/h-sl-ft</independentVar>
                                    <tableData>
                                              0      33000      50000
                                        160  11.7952    13.4573    13.4573
                                        270  11.9041    13.1381    13.1381
                                        330  11.9041    13.1381    13.1381
                                        400  12.0644    10.6808    10.6808
                                        580  11.0366    10.7511    10.7511
                                        700   9.3909    10.8556    10.8556
                                    </tableData>
                                </table>
                            </product>
                        </sum>
                        <!--table>
                            <independentVar lookup="row">velocities/vc-kts</independentVar>
                            <independentVar lookup="column">aero/alpha-rad</independentVar>
                            <tableData>
                                    -1    -0.25    0  0.25 0.5    1    2    3
                                160    1.5    1.25    1 1.25 1.5    2    2.5    3
                                270    1.5    1.25    1 1.25 1.5    2    2.5    3
                                400    1.5    1.25    1 1.25 1.5    2    2.5    3
                                500    1.5    1.15    1 1.15 1.35    2    2.5    3
                                580    1.5    1.15    1 1.15 1.35    2    2.5    3
                                1000    1.5    1.15    1 1.15 1.35    2    2.5    3

                            </tableData>
                        </table-->
                    </product>
                </function>    
                <clipto>
                    <min>-5</min>
                    <max>5</max>
                </clipto>        
            </fcs_function>

            <aerosurface_scale name="fcs/roll-reg-scale">
                <input> fcs/roll-cmd </input>
                <domain>
                    <min> -5 </min>
                    <max> 5 </max>
                </domain>
                <range>
                    <min> -1 </min>
                    <max> 1 </max>
                </range>
            </aerosurface_scale >

            <actuator name="fcs/aileron-act">
                <input> fcs/roll-reg-scale</input>
                <lag> 0.00 </lag>
                <rate_limit> 2.29 </rate_limit>
                <clipto>
                    <min> -1 </min>
                    <max> 1 </max>
                </clipto>
            </actuator>

            <summer name="fcs/left-aileron-out">
                <input>fcs/aileron-act</input>
                <input>fcs/speedbrake-aileron</input>
                <clipto>
                    <min> -1 </min>
                    <max> 1 </max>
                </clipto>
                <output>fcs/left-aileron-pos-norm</output>
            </summer>

            <aerosurface_scale name="fcs/left-aileron-control">
                <input>fcs/aileron-act</input>
                <range>
                    <min>-0.436</min>
                    <max>0.436</max>
                </range>
                <output>fcs/left-aileron-pos-rad</output>
            </aerosurface_scale>

            <pure_gain name="fcs/left-aileron-neg">
                <input>fcs/aileron-act</input>
                <gain>-1</gain>
            </pure_gain>

            <summer name="fcs/right-aileron-out">
                <input>fcs/left-aileron-neg</input>
                <input>fcs/speedbrake-aileron-right</input>
                <clipto>
                    <min> -1 </min>
                    <max> 1 </max>
                </clipto>
                <output>fcs/right-aileron-pos-norm</output>
            </summer>

            <aerosurface_scale name="fcs/right-aileron-control">
                <input>fcs/left-aileron-neg</input>
                <range>
                    <min>-0.436</min>
                    <max>0.436</max>
                </range>
                <output>fcs/right-aileron-pos-rad</output>
            </aerosurface_scale>

            <!-- LQR Tracker Integral rudder yaw-rate control-->
            <fcs_function name="fcs/yaw-cmd">
                <function>
                    <product>
                        <sum>                    
                            <product>
                                <property>fcs/yaw-cmd-summer</property>
                                <value>-0.2</value>
                                <table>
                                    <independentVar lookup="row">velocities/vc-kts</independentVar>
                                    <independentVar lookup="column">position/h-sl-ft</independentVar>
                                    <tableData>
                                              0      33000     50000
                                        160  22.1027    22.1741   22.1741
                                        270  22.1775    15.7518   15.7518
                                        400  14.0894    14.0894   14.0894
                                        580  12.8629    12.8629   12.8629
                                        700  14.8347    12.8631   12.8631
                                    </tableData>
                                </table>
                            </product>
                            <product>
                                <property>fcs/yaw-rate-filter</property>
                                <value>-0.2</value>
                                <table>
                                    <independentVar lookup="row">velocities/vc-kts</independentVar>
                                    <independentVar lookup="column">position/h-sl-ft</independentVar>
                                    <tableData>
                                               0      33000      50000
                                        160  -21.4844   -29.9948   -29.9948
                                        270  -19.5573   -17.5259   -17.5259
                                        400  -13.6930   -13.6930   -13.6930
                                        580   -9.6423    -9.6423    -9.6423
                                        700   -7.7903    -6.1197    -6.1197
                                    </tableData>
                                </table>
                            </product>
                        </sum>
                        <table>
                            <independentVar lookup="row">velocities/vc-kts</independentVar>
                            <independentVar lookup="column">position/h-sl-ft</independentVar>
                            <tableData>
                                     0   33000   50000
                                160  1       1.2     1.2
                                270  1       1.1     1.1
                                400  0.5     0.55    0.6
                                580  0.3     0.35    0.4
                                700  0.2     0.25    0.3
                            </tableData>
                        </table>
                        <table>
                            <independentVar lookup="row">aero/alpha-deg</independentVar>
                            <independentVar lookup="column">position/h-sl-ft</independentVar>
                            <tableData>
                                     0    33000    50000
                                -60  3        3.5      4
                                -40  2        2.5      3
                                -20  1.5      1.75     2
                                  0  0.7      0.8      0.9
                                 20  1.75     2        2.5
                                 40  2.5      3        3.5
                                 60  3        3.5      4
                                 80  3.5      4        5
                            </tableData>
                        </table>
                    </product>
                </function>
                <clipto>
                    <min>-5</min>
                    <max>5</max>
                </clipto>    
            </fcs_function>

            <aerosurface_scale name="fcs/yaw-reg-scale">
                <input> fcs/yaw-cmd </input>
                <domain>
                    <min> -5 </min>
                    <max> 5 </max>
                </domain>
                <range>
                    <min> -1 </min>
                    <max> 1 </max>
                </range>
            </aerosurface_scale >
        
            <actuator name="fcs/rudder-act">
                <input> fcs/yaw-reg-scale</input>
                <lag> 0 </lag>
                <rate_limit> 2.673 </rate_limit>
                
                <clipto>
                    
                    <min> -1 </min>
                    <max> 1 </max>
                </clipto>
            </actuator>

            <summer name="fcs/rudder-pos-out">
                <input>fcs/rudder-act</input>
                <input>fcs/speedbrake-rudder</input>
                <clipto>
                    <min> -1 </min>
                    <max> 1 </max>
                </clipto>
                <output>fcs/rudder-pos-norm</output>
            </summer>
            
            <aerosurface_scale name="fcs/rudder-position">
                <input>fcs/rudder-act</input>
                <range>
                    <min>-0.5236</min>
                    <max>0.5236</max>
                </range>
                <output>fcs/rudder-pos-rad</output>
            </aerosurface_scale>
        </channel>

        <channel name="Pitch">
            
            <!--
              - accelerations/n-pilot-z-norm has the disadvantage that it
              - has an offset of 1G when positioned horizontal (and -1G
              - when upside down). To calculate the difference between the
              - commanded pitch-rate and actual pitch-rate this offset has
              - to be eliminated. The following function calculates an offset
              - to compensate for the earth's gravity.
              -->
            <fcs_function name="fcs/n-pilot-z-correction">
                <function>
                    <product>
                        <cos>
                            <property>attitude/pitch-rad</property>
                        </cos>
                        <cos>
                            <property>attitude/roll-rad</property>
                        </cos>
                    </product>
                </function>
            </fcs_function>

            <summer name="fcs/g-load-corrected">
                <input>accelerations/n-pilot-z-norm</input>
                <input>-fcs/n-pilot-z-correction</input>
            </summer>

            <pure_gain name="fcs/g-load-norm">
                <input>fcs/g-load-corrected</input>
                <gain>-1.0</gain>
            </pure_gain>

            <!-- Pilot stick filter -->
            <lag_filter name="fcs/stick-filter">
                <input>fcs/elevator-cmd-norm</input>
                <c1>10</c1>
            </lag_filter>

            <!-- Do not allow TVC to operate when gear is down! -->
            <switch name="fcs/tvc-inhibit">
                <default value="1"/>
                <test logic="AND" value="0">
                    gear/gear-pos-norm gt 0
                </test>
                <output>fcs/tvc-inhibit</output>
            </switch>

