<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="F14A" version="2.0" release="PRODUCTION"
   xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
   xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

 <fileheader>
  <author>Richard Harrison</author>
  <filecreationdate>2014-08-02</filecreationdate>
  <version>1.0</version>
        <description>
            Models an F14A with GE engines. The aerodata used is from
  ref[1] volumes 1 and 2 is only for sweep of 22degrees, positive
  alpha, clean, low speed so various data have been extrapolated
  estimated based on best available data where I cannot find specific
  details for F14 other aero models that I can find (often using NASA
  CR-1756 as guidance for general trends) are guidance or starting point for each value.
            The estimation of negative alpha values follows CR-1756 trends with values based on 
            F14 data for positive values.

  Engine Thrust are based on NASA-TM-104326 tables 4-6 adjusted for altitude and with
  augmentation figures based on that of the mil thrust.
  
     The flaps and auxiliary flaps coefficients are modelled based on tuning to meet F-14AAD-1 as no data 
            is currently available. The proportions assigned are relative to their surface area 
            (as measured roughly 64% main, 36% aux) - the values assigned are 0.7 and 0.3 based on this 
            and this applies to ClDFM, CdDFM and CMDFM

  </description>
    <note>Aircraft origin for measurements is the nose.</note>
        <note>Low speed clean should be exactly as an F-14 as this model is based on accurate aerodata (see limitations below).</note>
        <limitation>Spoilers, sweep, speedbrake, flaps, gear aerodata not modelled in ADA101648 - figured out values are be used</limitation>
        <reference 
            refID="http://zaretto.com/f-14b"
            author="Richard Harrison"
            title="Grummnan F-14B Model for flightgear"
            date="October 24, 2014"
        />
    <reference
        refID="AFWAL-TR-80-3141"
        author="Donald E. Johnston, David G. Mitchell, Thomas T. Myers"
            title="Investigation of High-Angle-of-Attack Maneuver-limiting factors, Part I: Anaylsis and simulation"
        date="1980"
    />
    <reference
        refID="AFWAL-TR-80-3141"
        author="Donald E. Johnston, David G. Mitchell, Thomas T. Myers"
        title="Investigation of High-Angle-of-Attack Maneuver-limiting factors, Part III: Appendices aerodynamic models"
        date="1980"
    />
    <reference
        refID="NASA TN D-6909"
        author="Sue B. Grafton and Ernie L. Anglin"
        title="DYNAMIC STABILITY DERIVATIVES AT ANGLES OF ATTACK FROM -5deg TO 90deg FOR A VARIABLE-SWEEP FIGHTER CONFIGURATION WITH TWIN VERTICAL TAILS"
        date="1972"
    />
    <reference
        refID="NASA-TP-3253"
        author="Gary E. Erickson and Lawrence W. Rogers"
        title="Effects of Forebody Strakes an Mach number on overall aerodynamic characterisitcs of configuration with 55degree cropped delta wing"
        date="November 1992"
    />
    <reference
        refID="NASA-TM-84643"
        author="M. Leroy Spearman"
        title="Effects of Wing and tail location on the aerodynamic characteristics of an airplane for mach numbers from 0.25 to 4.63"
        date="March 1983"
    />
    <reference
        refID="NASA-aaia-2000-0900"
    />
    <reference
        refID="NASA-TM-104326"
        title="Flight and Static Exhaust Flow  Properties of an F110-GE-129  Engine in an F-16XL Airplane  During Acoustic Tests"
        author="Jon K. Holzman, Lannie D. Webb, and Frank W. Burcham, JR."
        date="November 1996"
    />
    <reference
            refID="NASA-TM-101717"
            title="Flutter clearance to the F-14A Variable-Sweep Transition Flight Expirement Airplane - Phase 2"
            author="Lawrence C. Freudinger and Michael W. Kehoe"
            date="July 1990"
        />
        <reference
        refID="NASA-TM-102409"
        author="Colin K. Drummond and Peter J. Ouzts"
        title="Real-Time Simulation of an F 110/STOVL Turbofan Engine"
        date="October 16-17, 1989"
    />
    <reference
        refID="http://www.ssdl.gatech.edu/papers/mastersProjects/MillerJ-8900.pdf"
            title="Investigation of Transonic Drag Computations in Aerodynamic Preliminary Analysis System (APAS)"
            author="Jeff Miller"
            date="April 26, 2002"
    />
     </fileheader>

<!--
Notes:

1. possibly need to consider differential spoiler deflection on yaw moments

2. Surface positions
Cockpit control	Stabilizer Surface	Parallel Trim
Actuation	Mode	Motion	Authority	Rate	Authority	Rate
Control Stick	Manual	4 Inches forward
5.5 inches AFT	12deg TED
33deg TEU	36deg/second	9deg TEU
18deg TEU	1 deg/second
AFCS	Series (SAS)	NONE	+/- 3deg	20deg/second	-	-
	Parallel 
(ACL Only)	4 Inches forward
5.5 inches AFT	12deg TED
33deg TEU	36deg/second	9deg TEU
18deg TEU	0.1 deg/second
Maneuver FLAP (ITS) AND DLC Thumbwheel	Series	+45 deg DLC Thumbwheel mode	8.4 TED maximum	36deg/second	-	-
		+45deg maneuver flap mode	+/- 3deg	3deg/sec	-	-
-->

<!-- <system file="f-14a-engines"/> -->
<!-- <system file="jt9d"/> -->
 <system file="f-14b-hydraulic"/>
 <system file="f-14b-electrics"/>
 <system file="f-14b-cadc"/>
 <system file="f-14b-apc"/>
    <system file="f-14b-engines-TF-30"/>
    <system file="hook"/>
 <system file="catapult"/>
 <system file="holdback"/>

 <metrics>
   <wingarea       unit="FT2">   565 </wingarea>
   <wingspan       unit="FT" >    64 </wingspan>
   <wing_incidence unit="DEG">     2 </wing_incidence>

        <chord     unit="FT" >    9.82 </chord>
   <htailarea unit="FT2">  140.00 </htailarea>
   <htailarm  unit="FT" >   25.10 </htailarm>
        <vtailarea unit="FT2">  118.00 </vtailarea>
        <!-- 59ft2 each -->
   <vtailarm  unit="FT" >   25.10 </vtailarm>

   <location name="EYEPOINT" unit="IN">
     <x> 197 </x>
     <y>   0.00 </y>
     <z>  -3.94 </z>
</location>
   <location name="VRP" unit="IN">
            <x>  386</x>
     <y>  0</y>
            <z>  31 </z>
   </location>
   <location name="AERORP" unit="IN">
      <x> 419 </x>
      <y>   0.00 </y>
      <z>   0.00 </z>
   </location>
 </metrics>

  <mass_balance>
    <location name="CG" unit="IN">
      <x> 403</x>
      <y>   0.00 </y>
            <z>   0.00 </z>
    </location>
    <ixx unit="SLUG*FT2">     58950 </ixx>
    <iyy unit="SLUG*FT2">    225600 </iyy>
    <izz unit="SLUG*FT2">    285000 </izz>
    <!-- using GE F110 engines but aero is for F14A -->
<!-- left to right; 01 pylons, 2 left tank, 3456 centre rails, 7 right tank, 89 right  pylons -->
    <emptywt unit="LBS" >     42104 </emptywt>
    <pointmass name="Left Pylon0">
        <weight unit="LBS"> 0 </weight>
        <location name="POINTMASS" unit="IN">
            <x> 403 </x>
            <y> -100 </y>
            <z> -13 </z>
        </location>
    </pointmass>
    <pointmass name="Left Pylon1">
        <weight unit="LBS"> 0 </weight>
        <location name="POINTMASS" unit="IN">
            <x> 403 </x>
            <y> -95 </y>
            <z> -10 </z>
        </location>
    </pointmass>
    <pointmass name="Left External Tank2">
        <weight unit="LBS"> 0 </weight>
        <location name="POINTMASS" unit="IN">
          <x>416</x>
          <y>-55</y>
          <z>-110</z>
        </location>
    </pointmass>
    
    <pointmass name="Centre Left Front3">
        <weight unit="LBS"> 0 </weight>
        <location name="POINTMASS" unit="IN">
                <x> 316 </x>
            <y> -5 </y>
            <z> -3 </z>
        </location>
    </pointmass>

    <pointmass name="Centre Left Rear4">
        <weight unit="LBS"> 0 </weight>
        <location name="POINTMASS" unit="IN">
                <x> 500 </x>
            <y> -5 </y>
            <z> -3 </z>
        </location>
    </pointmass>
    <pointmass name="Centre Right Front5">
        <weight unit="LBS"> 0 </weight>
        <location name="POINTMASS" unit="IN">
                <x> 316 </x>
            <y>   5 </y>
            <z>  -3 </z>
        </location>
    </pointmass>