            <summer name="fcs/elevator-cmd-limiter">
                <input>fcs/stick-filter</input>
                <input>fcs/pitch-trim-cmd-norm</input>
                <clipto>
                    <min>-1</min>
                    <max>0.6</max>
                </clipto>
            </summer>
            
            <!-- Limit pitch rate command based on altitude and mach.  Max of +50/-30 deg/sec command -->
            <fcs_function name="fcs/pitch-cmd-limiter">
                <function>
                    <table>
                        <independentVar lookup="row">velocities/mach</independentVar>
                        <independentVar lookup="column">position/h-sl-ft</independentVar>
                        <tableData>
                                   0      30000      60000
                            0      0.7        0.5236     0.349
                            0.2    0.8727     0.5236     0.349
                            0.4    0.8727     0.5236     0.349
                            0.6    0.8727     0.7        0.349
                            0.8    0.8727     0.7        0.349    
                            1.0    0.7845     0.7        0.4363
                            1.2    0.611      0.611      0.4363
                            1.4    0.611      0.5236     0.349
                            1.6    0.5236     0.4363     0.349
                            1.8    0.4363     0.4363     0.349
                            2.0    0.349      0.349      0.349
                        </tableData>
                    </table>
                </function>
            </fcs_function>

            <pure_gain name="fcs/pitch-rate-cmd">
                <input>fcs/elevator-cmd-limiter</input>
                <gain>-fcs/pitch-cmd-limiter</gain>
            </pure_gain>
            
            <!-- G-limiter based on mach.  +9.5/-3.5 G limit. --> 
            <fcs_function name="fcs/pitch-cmd-g-limiter">
                <function>
                    <table>
                        <independentVar lookup="column">velocities/mach</independentVar>
                        <independentVar lookup="row">fcs/g-load-norm</independentVar>
                        <tableData>
                                    0     0.4   0.8   1.0   1.2   1.4   1.6   1.8   2.0    
                            -3.75   0     0     0     0     0     0     0     0     0
                            -3.5    1     1     1     1     0     0     0     0     0
                            -3.25   1     1     1     1     1     1     0     0     0
                            -3.0    1     1     1     1     1     1     1     1     1
                             0      1     1     1     1     1     1     1     1     1
                             7      1     1     1     1     1     1     1     1     1
                             7.25   1     1     1     1     1    -0.1  -0.1  -0.1  -0.1    
                             7.5    1     1     1     1     1    -0.1  -0.1  -0.1  -0.1
                             7.75   1     1     1     1    -0.1  -0.1  -0.1  -0.1  -0.1
                             8.0    1     1     1     1    -0.1  -0.1  -0.1  -0.1  -0.1
                             8.25   1     1     1     1    -0.1  -0.1  -0.1  -0.1  -0.1
                             8.5    1     1     1     1    -0.1  -0.1  -0.1  -0.1  -0.1
                             8.75   1     1     1     1    -0.1  -0.1  -0.1  -0.1  -0.1
                             9.0    1     1     1     1    -0.1  -0.1  -0.1  -0.1  -0.1
                             9.25   1     1     1     1    -0.1  -0.1  -0.1  -0.1  -0.1
                             9.5    1     1     1     1    -0.1  -0.1  -0.1  -0.1  -0.1
                             9.75  -0.1  -0.1  -0.1  -0.1  -0.1  -0.1   0     0     0
                             10.0  -1    -1    -1    -1    -1    -1    -1    -1    -1    
                        </tableData>
                    </table>
                </function>
            </fcs_function>
    
            <pure_gain name="fcs/g-limiter">
                <input>fcs/pitch-rate-cmd</input>
                <gain>fcs/pitch-cmd-g-limiter</gain>
                <clipto>
                    <min>-0.5236</min>
                    <max>0.8727</max>
                </clipto>
            </pure_gain>
        
            <!--    Limit pitch rate command when gear is down--> 
            <switch name="fcs/gear-down-q-limit">
                <default value="1"/>
                <test logic="AND" value=".3">
                    gear/gear-pos-norm gt 0
                </test>
            </switch>

            <pure_gain name="fcs/q-gear-down-limiter">
                <input>fcs/g-limiter</input>
                <gain>fcs/gear-down-q-limit</gain>
                <clipto>
                    <min>-0.5236</min>
                    <max>0.8727</max>
                </clipto>
            </pure_gain>

            <deadband name="fcs/pitch-windup-trigger">
                <input>fcs/pitch-rate-integrator</input>
                <width>1.4</width>
                <clipto>
                    <min>-0.5236</min>
                    <max>0.8727</max>
                </clipto>
            </deadband>    

            <summer name="fcs/pitch-rate-error">
                <input>fcs/q-gear-down-limiter</input>
                <input>-velocities/q-aero-rad_sec</input>
                <input>-fcs/pitch-windup-trigger</input>
            </summer>

            <integrator name="fcs/pitch-rate-integrator">
                <!--trigger>fcs/pitch-int-trigger</trigger-->
                <input>fcs/pitch-rate-error</input>
                <c1> 1 </c1>
                <clipto>
                    <min>-0.5236</min>
                    <max>0.8727</max>
                </clipto>
                <output>fcs/pitch-rate-integrator</output>
            </integrator>

            <summer name="fcs/pitch-cmd-summer">
                <input>fcs/pitch-rate-integrator</input>
                <!--input>fcs/pitch-rate-override</input-->
            </summer>

            <!-- Normalize the w-velocity to m/s -->
            <pure_gain name="fcs/w-velocity-norm">
                <input>velocities/w-fps</input>
                <gain>0.3048</gain>
            </pure_gain>

            <!-- LQR Tracker Integral elevator pitch rate controller-->
            <fcs_function name="fcs/el-pitch-cmd">
                <function>       
                    <sum>
                        <product>
                            <table>
                                <independentVar lookup="row">velocities/vc-kts</independentVar>
                                <independentVar lookup="column">aero/alpha-deg</independentVar>
                                <tableData>
                                          19  25  35
                                     90    1   1   1
                                    180    1   1   1
                                    200    1   1   1
                                    215    1   1   1
                                    230    1   1   1
                                    380    1   1   1
                                    500    1   1   1
                                    900    1   1   1
                                </tableData>
                            </table>

                            <property>fcs/pitch-cmd-summer</property>
                            <value>-0.5</value>
                            <table>
                                <independentVar lookup="row">velocities/vc-kts</independentVar>
                                <independentVar lookup="column">aero/alpha-deg</independentVar>
                                <tableData>
                                         19       25       35
                                    90   38.8840  25.9906  25.9906
                                    180  38.8840  25.9906  25.9906
                                    200  38.8840  25.9906  25.9906
                                    215  58.8840  25.9906  25.9906
                                    230  81.9605  58.8840  25.9906
                                    380  63.4645  56.8517  34.4889
                                    500  61.1371  58.5955  33.0386
                                    900  48.8597  42.1147  42.1147
                                </tableData>
                            </table>
                        </product>
                        <product>
                            <property>fcs/w-velocity-norm</property>
                            <value>0</value>
                            <table>
                                <independentVar lookup="row">velocities/vc-kts</independentVar>
                                <independentVar lookup="column">aero/alpha-deg</independentVar>
                                <tableData>
                                         19       25       35
                                     90  -0.0231  -0.0119  -0.0119
                                    180  -0.0231  -0.0119  -0.0119
                                    200  -0.0231  -0.0119  -0.0119
                                    215  -0.0231  -0.0119  -0.0119
                                    230  -0.0406  -0.0231  -0.0119
                                    380  -0.0244  -0.0195  -0.0159
                                    500  -0.0115  -0.0085  -0.0061
                                    900  -0.0045  -0.0029  -0.0029
                                </tableData>
                            </table>
                        </product>
                        <product>
                            <table>
                                <independentVar lookup="row">velocities/vc-kts</independentVar>
                                <independentVar lookup="column">aero/alpha-deg</independentVar>
                                <tableData>
                                         19  25  35
                                     90   1   1   1
                                    180   1   1   1
                                    200   1   1   1
                                    215   1   1   1
                                    230   1   1   1
                                    380   1   1   1
                                    500   1   1   1
                                    900   1   1   1
                                </tableData>
                            </table>
                            <property>velocities/q-aero-rad_sec</property>
                            <value>-0.3</value>
                            <table>
                                <independentVar lookup="row">velocities/vc-kts</independentVar>
                                <independentVar lookup="column">aero/alpha-deg</independentVar>
                                <tableData>
                                          19        25        35
                                     90  -34.0297  -19.6316  -19.6316
                                    180  -34.0297  -19.6316  -19.6316
                                    200  -34.0297  -19.6316  -19.6316
                                    215  -44.0297  -19.6316  -19.6316
                                    230  -62.1151  -44.0297  -19.6316
                                    380  -47.3350  -42.1836  -26.0436
                                    500  -45.4195  -43.0593  -24.6616
                                    900  -35.7627  -30.5733  -30.5733
                                </tableData>
                            </table>
                        </product>
                    </sum>
                </function>
                <clipto>
                    <min>-5</min>
                    <max>5</max>
                </clipto>
            </fcs_function>