    <pointmass name="Centre Right Rear6">
        <weight unit="LBS"> 0 </weight>
        <location name="POINTMASS" unit="IN">
                <x> 500 </x>
            <y>   5 </y>
            <z>  -3 </z>
        </location>
    </pointmass>

    <pointmass name="Right External Tank7">
        <weight unit="LBS"> 0 </weight>
        <location name="POINTMASS" unit="IN">
          <x>416</x>
          <y> 55</y>
          <z>-110</z>
        </location>
    </pointmass>

    <pointmass name="Right Pylon8">
        <weight unit="LBS"> 0 </weight>
        <location name="POINTMASS" unit="IN">
            <x> 403 </x>
            <y> 100 </y>
            <z> -13 </z>
        </location>
    </pointmass>
    <pointmass name="Right Pylon9">
        <weight unit="LBS"> 0 </weight>
        <location name="POINTMASS" unit="IN">
            <x> 403 </x>
            <y> 95 </y>
            <z> -10 </z>
        </location>
    </pointmass>
  </mass_balance>

  <!-- 0 -->
  <ground_reactions>
    <contact type="BOGEY" name="NOSE_LG">
      <location unit="IN">
        <x> 197 </x>
        <y> 0 </y>
                <z> -94.01 </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"> 42500 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
      <max_steer unit="DEG"> 89 </max_steer>
      <brake_group> NOSE </brake_group>
      <retractable>1</retractable>
    </contact>
    <!-- 1 -->
    <contact type="BOGEY" name="LEFT_MLG">
      <location unit="IN">
                <x> 451 </x>
        <y> -98 </y>
                <z> -102.1  </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"> 42500 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
      <max_steer unit="DEG"> 0.0 </max_steer>
      <brake_group> LEFT </brake_group>
      <retractable>1</retractable>
    </contact>
    <!-- 2 -->
    <contact type="BOGEY" name="RIGHT_MLG">
      <location unit="IN">
                <x> 451 </x>
        <y> 98 </y>
                <z> -102.1 </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"> 42500 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
      <max_steer unit="DEG"> 0.0 </max_steer>
      <brake_group> RIGHT </brake_group>
      <retractable>1</retractable>
    </contact>
    <!-- 3 -->
    <contact type="STRUCTURE" name="LEFT_WING_TIP">
      <location unit="IN">
                <x> 472 </x>
                <y> -300 </y>
                <z>   13 </z>
      </location>
      <static_friction> 1.2 </static_friction>
      <dynamic_friction> 1.212 </dynamic_friction>
      <rolling_friction> 1.413 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
    </contact>

    <!--  4 -->
    <contact type="STRUCTURE" name="RIGHT_WING_TIP">
      <location unit="IN">
                <x> 472 </x>
                <y> 300 </y>
                <z> 13 </z>
      </location>
      <static_friction> 1.2 </static_friction>
      <dynamic_friction> 1.212 </dynamic_friction>
      <rolling_friction> 1.413 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
    </contact>


    <!--  5 -->
    <contact type="STRUCTURE" name="FRONT_BODY">
      <location unit="IN">
                <x> 110 </x>
        <y> 0 </y>
                <z> -47 </z>
      </location>
      <static_friction> 1.2 </static_friction>
      <dynamic_friction> 1.212 </dynamic_friction>
      <rolling_friction> 1.413 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 41300 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 8600 </damping_coeff>
      </contact>

      <!--  8 -->
    <contact type="STRUCTURE" name="CANOPY">
      <location unit="IN">
        <x> 214 </x>
        <y>  0 </y>
                <z> 10 </z>
      </location>
      <static_friction> 1.2 </static_friction>
      <dynamic_friction> 1.212 </dynamic_friction>
      <rolling_friction> 1.413 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 41300 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 8600 </damping_coeff>
    </contact>

    <!--  9 -->
        <!--<contact type="STRUCTURE" name="RADOME_FRONT">
      <location unit="IN">
                <x>  20 </x>
        <y>  0 </y>
                <z>  -18 </z>
      </location>
      <static_friction> 1.2 </static_friction>
      <dynamic_friction> 1.212 </dynamic_friction>
      <rolling_friction> 1.413 </rolling_friction>
           <spring_coeff unit="LBS/FT"> 24000 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC"> 20000 </damping_coeff>
        </contact>-->