            <aerosurface_scale name="fcs/el-reg-scale">
                <input> fcs/el-pitch-cmd </input>
                <domain>
                    <min> -5 </min>
                    <max> 5 </max>
                </domain>
                <range>
                    <min> -1 </min>
                    <max> 1 </max>
                </range>
            </aerosurface_scale >

            <actuator name="fcs/elevator-act">
                <input> fcs/el-reg-scale</input>
                <lag> 0.0 </lag>
                <rate_limit> 2 </rate_limit>
                <clipto>
                    <min> -1 </min>
                    <max> 1 </max>
                </clipto>
                <output>fcs/elevator-pos-norm</output>
            </actuator>

            <aerosurface_scale name="fcs/elevator-position">
                <input>fcs/elevator-pos-norm</input>
                <range>
                    <min>-0.5236</min>
                    <max>0.5236</max>
                </range>
                <output>fcs/elevator-pos-rad</output>
            </aerosurface_scale>

            <summer name="fcs/dht-left-pos-rad">
                <input>-fcs/elevator-pos-rad</input>
                <input>-fcs/left-aileron-pos-rad</input>
                <clipto>
                    <min>-0.5236</min>
                    <max>0.5236</max>
                </clipto>
            </summer>

            <summer name="fcs/dht-right-pos-rad">
                <input>fcs/elevator-pos-rad</input>
                <input>fcs/right-aileron-pos-rad</input>
                <clipto>
                    <min>-0.5236</min>
                    <max>0.5236</max>
                </clipto>
            </summer>

            <!-- Reduce TVC gains if AB is on-->
            <switch name="fcs/tvc-gain-select">
                <default value="1"/>
                <test logic="AND" value="0.6">
                    fcs/throttle-pos-norm ge 0.99
                </test>
            </switch>

            <!-- LQR Tracker Integral TVC pitch rate controller-->
            <fcs_function name="fcs/tvc-pitch-cmd">
                <!-- description>thrust vector control lqr regulator</description -->
                <function>
                    <product>
                        <sum>
                            <product>
                                <table>
                                    <independentVar lookup="row">velocities/vc-kts</independentVar>
                                    <independentVar lookup="column">aero/alpha-deg</independentVar>
                                    <tableData>
                                             12    20    30    60
                                         70   0.4   0.4   0.3   0.3
                                        140   0.4   0.4   0.3   0.3
                                        200   0.4   0.45  0.35  0.3
                                        215   0.4   0.45  0.35  0.3
                                        230   0.4   0.45  0.35  0.3
                                        330   0.4   0.45  0.35  0.3
                                        380   0.4   0.4   0.4   0.4
                                        500   0.4   0.4   0.4   0.4
                                        900   0.4   0.4   0.4   0.4
                                    </tableData>
                                </table>
                                <property>fcs/pitch-cmd-summer</property>
                                <value>-1</value>
                                <table>
                                    <independentVar lookup="row">velocities/vc-kts</independentVar>
                                    <independentVar lookup="column">aero/alpha-deg</independentVar>
                                    <independentVar lookup="table">position/h-sl-ft</independentVar>
                                    <tableData breakPoint="-1000">
                                             12       20       30
                                         70  97.6705  95.6705  95.6705
                                        140  97.6705  95.6705  95.6705
                                        200  97.6705  95.6705  95.6705
                                        215  67.9777  95.6705  95.6705
                                        230   0       67.9777  95.6705
                                        330   0        0        0
                                        380   0        0        0
                                        500   0        0        0
                                        900   0        0        0
                                    </tableData>
                                    <tableData breakPoint="30000">
                                             12       20       30
                                        70   97.6705  95.6705  95.6705
                                        140  97.6705  95.6705  95.6705
                                        200  97.6705  95.6705  95.6705
                                        215  67.9777  95.6705  95.6705
                                        230   0       67.9777  95.6705
                                        330   0       49.6594  70.1697
                                        380   0       34.2680  34.2680
                                        500   0        0        0
                                        900   0        0        0
                                    </tableData>
                                    <tableData breakPoint="70000">
                                             12       20       30
                                         70  97.6705  95.6705  95.6705
                                        140  97.6705  95.6705  95.6705
                                        200  97.6705  95.6705  95.6705
                                        215  67.9777  95.6705  95.6705
                                        230   0       67.9777  95.6705
                                        330   0       56.0773  75.1918
                                        380   0       56.0773  75.1918
                                        500   0       49.6594  70.1697
                                        900   0       34.2680  34.2680
                                    </tableData>
                                </table>
                            </product>
                            <product>
                                <property>fcs/w-velocity-norm</property>
                                <value>-0</value>
                                <table>
                                    <independentVar lookup="row">velocities/vc-kts</independentVar>
                                    <independentVar lookup="column">aero/alpha-deg</independentVar>
                                    <independentVar lookup="table">position/h-sl-ft</independentVar>
                                    <tableData breakPoint="-1000">
                                             12       20       30
                                         70  -0.0444  -0.0444  -0.0444
                                        140  -0.0444  -0.0444  -0.0444
                                        200  -0.0444  -0.0444  -0.0444
                                        215  -0.0271  -0.0444  -0.0444
                                        230   0       -0.0271  -0.0444
                                        330   0        0        0
                                        380   0        0        0
                                        500   0        0        0
                                        900   0        0        0
                                    </tableData>
                                    <tableData breakPoint="30000">
                                             12       20       30
                                         70  -0.0444  -0.0444  -0.0444
                                        140  -0.0444  -0.0444  -0.0444
                                        200  -0.0444  -0.0444  -0.0444
                                        215  -0.0271  -0.0444  -0.0444
                                        230   0       -0.0271  -0.0444
                                        330   0       -0.0073  -0.0130
                                        380   0       -0.0024  -0.0024
                                        500   0        0        0
                                        900   0        0        0
                                    </tableData>
                                    <tableData breakPoint="70000">
                                             12       20       30
                                         70  -0.0444  -0.0444  -0.0444
                                        140  -0.0444  -0.0444  -0.0444
                                        200  -0.0444  -0.0444  -0.0444
                                        215  -0.0271  -0.0444  -0.0444
                                        230   0       -0.0271  -0.0444
                                        330   0       -0.0195  -0.0349
                                        380   0       -0.0195  -0.0349
                                        500   0       -0.0073  -0.0130
                                        900   0       -0.0024  -0.0024
                                    </tableData>
                                </table>
                            </product>
                            <product>
                                <table>
                                    <independentVar lookup="row">velocities/vc-kts</independentVar>
                                    <independentVar lookup="column">aero/alpha-deg</independentVar>
                                    <tableData>
                                             12     20     30
                                         70   0.2    0.2    0.2
                                        140   0.2    0.2    0.2
                                        200   0.2    0.2    0.2
                                        215   0.2    0.2    0.2
                                        230   0.225  0.2    0.2
                                        330   0.225  0.225  0.2
                                        380   0.225  0.225  0.2
                                        500   0.225  0.225  0.2
                                        900   0.225  0.225  0.2
                                    </tableData>
                                </table>
                                <property>velocities/q-aero-rad_sec</property>
                                <value>-1</value>
                                <table>
                                    <independentVar lookup="row">velocities/vc-kts</independentVar>
                                    <independentVar lookup="column">aero/alpha-deg</independentVar>
                                    <independentVar lookup="table">position/h-sl-ft</independentVar>
                                    <tableData breakPoint="-1000">
                                              12        20        30
                                         70  -72.1205  -72.1205  -72.1205
                                        140  -72.1205  -72.1205  -72.1205
                                        200  -72.1205  -72.1205  -72.1205
                                        215  -50.7416  -72.1205  -72.1205
                                        230    0       -50.7416  -72.1205
                                        330    0         0         0
                                        380    0         0         0
                                        500    0         0         0
                                        900    0         0         0
                                    </tableData>
                                    <tableData breakPoint="30000">
                                              12        20        30
                                         70  -72.1205  -72.1205  -72.1205
                                        140  -72.1205  -72.1205  -72.1205
                                        200  -72.1205  -72.1205  -72.1205
                                        215  -50.7416  -72.1205  -72.1205
                                        230    0       -50.7416  -72.1205
                                        330    0       -36.1358  -51.7437
                                        380    0       -24.8715  -24.8715
                                        500    0         0         0
                                        900    0         0         0
                                    </tableData>
                                    <tableData breakPoint="70000">
                                              12        20        30
                                         70  -72.1205  -72.1205  -72.1205
                                        140  -72.1205  -72.1205  -72.1205
                                        200  -72.1205  -72.1205  -72.1205
                                        215  -50.7416  -72.1205  -72.1205
                                        230    0       -50.7416  -72.1205
                                        330    0       -41.5043  -56.5934
                                        380    0       -41.5043  -56.5934
                                        500    0       -36.1358  -51.7437
                                        900    0       -24.8715  -24.8715
                                    </tableData>
                                </table>
                            </product>
                        </sum>
                        <value>1</value>
                    </product>
                </function>
                <clipto>
                    <min>-5</min>
                    <max>5</max>
                </clipto>
            </fcs_function>

            <!-- inhibit the tvc if gear down -->
            <pure_gain name="fcs/tvc-gain">
                <input>fcs/tvc-pitch-cmd</input>
                <gain>fcs/tvc-inhibit</gain>
            </pure_gain>

            <!-- reduce tvc gain for burner on -->
            <pure_gain name="fcs/tvc-gain-hi-lo">
                <input>fcs/tvc-gain</input>
                <gain>1</gain>
            </pure_gain>

            <!--TVC used for trim in high altitude supersonic flight-->
            <!-- Uses TVC to reduce trim setting of elevator for reduced drag-->
            <fcs_function name="fcs/ss-trim">
                <function>
                    <product>
                        <sum>
                            <product>
                                <value>7.0626</value>
                                <property>fcs/pitch-rate-integrator</property>
                            </product>
                            <product>
                                <value>-0.0019</value>
                                <property>fcs/u-velocity-norm</property>
                            </product>
                            <product>
                                <value>0.0083</value>
                                <property>fcs/w-velocity-norm</property>
                            </product>
                            <product>
                                <value>-5.1005</value>
                                <property>velocities/q-aero-rad_sec</property>
                            </product>
                        </sum>
                        <table>
                            <independentVar lookup="row">velocities/mach</independentVar>
                            <independentVar lookup="column">position/h-sl-ft</independentVar>
                            <tableData>
                                      45000  50000
                                0.92      0      0
                                0.95      0      1.5    
                                1.00      0      2.5
                                1.10      0      3.5
                                1.15      0      4
                                1.20      0      2.5
                                1.25      0      2
                                1.30      0      1.5
                                1.35      0      1.5
                                1.40      0      1
                                1.45      0      0.9
                                1.50      0      0.75
                                1.55      0      0.7
                                1.60      0      0.65
                                1.7       0      0.6
                                1.8       0      0.6    
                                1.9       0      0.6
                                2.0       0      0.6
                            </tableData>
                        </table>
                    </product>
                </function>
                <clipto>
                    <min>-0.7</min>
                    <max>0.05</max>
                </clipto>
            </fcs_function>

            <!-- In situations where TVC control is not called for, disable TVC SS Trim if manuevering-->
            <fcs_function name="fcs/ss-trim-override">
                <function>
                    <table>
                        <independentVar lookup="row">velocities/q-aero-rad_sec</independentVar>
                        <tableData>
                            -0.15  0
                            -0.1   1
                             0.0   1
                             0.1   1
                             0.15  0
                        </tableData>
                    </table>
                </function>
            </fcs_function>
            
            <!-- inhibit the ss trim if manuevering-->
            <pure_gain name="fcs/ss-trim-gain">
                <input>fcs/ss-trim</input>
                <gain>fcs/ss-trim-override</gain>
            </pure_gain>

            <summer name="fcs/tvc-summer">
                <input>fcs/tvc-gain-hi-lo</input>
                <input>fcs/ss-trim-gain</input>
            </summer>

            <aerosurface_scale name="fcs/tvc-reg-scale">
                <input> fcs/tvc-summer</input>
                <domain>
                    <min> -5 </min>
                    <max> 5 </max>
                </domain>
                <range>
                    <min> -1 </min>
                    <max> 1 </max>
                </range>
            </aerosurface_scale >

            <actuator name="fcs/tvc-act">
                <input> fcs/tvc-reg-scale</input>
                <lag> 0.00 </lag>
                <rate_limit> 2 </rate_limit>
                <clipto>
                    <min> -1 </min>
                    <max> 1 </max>
                </clipto>
                <output>fcs/tvc-pos-norm</output>
            </actuator>
        
            <aerosurface_scale name="fcs/tvc-position">
                <input>fcs/tvc-pos-norm</input>
                <range>
                    <min>-0.349</min>
                    <max>0.349</max>
                </range>
                <output>fcs/tvc-pos-rad</output>
            </aerosurface_scale>

        </channel>

        <channel name="Leading Edge Flap">

            <pure_gain name="fcs/lef-alpha-gain">
                <input>aero/alpha-deg</input>
                <gain>1.38</gain>
            </pure_gain>

            <lead_lag_filter name="fcs/lef-alpha-filter">
                <input>fcs/lef-alpha-gain</input>
                <c1> 2 </c1>
                <c2> 7.25 </c2>
                <c3> 1 </c3>
                <c4> 7.25 </c4>
            </lead_lag_filter>

            <fcs_function name="fcs/lef-transfer-function">
                <function>
                    <description>leading edge flap control function</description>
                    <sum>
                        <property> fcs/lef-alpha-filter </property>
                        <product>
                            <quotient>
                                <property>aero/qbar-psf</property>
                                <property>atmosphere/P-psf</property>
                            </quotient>
                            <value>-9.05</value>     
                        </product>
                        <value>1.45</value>
                    </sum>
                </function>
            </fcs_function>
 
            <pure_gain name="fcs/lef-deg-to-rad">
                <input>fcs/lef-transfer-function</input>
                <gain>0.01745</gain>
                <clipto>
                    <min> -0.001 </min>
                    <max> 0.6108 </max>
                </clipto>
            </pure_gain>
        
            <switch name="fcs/lef-pos">
                <default value="0.0"/>
                <test logic="AND" value="0">
                    gear/wow eq 1
                    gear/gear-pos-norm gt 0
                </test>
                <test value="fcs/lef-deg-to-rad">
                    gear/gear-pos-norm == 0       
                </test>
                <test logic="AND" value="0">
                    velocities/mach gt 0.9
                </test>
            </switch>

            <pure_gain name="fcs/lef-norm">
                <input>fcs/lef-pos</input>
                <gain>1.637197</gain>
            </pure_gain>

            <kinematic name="fcs/lef-control">
                <input>fcs/lef-norm</input>
                <traverse>
                    <setting>
                        <position>-1.0</position>
                        <time>0.55</time>
                    </setting>
                    <setting>
                        <position>1.0</position>
                        <time>0.55</time>
                    </setting>
                </traverse>
                <output>fcs/lef-pos-norm</output>
            </kinematic>

            <aerosurface_scale name="fcs/lef-deg">
                <input>fcs/lef-control</input>
                <domain>
                    <min>-1.0</min>
                    <max>1.0</max>
                </domain>
                <range>
                    <min>0</min>
                    <max>35</max>
                </range>
                <output>fcs/lef-pos-deg</output>
            </aerosurface_scale>

            <aerosurface_scale name="fcs/lef-pos-rad">
                <input>fcs/lef-control</input>
                <domain>
                    <min>-1.0</min>
                    <max>1.0</max>
                </domain>
                <range>
                    <min>0</min>
                    <max>0.6108</max>
                </range>
                <output>fcs/lef-pos-rad</output>
            </aerosurface_scale>