    <!--  10 -->
    <contact type="STRUCTURE" name="LEFT_VERTICAL_TAIL">
      <location unit="IN">
                <x> 744 </x>
        <y> -98 </y>
                <z> 60 </z>
      </location>
      <static_friction> 1.2 </static_friction>
      <dynamic_friction> 1.212 </dynamic_friction>
      <rolling_friction> 1.413 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 41300 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 8600 </damping_coeff>
    </contact>

    <!--  11 -->
    <contact type="STRUCTURE" name="RIGHT_VERTICAL_TAIL">
      <location unit="IN">
                <x> 744 </x>
        <y>  98 </y>
                <z> 60 </z>
      </location>
      <static_friction> 1.2 </static_friction>
      <dynamic_friction> 1.212 </dynamic_friction>
      <rolling_friction> 1.413 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 41300 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 8600 </damping_coeff>
    </contact>
    <!-- 12 -->
  <contact type="STRUCTURE" name="REAR_BODY_LEFT">
      <location unit="IN">
        <x> 713 </x>
                <y> -58 </y>
                <z> -40 </z>
      </location>
      <static_friction> 1.2 </static_friction>
      <dynamic_friction> 1.212 </dynamic_friction>
      <rolling_friction> 1.413 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 41300 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 8600 </damping_coeff>
    </contact>

    <!--  13 -->
    <contact type="STRUCTURE" name="REAR_BODY_RIGHT">
      <location unit="IN">
        <x> 713 </x>
                <y>  58 </y>
                <z> -40 </z>
      </location>
      <static_friction> 1.2 </static_friction>
      <dynamic_friction> 1.212 </dynamic_friction>
      <rolling_friction> 1.413 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 41300 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 8600 </damping_coeff>
        </contact>
<!-- 14 -->
        <contact type="STRUCTURE" name="NOSE_CONE">
            <location unit="IN">
                <x>  0 </x>
                <y>  0 </y>
                <z>  -15 </z>
            </location>
            <static_friction> 1.2 </static_friction>
            <dynamic_friction> 1.212 </dynamic_friction>
            <rolling_friction> 1.413 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
    </contact>
  </ground_reactions>
<!--<strut_force>
    <function>
        <sum>
            <product>
                <value>-1</value>
                <property>inertia/weight-lbs</property>
                <property> contact/unit[5]/compression-ft </property>
            </product>
        </sum>
    </function>
    <ifthen>
        <ge>
            <property> contact/unit[5]/compression-velocity-fps </property>
            <value> 0.0 </value>
        </ge>
        <product>
            <value> -24000. </value>
            <property> contact/unit[5]/compression-velocity-fps </property>
        </product>
        <product>
            <value> 0. </value>
            <property> contact/unit[5]/compression-velocity-fps </property>
        </product>
    </ifthen>
    <clipto>
        <min>-inertia/weight-lbs</min>
        <max>inertia/weight-lbs</max>
    </clipto>
</strut_force>-->   
<propulsion>
        <engine file="TF30-P-414">
            <location unit="IN">
                <x> 682 </x>
                    <y> -45 </y>
                <z> -15 </z>
            </location>
            <orient unit="DEG">
                <roll> 0 </roll>
                <pitch> 0 </pitch>
                <yaw> 0 </yaw>
            </orient>
            <feed>1</feed>
            <feed>2</feed>
            <feed>3</feed>
            <feed>6</feed>
            <feed>8</feed>
            <feed>10</feed>
            <thruster file="direct">
                <location unit="IN">
                    <x> 682 </x>
                    <y> -45 </y>
                    <z> -15 </z>
                </location>
                <orient unit="DEG">
                    <roll> 0 </roll>
                    <pitch> 0 </pitch>
                    <yaw> 0 </yaw>
                </orient>
            </thruster>
        </engine>
        <engine file="TF30-P-414">
            <location unit="IN">
                <x> 682 </x>
                    <y> 45 </y>
                <z> -15 </z>
            </location>
            <orient unit="DEG">
                <roll> 0 </roll>
                <pitch> 0 </pitch>
                <yaw> 0 </yaw>
            </orient>
            <feed>0</feed>
            <feed>4</feed>
            <feed>5</feed>
            <feed>7</feed>
            <feed>9</feed>
            <feed>11</feed>