        </channel>

        <channel name="Throttle">

            <!--FADEC function to automatically add throttle in post stall conditions for TVC pitch authority-->
            <fcs_function name="fcs/throttle-adjust">
                <function>
                    <table>
                        <independentVar lookup="column">aero/alpha-deg</independentVar>
                        <independentVar lookup="row">velocities/vc-kts</independentVar>
                        <tableData>
                                    0     20     30     40    50
                               0    0.85   0.9    0.98   1     1
                              50    0.8    0.85   0.95   1     1
                              60    0.75   0.65   0.93   1     1
                              70    0.7    0.55   0.9    0.98  1
                              80    0.65   0.5    0.85   0.98  1
                              90    0.6    0.7    0.8    0.95  1
                             100    0.55   0.65   0.75   0.85  1
                             110    0.4    0.5    0.6    0.65  1
                             120    0.2    0.3    0.35   0.35  1
                             130    0.1    0.2    0.25   0.25  0.5
                            1000    0.1    0.1    0.2    0.25  0.5
                        </tableData>
                    </table>
                </function>
            </fcs_function>

            <pure_gain name="fcs/throttle-gain">
                <input>fcs/throttle-adjust</input>
                <gain>fcs/tvc-inhibit</gain>
                <output>fcs/throttle-override</output>        
            </pure_gain>

            <!-- Throttle filter -->
            <lag_filter name="fcs/throttle-filter">
                <input>fcs/throttle-cmd-norm</input>
                <c1>1</c1>
            </lag_filter>

            <summer name="fcs/t1-summer">
                <input>fcs/throttle-filter</input>
                <!--input>fcs/throttle-override</input-->
                <clipto>
                    <min>fcs/throttle-override</min>
                    <max>1</max>
                </clipto>
            </summer>

            <pure_gain name="fcs/throttle1">
                <input>fcs/t1-summer</input>
                <gain>1.001</gain>
                <output>fcs/throttle-pos-norm</output>
            </pure_gain>

            <!-- Throttle filter -->
            <lag_filter name="fcs/throttle1-filter">
                <input>fcs/throttle-cmd-norm[1]</input>
                <c1>1</c1>
            </lag_filter>

            <summer name="fcs/t2-summer">
                <input>fcs/throttle1-filter</input>
                <!--input>fcs/throttle-override</input-->
                <clipto>
                    <min>fcs/throttle-override</min>
                    <max>1</max>
                </clipto>
            </summer>

            <pure_gain name="fcs/throttle2">
                <input>fcs/t2-summer</input>
                <gain>1.001</gain>
                <output>fcs/throttle-pos-norm[1]</output>
            </pure_gain>

            <!-- Needed to compute TVC pitch moment contribution-->
            <fcs_function name="fcs/thrust-normalized">
                <!-- description>Normalized thrust output</description -->
                <function>
                    <quotient>
                        <property>propulsion/engine/thrust-lbs</property>
                        <value>26550</value>
                    </quotient>
                </function>
                <clipto>
                    <min> 0 </min>
                    <max> 1.5 </max>
                    </clipto>
                <output>fcs/thrust-norm</output>
            </fcs_function>
             
        </channel>
        
        <channel name="Flaps">

            <switch name="fcs/tef-pos">
                <default value="0.0"/>
                <test logic="AND" value="1">
                    velocities/vc-kts lt 180
                    velocities/mach lt 0.4
                </test>
                <test logic="AND" value="0.5235">
                    velocities/vc-kts lt 200
                    velocities/mach lt 0.45
                </test>
                <test logic="AND" value="0.26175">
                    velocities/vc-kts lt 225
                    velocities/mach lt 0.5
                </test>
                <test logic="AND" value="0.13">
                    velocities/vc-kts lt 240
                    velocities/mach lt 0.55
                </test>
                <test logic="AND" value="0.065">
                    velocities/vc-kts lt 255
                    velocities/mach lt 0.6
                </test>
            </switch>

            <pure_gain name="fcs/tef-norm">
                <input>fcs/tef-pos</input>
                <gain>1.91</gain>
            </pure_gain>

            <kinematic name="fcs/flap-controller">
                <input>fcs/tef-norm</input>
                <traverse>
                    <setting>
                        <position>0</position>
                        <time>0</time>
                    </setting>
                    <setting>
                        <position>0.5</position>
                        <time>3.0</time>
                    </setting>
                    <setting>
                        <position>1.0</position>
                        <time>3.0</time>
                    </setting>
                </traverse>
                <output>fcs/flap-pos-norm</output>
            </kinematic>
        
            <summer name="fcs/flap-pos-out">
                <input>fcs/flap-controller</input>
                <input>fcs/speedbrake-flap</input>
                <clipto>
                    <min> 0 </min>
                    <max> 1 </max>
                </clipto>
            </summer>

            <aerosurface_scale name="fcs/tef-pos-deg">
                <input>fcs/flap-pos-out</input>
                <domain>
                    <min>0</min>
                    <max>1.0</max>
                </domain>
                <range>
                    <min>0</min>
                    <max>30</max>
                </range>
                <output>fcs/flap-pos-deg</output>
            </aerosurface_scale>

        </channel>

        <!-- Speedbrake currently borrowed from F-16 -->
        <channel name="Speedbrake">
            <!--
              - To prevent deep stall the Flight Computer commands speedbrake
              - deflection at high angle of attack (alpha) and low speeds. This
              - will provide just enough pitch down moment to keep the aircraft
              - under control.
              -->
            <switch name="fcs/speedbrake-alpha-limiter">
                <default value="0"/>
                <test logic="AND" value="1">
                    aero/alpha-deg ge 120
                    velocities/v-fps le 10
                </test>
            </switch>

            <switch name="fcs/speedbrake-initiate">
                <default value="0"/>
                <test logic="OR" value="1">
                    fcs/speedbrake-alpha-limiter eq 1
                    fcs/speedbrake-cmd-norm eq 1
                </test>
            </switch>

            <kinematic name="fcs/speedbrake-control">
                <input>fcs/speedbrake-initiate</input>
                <traverse>
                    <setting>
                        <position>0</position>
                        <time>0</time>
                    </setting>
                    <setting>
                        <position>60</position>
                        <time>1</time>
                    </setting>
                </traverse>
                <output>fcs/speedbrake-pos-deg</output>
            </kinematic>

            <aerosurface_scale name="fcs/speedbrake-position-normalizer">
                <input>fcs/speedbrake-control</input>
                <domain>
                    <min>0</min>
                    <max>60</max>
                </domain>
                <range>
                    <min>0</min>
                    <max>1</max>
                </range>
                <output>fcs/speedbrake-pos-norm</output>
            </aerosurface_scale>

            <!-- F-22 uses flaps, ailerons and rudders for speedbrakes. Outputs are
                 used to animate surfaces during speedbrake deployment-->
            <pure_gain name="fcs/speedbrake-aileron">
                <input>fcs/speedbrake-pos-norm</input>
                <gain>-1</gain>
                <output>fcs/speedbrake-aileron</output>
            </pure_gain>

            <pure_gain name="fcs/speedbrake-ail-right">
                <input>fcs/speedbrake-pos-norm</input>
                <gain>-1</gain>
                <output>fcs/speedbrake-aileron-right</output>
            </pure_gain>

            <pure_gain name="fcs/speedbrake-rudder">
                <input>fcs/speedbrake-pos-norm</input>
                <gain>1</gain>
                <output>fcs/speedbrake-rudder</output>
            </pure_gain>
        
            <pure_gain name="fcs/speedbrake-flaps">
                <input>fcs/speedbrake-pos-norm</input>
                <gain>1</gain>
                <output>fcs/speedbrake-flap</output>
            </pure_gain>

        </channel>

        <channel name="Landing Gear">

            <kinematic name="fcs/gear-control">
                <input>gear/gear-cmd-norm</input>
                <traverse>
                    <setting>
                        <position>0</position>
                        <time>0</time>
                    </setting>
                    <setting>
                        <position>1</position>
                        <time>5</time>
                    </setting>
                </traverse>
                <output>gear/gear-pos-norm</output>
            </kinematic>

            <scheduled_gain name="fcs/scheduled-steer-pos-deg">
                <input>fcs/steer-cmd-norm</input>
                <table>
                    <independentVar>velocities/vg-fps</independentVar>
                    <tableData>
                        10.0        80
                        50.0        15
                        150.0       2
                    </tableData>
                </table>
                <output>fcs/steer-pos-deg</output>
            </scheduled_gain>

        </channel>

    </flight_control>

    <aerodynamics>

        <!-- Shift the aero ref point aft. F-22 is 10% unstable at subsonic, stable at around Mach 1.2+ -->
        <function name="aero_ref_pt_shift_x">
            <table>
                <independentVar>velocities/mach</independentVar>
                <tableData>
                    0.0000    0.0000
                    0.6000  0.01
                    0.8000  0.025
                    0.9000  0.035
                    1.0000  0.045
                    1.1000  0.1
                    1.2000  0.105    
                    1.3000  0.11
                </tableData>
            </table>
        </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  1.3893
                         0.1000  1.2108
                         0.1500  1.1972
                         0.2000  1.2108
                         0.3000  1.1785
                         0.4000  1.0697
                         0.5000  1.0578
                         0.6000  1.0323
                         0.7000  1.0136
                         0.8000  1.0051
                         0.9000  1.0017
                         1.0000  1.0000
                         1.1000  1.0000
                    </tableData>
                </table>
            </product>
        </function>

        <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  0.5235
                        0.1000  0.4759
                        0.1500  0.5250
                        0.2000  0.5388
                        0.3000  0.5924
                        0.4000  0.6471
                        0.5000  0.6941
                        0.6000  0.7624
                        0.7000  0.8253
                        0.8000  0.8812
                        0.9000  0.9412
                        1.0000  1.0000
                        1.1000  1.0000
                    </tableData>
                </table>
            </product>
        </function>

        <axis name="DRAG">

            <function name="aero/coefficient/CD0">
                <description>Drag_at_zero_lift</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/function/kCDge</property>
                    <table>
                        <independentVar>aero/alpha-rad</independentVar>
                        <tableData>
                            -1.5700    1.5000
                            -0.2600    0.0480
                             0.0000    0.00820
                             0.2600    0.0480
                             1.5700    1.5000
                        </tableData>
                    </table>
                </product>
            </function>

            <function name="aero/coefficient/CDi">
                <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>0.0700</value>
                </product>
            </function>

            <function name="aero/coefficient/CDmach">
                <description>Drag_due_to_mach</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <table>
                        <independentVar>velocities/mach</independentVar>
                        <tableData>
                            0.0000    0.0000
                            0.8100    0.0000
                            1.1000    0.0220
                            1.8000    0.0140
                            2.4000    0.020
                        </tableData>
                    </table>
                </product>
            </function>

            <function name="aero/coefficient/CDflap">
                <description>Drag_due_to_flaps</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/flap-pos-norm</property>
                    <property>aero/function/kCDge</property>
                    <value>0.0750</value>
                </product>
            </function>

            <function name="aero/coefficient/CDgear">
                <description>Drag_due_to_gear</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>gear/gear-pos-norm</property>
                    <value>0.0200</value>
                </product>
            </function>

            <function name="aero/coefficient/CDsb">
                <description>Drag_due_to_speedbrakes</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/speedbrake-pos-norm</property>
                    <value>0.0240</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/function/kCDge</property>
                    <table>
                        <independentVar>aero/beta-rad</independentVar>
                        <tableData>
                            -1.5700    1.2300
                            -0.2600    0.0500
                             0.0000    0.0000
                             0.2600    0.0500
                             1.5700    1.2300
                        </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>aero/function/kCDge</property>
                        <table>
                             <independentVar>fcs/elevator-pos-rad</independentVar>
                             <tableData>
                -0.5236           0.075
                -0.218           0.0375
                0        0.010
                0.218        0.0375
                0.5236        0.077
                 </tableData>
                       </table>
                   </product>
              </function>

         <function name="aero/coefficient/CDDlef">
                   <description>Drag_due_to_leading_edge_flap_deflection</description>
                   <product>
                       <property>aero/qbar-psf</property>
                       <property>metrics/Sw-sqft</property>
                       <property>aero/function/kCDge</property>
            <property>fcs/lef-pos-rad</property>
                        <table>
                             <independentVar>aero/alpha-rad</independentVar>
                             <tableData>
                -0.175  0.003
                    -0.087  0.001
                     0.000  0.000
                     0.087  0.001
                     0.175  0.002
                     0.262  0.004
                     0.349  0.007
                     0.436  0.011
                     0.524  0.015
                     0.611  0.019
                     0.698  0.023
                     0.785  0.024
                 </tableData>
                       </table>
                   </product>
              </function>
        <function name="aero/coefficient/CDq">
                   <description>Drag_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>
                        <table>
                             <independentVar>aero/alpha-rad</independentVar>
                             <tableData>
                -0.175 -1.265
                    -0.087 -2.139
                     0.000 -0.308
                     0.087  1.402
                     0.175  3.369
                     0.262  5.135
                     0.349  6.880
                     0.436  8.060
                     0.524 11.201
                     0.611 13.872
                     0.698 19.217
                     0.785 22.105
                 </tableData>
                       </table>
                   </product>
              </function>
        <function name="aero/coefficient/CDq_Dlef">
                    <description>Drag_due_to_pitch_rate_and_leading_edge_flap_deflection</description>
                   <product>
                       <property>aero/qbar-psf</property>
                       <property>metrics/Sw-sqft</property>
                       <property>velocities/q-aero-rad_sec</property>
            <property>aero/ci2vel</property>
            <property>fcs/lef-pos-rad</property>
                        <table>
                             <independentVar>aero/alpha-rad</independentVar>
                             <tableData>
                -0.175  0.067
                    -0.087  0.034
                     0.000  0.028
                     0.087  0.029
                     0.175  0.033
                     0.262  0.059
                     0.349  0.061
                     0.436  0.027
                     0.524  0.036
                     0.611  0.047
                     0.698  0.029
                     0.785  0.015
                 </tableData>
                       </table>
                   </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>
                       <property>aero/beta-rad</property>
                       <value>-1.7875</value>
                   </product>
               </function>
        <function name="aero/coefficient/CYb_M">
                   <description>Side_force_due_to_beta_due_to_mach</description>
                   <product>
                       <property>aero/qbar-psf</property>
                       <property>metrics/Sw-sqft</property>
                       <property>aero/beta-rad</property>
                       <table>
                             <independentVar>velocities/mach</independentVar>
                             <tableData>
                    0.4        0.0
                       1.2      0.0573
                       1.6     -0.1719
                 </tableData>
            </table>
                   </product>
               </function>
               <function name="aero/coefficient/CYbdot">
                   <description>Side_force_due_to_beta_rate</description>
                   <product>
                       <property>aero/qbar-psf</property>
                       <property>metrics/Sw-sqft</property>
                       <property>aero/betadot-rad_sec</property>
                       <value>-0.0458</value>
                   </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>-1.1516e-3</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>0.0619</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>
                       <value>0.0399</value>
                   </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>
                       <value>0.1218</value>
                   </product>
               </function>
           </axis>
  
           <axis name="LIFT">

               <function name="aero/coefficient/CLalpha">
                   <description>Lift_due_to_alpha</description>
                   <product>
                       <property>aero/qbar-psf</property>
                       <property>metrics/Sw-sqft</property>
                         <table>
                             <independentVar>aero/alpha-rad</independentVar>
                             <tableData>
                                 -0.1745    -0.4279
                                 0.7854    2.3000
                                 1.3963    1.0726
                             </tableData>
                        </table>
                   </product>
               </function>

        <function name="aero/coefficient/CLDlef">
                   <description>Lift_due_to_leading_edge_flap_deflection</description>
                   <product>
                       <property>aero/qbar-psf</property>
                       <property>metrics/Sw-sqft</property>
            <property>fcs/lef-pos-rad</property>
            <property>aero/function/kCLge</property>
                         <table>
                             <independentVar>aero/alpha-rad</independentVar>
                             <tableData>
                                 -0.1750  -0.0120
                              -0.0870  -0.0040
                              0.0000  0.0020
                              0.0870  0.0070
                              0.1750  0.0120
                              0.2620  0.0180
                              0.3490  0.0220
                              0.4360  0.0250
                              0.5240  0.0260
                              0.6110  0.0280
                              0.6980  0.0300
                              0.7850  0.032
                        0.8727   0.03
                        1.0472   0.028
                        1.2217   0.025
                        1.3963   0.02
                             </tableData>
                        </table>
                   </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>2.5602</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>
            <property>aero/function/kCLge</property>
                         <table>
                             <independentVar>aero/alpha-rad</independentVar>
                             <tableData>
                                -0.175  8.7127
                     -0.087 25.7114
                      0.000 28.9000
                      0.087 31.3973
                      0.175 31.0872
                      0.262 30.4071
                      0.349 28.9735
                      0.436 28.4242
                      0.524 27.8647
                      0.611 27.2654
                      0.698 30.5158
                      0.785 27.8165
                             </tableData>
                        </table>
                   </product>
               </function>
               <function name="aero/coefficient/dCLflap">
                   <description>Delta_Lift_due_to_flaps</description>
                   <product>
                       <property>aero/qbar-psf</property>
                       <property>metrics/Sw-sqft</property>
                       <property>fcs/flap-pos-norm</property>
            <property>aero/function/kCLge</property>
                       <value>0.3500</value>
                   </product>
               </function>
               <function name="aero/coefficient/dCLsb">
                   <description>Delta_Lift_due_to_speedbrake</description>
                   <product>
                       <property>aero/qbar-psf</property>
                       <property>metrics/Sw-sqft</property>
                      <property>fcs/speedbrake-pos-norm</property>
            <property>aero/function/kCLge</property>
                       <value>0.3500</value>
                   </product>
               </function>
<!--
            <function name="aero/coefficient/CLDh">
                <description>Lift_due_to_horizontal_tail_deflection</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">fcs/elevator-pos-rad</independentVar>
                          <tableData>
                              -0.1745    -0.4279
                    0.0000    0.1346
                    0.7854    2.00
                    1.3963    1.0726  
                           