            <thruster file="direct">
                <location unit="IN">
                    <x> 682 </x>
                    <y> 45 </y>
                    <z> -15 </z>
                </location>
                <orient unit="DEG">
                    <roll> 0 </roll>
                    <pitch> 0 </pitch>
                    <yaw> 0 </yaw>
                </orient>
            </thruster>
        </engine>
<!-- Fuel tank positions are hard to determine - so the values here are based on Figure 8-2 F14AAD-1 
     for the fore / aft tanks - with the other tanks moved from my original estimated position
     so that the CG remains in the range of no more than 18%. 
     I also had to move the MLG forwards slightly from the diagram otherwise it was impossible to take off a
     fully laden aircraft with flaps until over 210kts (which has to be wrong and as the contact point of the
             gear isn't defined (in AFWAL-TR-80-3141) and I can only assume that those measurements are from the end of the 
             radome excluding the probe. (about 20 inches according to my diagram)
  -->
      <!--  FWD Fuselage -->
      <tank type="FUEL">
        <location unit="IN">
                <x>382</x>
          <y>0</y>
          <z>-51.77165354</z>
        </location>
<priority>4</priority>
        <capacity unit="LBS">4700</capacity>
        <contents unit="LBS">4700</contents>
      </tank>
      <!-- AFT Fuselage -->
      <tank type="FUEL">
        <location unit="IN">
                <x>592</x>
          <y>0</y>
          <z>-47.83464567</z>
        </location>
        <capacity unit="LBS">4400</capacity>
        <contents unit="LBS">4400</contents>
<priority>4</priority>
      </tank>
      <!-- Left Beam Box - Feed Group   -->
      <tank type="FUEL">
        <location unit="IN">
          <x>396</x>
          <y>-47.95275591</y>
          <z>-45.07874016</z>
        </location>
        <capacity unit="LBS">1300</capacity>
        <contents unit="LBS">1300</contents>
<priority>3</priority>
      </tank>
      <!--  Left Sump - Feed Group    -->
      <tank type="FUEL">
        <location unit="IN">
          <x>396</x>
          <y>-38.58267717</y>
          <z>-47.83464567</z>
        </location>
        <capacity unit="LBS">300</capacity>
        <contents unit="LBS">300</contents>
<priority>5</priority>
      </tank>
      <!-- Right Beam Box - Feed Group    -->
      <tank type="FUEL">
        <location unit="IN">
          <x>396</x>
          <y>47.95275591</y>
          <z>-45.07874016</z>
        </location>
        <capacity unit="LBS">1300</capacity>
        <contents unit="LBS">1300</contents>
<priority>3</priority>
      </tank>
      <!-- Right Sump - Feed Group   -->
      <tank type="FUEL">
        <location unit="IN">
          <x>396</x>
          <y>38.58267717</y>
          <z>-47.83464567</z>
        </location>
        <capacity unit="LBS">300</capacity>
        <contents unit="LBS">300</contents>
<priority>5</priority>
      </tank>
      <!-- Left wing    -->
      <tank type="FUEL">
        <location unit="IN">
                <x> 462</x>
          <y> -38.5826772</y>
          <z> -27</z>
        </location>
        <capacity unit="LBS">2000</capacity>
        <contents unit="LBS">2000</contents>
<priority>2</priority>
      </tank>
      <!-- Right Wing -->
      <tank type="FUEL">
        <location unit="IN">
                <x> 462</x>
          <y> 38.5826772</y>
          <z> -27</z>
        </location>
        <capacity unit="LBS">2000</capacity>
        <contents unit="LBS">2000</contents>
<priority>2</priority>
      </tank>
      <!-- Left External -->
      <tank type="FUEL">
        <location unit="IN">
                <x>403</x>
          <y>-55.51181102</y>
          <z>-110.8267717</z>
        </location>
        <capacity unit="LBS">1600</capacity>
        <contents unit="LBS">1600</contents>
<priority>1</priority>
      </tank>
      <!-- Right External -->
      <tank type="FUEL">
        <location unit="IN">
                <x>403</x>
          <y>55.51181102</y>
          <z>-110.8267717</z>
        </location>
        <capacity unit="LBS">1600</capacity>
        <contents unit="LBS">1600</contents>
<priority>1</priority>
      </tank>
      <!-- Left Feed line -->
      <tank type="FUEL">
        <location unit="IN">
          <x>454</x>
          <y>-38.58267717</y>
          <z>-47.83464567</z>
        </location>
        <capacity unit="LBS">10</capacity>
        <contents unit="LBS">10</contents>
<priority>6</priority>
      </tank>
      <!-- Right Feed line -->
      <tank type="FUEL">
        <location unit="IN">
          <x>454</x>
          <y>38.58267717</y>
          <z>-47.83464567</z>
        </location>
        <capacity unit="LBS">10</capacity>
        <contents unit="LBS">10</contents>
<priority>6</priority>
      </tank>
    </propulsion>


  <flight_control name="FCS F14">

      <property>systems/NWS/engaged</property>

      <property>fcs/hook-engage</property>
      <property>fcs/wing-sweep-pilot-dmd</property>
      <property>systems/hook/tailhook-cmd-norm</property>
      <property>fcs/wing-sweep-auto</property>
      <property>fcs/spoiler-ground-brake-armed</property>
      <property>fcs/flap-cmd-sum</property>
      <property>fcs/roll-trim-sas-cmd-norm</property>

      <property value="1.0">Factor1</property>

      <property value="0">fcs/yaw-damper-enable</property>
      <property value="0">fcs/pitch-damper-enable</property>
      <property value="0">fcs/roll-sas-enable</property>
      <property value="0">fcs/external-tanks-fitted</property>
      <property value="0">fcs/aim-fitted</property>
      <property value="0">fcs/slat-cmd</property>

      <channel>

        <fcs_function  name="fcs/wing-sweep-cadc-dmd">
            <function>
                <description>Wing autosweep</description>
                <!-- based on what I can figure out from NAVAIR 01-F14AAD-1 Figure 2-48: p. 2-87 
         using a 2d lookup table so we have no sweep when flaps are out -->
                <sum>
                    <table>
                        <independentVar lookup="row">velocities/mach</independentVar>
                        <independentVar lookup="column">fcs/flap-pos-deg</independentVar>
                        <tableData>
                            0                   5              50
                            0.00 	0.294117647   0.294117647	 0.294117647
                            0.448	0.294117647	  0.294117647	 0.294117647
                            0.711	0.308823529	  0.294117647	 0.294117647
                            0.913   1	          0.735294117	 0.735294117
                        </tableData>
                    </table>
                </sum>
                <output>fcs/wing-sweep-cadc-dmd</output>
            </function>
        </fcs_function>
        
    <!-- manual sweep; it is only permitted to sweep the wings more back than the CADC requires so effectively
     we limit the sweep to the computed wing-sweep-cadc-pos -->
    <switch name="fcs/wing-sweep-dmd">
        <default value="fcs/wing-sweep-cadc-dmd"/>

        <test value="fcs/wing-sweep-dmd">
            systems/hydraulics/combined-system-pressure ne 1
        </test>
        <test value="fcs/wing-sweep-pilot-dmd">
            fcs/wing-sweep-pilot-dmd ge fcs/wing-sweep-cadc-dmd
            fcs/wing-sweep-auto ne 1
        </test>
    </switch>

    <switch name="fcs/wing-sweep-dmd-flap-limit">
        <default value="0.2941176470588235"/>
        <test value="0.3088235294117647">
            fcs/aux-flap-pos-deg ne 0
            fcs/wing-sweep-dmd ge 0.3088235294117647
            fcs/wing-sweep-dmd lt 0.3235294117647059
        </test>
        <test value="0.3235294117647059">
            fcs/aux-flap-pos-deg ne 0
            fcs/wing-sweep-dmd ge 0.3235294117647059
            fcs/wing-sweep-dmd lt 0.3382352941176471
        </test>
        <test value="fcs/wing-sweep-dmd">
            fcs/flap-pos-deg ne 0
            fcs/wing-sweep-dmd le 0.7352941176470588
        </test>
        <test value=".7352941176470588">
            fcs/flap-pos-deg ne 0
            fcs/wing-sweep-dmd gt 0.7352941176470588
        </test>
        <test value="fcs/wing-sweep-dmd">
            fcs/flap-pos-deg eq 0
        </test>
        <output>fcs/wing-sweep-dmd-flap-limit</output>
    </switch>
    <aerosurface_scale name="Sweep Control">
      <input>fcs/wing-sweep-cmd</input>
      <range>
        <min> 20 </min>
        <max> 68 </max>
      </range>
      <output>fcs/wing-sweep-pos-deg</output>
   </aerosurface_scale>