                          </tableData>
                      </table>
                </product>
            </function>
               
               <function name="aero/coefficient/CLDh">
                <description>Lift_due_to_horizontal_tail_deflection</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">fcs/elevator-pos-rad</independentVar>
                          <tableData>
                                
           -0.175  -0.428 
           -0.087  -0.135 
            0.000  0.135  
            0.087   0.414 
            0.175  0.725 
            0.262  1.041 
            0.349  1.327 
            0.436  1.547 
            0.524  1.737 
            0.611  1.829 
            0.698  1.930 
            0.785  2.000 
        0.8727 1.982 
            1.0472 1.830 
            1.2217 1.548 
            1.3963 1.073 
                          </tableData>
                      </table>
                </product>
            </function>
-->
        <function name="aero/coefficient/CLde">
                   <description>Lift_due_to_elevator</description>
                   <product>
                       <property>aero/qbar-psf</property>
                       <property>metrics/Sw-sqft</property>
                      <property>fcs/elevator-pos-rad</property>
            <property>aero/function/kCLge</property>
                       <value>0.190</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>
                       <property>aero/beta-rad</property>
                         <table>
                             <independentVar>aero/alpha-rad</independentVar>
                             <tableData>
                                 -0.0873    0.0189
                                 0.0000    0.0176
                                 0.0873    0.0119
                                 0.1745    0.0050
                                 0.2618    0.0049
                                 0.3491    0.0028
                                 0.4363    0.0084
                                 0.5236    0.0171
                                 0.6109    0.0044
                             </tableData>
                         </table>
                   </product>
               </function>
        <function name="aero/coefficient/Clda_M">
                   <description>Change_in_Roll_moment_due_to_aileron_due_to_mach</description>
                   <product>
                       <property>aero/qbar-psf</property>
                       <property>metrics/Sw-sqft</property>
                       <property>metrics/bw-ft</property>
                       <property>aero/alpha-rad</property>
                       <property>fcs/left-aileron-pos-rad</property>
                         <table>
                             <independentVar>velocities/mach</independentVar>
                             <tableData>
                                 0.6      0.0
                       1.2     -0.063
                       1.6     -0.063
                             </tableData>
                         </table>
                   </product>
               </function>
        <function name="aero/coefficient/Cldr_M">
                   <description>Change_in_Roll_moment_due_to_rudder_due_to_mach</description>
                   <product>
                       <property>aero/qbar-psf</property>
                       <property>metrics/Sw-sqft</property>
                       <property>metrics/bw-ft</property>
                       <property>aero/alpha-rad</property>
                        <property>fcs/rudder-pos-rad</property>
                         <table>
                             <independentVar>velocities/mach</independentVar>
                             <tableData>
                                 0.6      0.0
                        1.6     -0.0201
                             </tableData>
                         </table>
                   </product>
               </function>
               <function name="aero/coefficient/Clbdot">
                  <description>Roll_moment_due_to_beta_rate</description>
                   <product>
                       <property>aero/qbar-psf</property>
                       <property>metrics/Sw-sqft</property>
                       <property>metrics/bw-ft</property>
                       <property>aero/bi2vel</property>
                       <property>aero/betadot-rad_sec</property>
                       <value>-0.0037</value>
                   </product>
               </function>
              <function name="aero/coefficient/Clp">
                   <description>Roll_moment_due_to_roll_rate</description>
                   <product>
                       <property>aero/qbar-psf</property>
                       <property>metrics/Sw-sqft</property>
                       <property>metrics/bw-ft</property>
                      <property>aero/bi2vel</property>
                       <property>velocities/p-aero-rad_sec</property>
                       <table>
                           <independentVar>aero/alpha-rad</independentVar>
                           <tableData>
                               0.0000  -0.4000
                               0.3490  -0.3100
                           </tableData>
                       </table>
                   </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>aero/alpha-rad</independentVar>
                           <tableData>
                               -0.175 -0.126
                    -0.087 -0.026
                     0.0    0.063
                     0.087  0.113
                     0.175  0.208
                     0.262  0.230
                     0.349  0.319
                     0.436  0.437
                     0.524  0.680
                     0.611  0.100
                     0.698  0.447
                     0.785 -0.330
                           </tableData>
                       </table>
                   </product>
               </function>
               <function name="aero/coefficient/Clda">
                   <description>Roll_moment_due_to_aileron</description>
                   <product>
                <value>4</value>
                       <property>aero/qbar-psf</property>
                       <property>metrics/Sw-sqft</property>
                       <property>metrics/bw-ft</property>
                       <property>fcs/left-aileron-pos-rad</property>
                         <table>
                             <independentVar>aero/alpha-rad</independentVar>
                             <tableData>
                                -0.1745   0.045
                      -0.0873   0.052
                       0.0000   0.060
                       0.0873   0.057
                       0.1745   0.052
                       0.2618   0.047
                       0.3491   0.040
                       0.4363   0.034
                       0.5236   0.029
                       0.6109   0.023
                       0.6981   0.019
                       0.7854   0.015
                       0.8727   0.012
                       1.0472   0.011
                       1.2217   0.009
                       1.3963   0.008
                             </tableData>
                         </table>
                   </product>
               </function>
               <function name="aero/coefficient/ClDr">
                   <description>Roll_moment_due_to_rudder</description>
                   <product>
                <value>2</value>
                       <property>aero/qbar-psf</property>
                       <property>metrics/Sw-sqft</property>
                       <property>metrics/bw-ft</property>
                      <property>fcs/rudder-pos-rad</property>
                         <table>
                             <independentVar>aero/alpha-rad</independentVar>
                            <tableData>
                                 -0.1745    0.0078
                                 -0.0873    0.0070
                                 0.0000    0.0059
                                 0.0873    0.0043
                                 0.1745    0.0023
                                 0.2618    0.0007
                                 0.3491    -0.0008
                                 0.4363    0.0004
                                 0.5236    0.0019
                                 0.6109    0.0019
                                 0.6981    0.0017
                                 0.7854    0.0009
                                 0.8727    0.0003
                                 1.0472    0.0000
                                 1.2217    0.0000
                                 1.3963    0.0000
                             </tableData>
                         </table>
                   </product>
               </function>
           </axis>
   
           <axis name="PITCH">
               <function name="aero/coefficient/CmDh">
                   <description>Pitch_moment_due_to_horizontal_tail_deflection</description>
                   <product>
                
                       <property>aero/qbar-psf</property>
                       <property>metrics/Sw-sqft</property>
                       <property>metrics/cbarw-ft</property>
                         <table>
                           <independentVar lookup="row">aero/alpha-rad</independentVar>
                           <independentVar lookup="column">fcs/elevator-pos-rad</independentVar>
                           <tableData>
                                        -0.5236  0.0    0.5236
                      -0.0873    0.3222 -0.0546 -0.4911
                               0.0000    0.3482  0.0000 -0.4729
                               0.0873    0.3897  0.0286 -0.4782
                               0.1745    0.3689  0.0156 -0.4988
                               0.2618    0.3975  0.0546 -0.4287
                               0.3491    0.3819  0.0442 -0.2722
                               0.4363    0.4131  0.0831 -0.1637
                               0.5236    0.4599  0.1377 -0.0546
                               0.6109    0.4443  0.1325 -0.0530
                               0.6981    0.3819  0.1013 -0.0650
                               0.7854    0.3585  0.0909 -0.0624
                               0.8727    0.3430  0.1299 -0.0364
                               1.0472    0.0208 -0.1117 -0.1975
                               1.2217    0.3248 -0.4521 -0.5144