      <kinematic name="Sweep Position">
      <input>fcs/wing-sweep-dmd-flap-limit</input>
      <traverse>
          <setting>
              <position>0.294117647</position>
              <time>16</time> <!-- F14AAD-1 15 deg/sec sweep rate, (68-20)/15 -->
          </setting>
          <setting>
              <position>1</position>
              <time>16</time>
          </setting>
      </traverse>
      <output>fcs/wing-sweep-cmd</output>
   </kinematic>

   <aerosurface_scale name="Sweep Control">
      <input>fcs/wing-sweep-cmd</input>
      <range>
        <min> 20 </min>
        <max> 68 </max>
      </range>
      <output>fcs/wing-sweep-pos-deg</output>
   </aerosurface_scale>

      <kinematic name="fcs/hook-control">
        <input>fcs/hook-engage</input>
        <traverse>
          <setting>
            <position>0</position>
            <time>0</time>
          </setting>
          <setting>
            <position>1</position>
            <time>2.5</time>
          </setting>
        </traverse>
        <output>fcs/hook-pos-norm</output>
      </kinematic>


   <summer name="Pitch Trim Sum">
      <input>fcs/elevator-cmd-norm</input>
      <input>fcs/pitch-trim-cmd-norm</input>
      <input>systems/afcs/elevator-cmd-delta</input>
      <clipto>
        <min> -1 </min>
        <max>  1 </max>
      </clipto>
   </summer>

      <switch name="position/aircraft-on-ground">
          <description>Aircraft on ground</description>
          <default value="0"/>
          <test value="1" logic="OR">
              gear/unit[0]/WOW ne 0
              gear/unit[1]/WOW ne 0
              gear/unit[2]/WOW ne 0
          </test>
      </switch>

      <!-- spoilers -4deg when flaps deployed more than 25 deg -->
      <switch name="fcs/spoilers-zeropos">
          <default value="0"/>
          <test value="-0.081">
              fcs/flap-pos-norm ge 0.7142857142857143
          </test>
      </switch>

      <switch name="fcs/pitch-trim-actuator">
          <default value="fcs/pitch-trim-sum"/>
          <test value="fcs/pitch-trim-actuator">
              systems/hydraulics/flight-system-pressure ne 1
          </test>
      </switch>
      <aerosurface_scale name="Elevator Control">
          <input>fcs/pitch-trim-actuator</input>
          <!-- maybe this should take into account the trim limits from the AAP -->
          <range>
              <min> -0.57895 </min>
              <max>  0.2105 </max>
          </range>
          <output>fcs/elevator-pos-demand</output>
      </aerosurface_scale>

        <switch name="fcs/spoiler-ground-brake-deployed">
            <description>Ground braking spoilers</description>
            <default value="0"/>

            <test value="fcs/spoiler-ground-brake-deployed">
                systems/hydraulics/combined-system-pressure eq 0
            </test>

            <test value="1">
                systems/hydraulics/combined-system-pressure ne 0
                fcs/wing-sweep-pos-deg lt 55.0
                fcs/spoiler-ground-brake-armed ne 0.0
                fcs/throttle-cmd-norm[0] le 0.15
                fcs/throttle-cmd-norm[1] le 0.15
                position/aircraft-on-ground ne 0
            </test>
        </switch>

        <switch name="fcs/spoiler-left-cmd">
            <description>Left wing spoiler deflection</description>
            <default value="fcs/spoilers-zeropos"/>

                <test value="0">
                    aero/wing-asymmetry lt  0
                </test>

            <test value="1">
                fcs/spoiler-ground-brake-deployed eq 1
            </test>

            <test value="-fcs/spoiler-differential-pos">
                fcs/spoiler-differential-pos le 0
            </test>
        </switch>

      <kinematic name="fcs/spoiler-left-pos">
      <input>fcs/spoiler-left-cmd</input>
        <traverse>
          <setting>
              <position>-0.0818181818181819</position>
              <time>0.22</time> <!-- F14AAD-1 Figure 2-61 250 deg/sec sweep rate -->
          </setting>
          <setting>
              <position>1</position>
              <time>0.22</time> <!-- F14AAD-1 Figure 2-61 15 deg/sec sweep rate  -->
          </setting>
        </traverse>
      </kinematic>

        <switch name="fcs/spoiler-right-cmd">
            <description>Right  wing spoiler deflection</description>
            <default value="fcs/spoilers-zeropos"/>

                <test value="0">
                    aero/wing-asymmetry gt  0
                </test>