                           </tableData>
                         </table>
            <value>1.5</value>
                   </product>
               </function>
   
               <function name="aero/coefficient/CmDtv">
                   <description>Pitch_moment_due_to_thrust_vectoring</description>
                   <product>
            <value>1.25</value>
                       <property>aero/qbar-psf</property>
                       <property>metrics/Sw-sqft</property>
                       <property>metrics/cbarw-ft</property>
                       <property>fcs/thrust-norm</property>
                         <table>
                           <independentVar lookup="row">aero/alpha-rad</independentVar>
                           <independentVar lookup="column">fcs/tvc-pos-rad</independentVar>
                           <tableData>
                    -0.3491  0.0  0.3491
                   -0.0873    0.4417  0.0 -0.7924
                    0.0000    0.4650  0.0 -0.8366
                    0.0873    0.4448  0.0 -0.8808
                    0.1745    0.4677  0.0 -0.8886
                    0.2618    0.4755  0.0 -0.8600
                    0.3491    0.4625  0.0 -0.7534
                    0.4363    0.4963  0.0 -0.6901
                    0.5236    0.4936  0.0 -0.6408
                    0.6109    0.4781  0.0 -0.6000
                    0.6981    0.5025  0.0 -0.5454
                    0.7854    0.5015  0.0 -0.5143
                    0.8727    0.4209  0.0 -0.5284
                    1.0472    0.4417  0.0 -0.5047
                    1.2217    0.2988  0.0 -0.4883

                           </tableData>
                        </table>
                   </product>
               </function>
           <function name="aero/coefficient/Cma_M">
                   <description>Change_in_Pitch_moment_due_to_alpha_due_to_mach</description>
                   <product>
                       <property>aero/qbar-psf</property>
                       <property>metrics/Sw-sqft</property>
                       <property>metrics/cbarw-ft</property>
                       <property>aero/alpha-rad</property>
                        <table>
                             <independentVar>velocities/mach</independentVar>
                             <tableData>              
                       0.6000  0.0000
                       0.8000  0.0974
                       0.9000  -0.3323
                       1.0000  -0.9626
                       1.1000  -0.8480
                       1.2000  -0.7907
                             </tableData>
                         </table>
                   </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>
                       <table>
                             <independentVar>aero/alpha-rad</independentVar>
                             <tableData>              
                       -0.1750  -7.2100
                    -0.0870  -5.4000
                    0.0000  -5.2300
                    0.0870  -5.2600
                    0.1750  -6.1100
                    0.2620  -6.6400
                    0.3490  -5.6900
                    0.4360  -6.0000
                    0.5240  -6.2000
                    0.6110  -6.4000
                    0.6980  -6.6000
                    0.7850  -6.0000
                             </tableData>
                         </table>
                   </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>
                       <table>
                             <independentVar>velocities/mach</independentVar>
                             <tableData>
                                 0.2570    -1.5611
                                 1.8000    -2.0500
                             </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>
                       <property>aero/beta-rad</property>
                      <table>
                             <independentVar>aero/alpha-rad</independentVar>
                             <tableData>
                                 -0.349    0.0745
                           0.000    0.1780
                            0.873    0.0086


                             </tableData>
                         </table>
                   </product>
               </function>
               <function name="aero/coefficient/Cnb_M">
                   <description>Change_in_Yaw_moment_due_to_beta_due_to_mach</description>
                   <product>
                       <property>aero/qbar-psf</property>
                       <property>metrics/Sw-sqft</property>
                       <property>metrics/bw-ft</property>
                       <property>aero/beta-rad</property>
                         <table>
                             <independentVar>velocities/mach</independentVar>
                             <tableData>
                                 0.6000  0.0000
                      0.7000  -0.0688
                      0.8000  -0.0172
                      0.9000  0.0229
                      1.0000  0.0000
                      1.2000  -0.0688
                      1.4000  0.0057
                      1.6000  0.0688
                             </tableData>
                         </table>
                   </product>
               </function>
               <function name="aero/coefficient/Cnbdot">
                   <description>Yaw_moment_due_to_beta_rate</description>
                   <product>
                       <property>aero/qbar-psf</property>
                       <property>metrics/Sw-sqft</property>
                       <property>metrics/bw-ft</property>
                      <property>aero/bi2vel</property>
                       <property>aero/betadot-rad_sec</property>
                       <value>-0.0115</value>
                   </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>-0.0035</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>
                       <table>
                          <independentVar>aero/alpha-rad</independentVar>
                          <tableData>
                              -0.1750  -0.3800
                              -0.0870  -0.3630
                              0.0000  -0.3780
                              0.0870  -0.3860
                              0.1750  -0.3700
                              0.2620  -0.4530
                              0.3490  -0.5500
                              0.4360  -0.5820
                              0.5240  -0.5950
                              0.6110  -0.6370
                              0.6980  -1.0200
                              0.7850  -0.8400
                          </tableData>
                      </table>

                   </product>
               </function>
               <function name="aero/coefficient/CnDr">
                   <description>Yaw_moment_due_to_rudder</description>
                   <product>
                <value>5</value>
                       <property>aero/qbar-psf</property>
                       <property>metrics/Sw-sqft</property>
                       <property>metrics/bw-ft</property>
                       <property>fcs/rudder-pos-rad</property>
                         <table>
                             <independentVar>aero/alpha-rad</independentVar>
                             <tableData>
                                 
                      -0.1745    -0.048
                                -0.0873    -0.045
                                 0.0000    -0.045
                                 0.0873    -0.045
                                 0.1745    -0.044
                                 0.2618    -0.045
                                0.3491    -0.047
                                 0.4363    -0.048
                                 0.5236    -0.040
                                 0.6109    -0.033
                                 0.6981    -0.025
                                 0.7854    -0.017
                                 0.8727    -0.010
                                 1.0472    -0.0075
                                 1.2217    -0.0075
                                 1.3963    -0.0075

                             </tableData>
                         </table>
                   </product>
               </function>
        <function name="aero/coefficient/Cndr_M">
                   <description>Change_in_Yaw_moment_due_to_rudder_due_to_mach</description>
                   <product>
                       <property>aero/qbar-psf</property>
                       <property>metrics/Sw-sqft</property>
                       <property>metrics/bw-ft</property>
            <property>aero/alpha-rad</property>
                       <property>fcs/rudder-pos-rad</property>
                         <table>
                             <independentVar>velocities/mach</independentVar>
                             <tableData>
                                 0.6000  0.0000
                      1.2000  0.0401
                      1.6000  0.0716
                             </tableData>
                         </table>
                   </product>
               </function>
               <function name="aero/coefficient/Cnda">
                   <description>Adverse_yaw</description>
                   <product>
                <value>2</value>
                       <property>aero/qbar-psf</property>
                       <property>metrics/Sw-sqft</property>
                       <property>metrics/bw-ft</property>
                       <property>fcs/left-aileron-pos-rad</property>
                       <table>
                             <independentVar>aero/alpha-rad</independentVar>
                             <tableData>
                -0.1745  0.01
                      -0.0873  0.009
                       0.0000  0.010
                       0.0873  0.009
                       0.1745  0.008
                       0.2618  0.006
                       0.3491  -0.002
                       0.4363  -0.003
                       0.5236  -0.005
                       0.6109  -0.008
                       0.6981  -0.006
                       0.7854  -0.006
                       0.8727  -0.008
                       1.0472  -0.01
                       1.2217  -0.011
                       1.3963  -0.013
                 </tableData>
            </table>
                   </product>
               </function>
           </axis>
       </aerodynamics>
<!--
  <output name="f16_datalog.csv" type="CSV" rate="1">
    <property> aero/qbar-psf </property>
    <property> attitude/phi-rad </property>
    <property> position/h-sl-ft </property>
    <property> velocities/vc-kts </property>
    <property> fcs/throttle-cmd-norm </property>
    <property> fcs/elevator-cmd-norm </property>
    <property> fcs/pitch-trim-cmd-norm </property>
    <property> propulsion/total-fuel-lbs </property>
    <property> flight-path/gamma-rad </property>
    <property> accelerations/n-pilot-z-norm </property>
    <rates> ON </rates>
    <velocities> ON </velocities>
    <forces> ON </forces>
    <moments> ON </moments>
    <position> ON </position>
    <fcs> ON </fcs>
    <propulsion> OFF </propulsion>
    <aerosurfaces> ON </aerosurfaces>
    <fcs> ON </fcs>
    <ground_reactions> ON </ground_reactions>
  </output>
-->
</fdm_config>