            <test value="1">
                fcs/spoiler-ground-brake-deployed eq 1
            </test>

            <test value="fcs/spoiler-differential-pos">
                fcs/spoiler-differential-pos ge 0
            </test>
        </switch>

       <kinematic name="fcs/spoiler-right-pos">
         <input>fcs/spoiler-right-cmd</input>
         <traverse>
          <setting>
              <position>-0.0818181818181819</position>
              <time>0.22</time> <!-- F14AAD-1 Figure 2-61 250 deg/sec sweep rate -->
          </setting>
          <setting>
              <position>1</position>
              <time>0.22</time> <!-- F14AAD-1 Figure 2-61 15 deg/sec sweep rate  -->
          </setting>
        </traverse>
     </kinematic>

   <aerosurface_scale name="fcs/spoiler-left-pos-deg">
      <input>fcs/spoiler-left-pos</input>
      <range>
        <min> -5 </min>
        <max> 55 </max>
      </range>
   </aerosurface_scale>
   <aerosurface_scale name="fcs/spoiler-right-pos-deg">
      <input>fcs/spoiler-right-pos</input>
      <range>
        <min> -5 </min>
        <max> 55 </max>
      </range>
   </aerosurface_scale>

<!-- F14a stabilizer: +/- 7deg : +/- 30 deg/sec -->
    <kinematic name="elevator position">
      <input>fcs/elevator-pos-demand</input>
      <traverse>
          <setting>
              <position>-1</position>
              <time>1.75</time>
          </setting>
          <setting>
              <position>1</position>
              <time>0.90</time> <!-- based on 30 deg/sec -->
          </setting>
      </traverse>
      <output>fcs/elevator-pos-rad</output>
    </kinematic>


   <summer name="Left elevator normalization">
      <input>fcs/elevator-pos-deg</input>
      <input>fcs/left-aileron-pos-deg</input>
      <output>fcs/left-elevator-pos-deg</output>
   </summer>
   <summer name="Right elevator normalization">
      <input>fcs/elevator-pos-deg</input>
      <input>-fcs/right-aileron-pos-deg</input>
      <output>fcs/right-elevator-pos-deg</output>
   </summer>

   <aerosurface_scale name="elevator normalization">
      <input>fcs/elevator-pos-rad</input>
      <domain>
        <min>  -0.57895 </min>
        <max>   0.21053 </max>
      </domain>
      <range>
        <min> -1 </min>
        <max>  1 </max>
      </range>
      <output>fcs/elevator-pos-norm</output>
   </aerosurface_scale>

   <switch name="fcs/stabilizer-1p-factor">
                <default value="0"/>
                <test logic="AND" value="1">
                    fcs/elevator-pos-rad ge -0.17453
                </test>
   </switch>
   <switch name="fcs/stabilizer-2p-factor">
                <default value="0.0"/>
                <test logic="AND" value="1">
                    fcs/elevator-pos-rad lt -0.17453
                </test>
   </switch>


          <switch name="systems/NWS/engaged">
              <default value="0"/>
              <test value="1">
                    gear/unit[0]/wheel-speed-fps le 135
                  systems/hydraulics/combined-system-pressure ne 0
                  position/aircraft-on-ground ne 0
                  systems/holdback/launchbar-engaged eq 0
              </test>
              <output>systems/NWS/engaged</output>
          </switch>

          <scheduled_gain name="fcs/scheduled-steer-pos-deg">
              <input>fcs/steer-cmd-norm</input>
              <table>
                    <independentVar lookup="row">gear/unit[0]/wheel-speed-fps</independentVar>
                  <independentVar lookup="column">systems/NWS/engaged</independentVar>
                  <tableData>
                          0   1
                        0   0   87
                        80  0   15
                        135 0   0
                  </tableData>
              </table>
              <output>fcs/steer-pos-deg</output>
          </scheduled_gain>
     <fcs_function name="fcs/flap-windfx-volume">
       <function>
         <product>
             <property>velocities/ve-kts</property>
             <property>fcs/flap-pos-norm</property>
         </product>
       </function>
       <output>fcs/flap-windfx-volume</output>
     </fcs_function>
     <fcs_function name="fcs/gear-windfx-volume">
       <function>
         <product>
             <property>velocities/ve-kts</property>
             <property>gear/gear-pos-norm</property>
         </product>
       </function>
       <output>fcs/gear-windfx-volume</output>
     </fcs_function>
          <switch name="fcs/roll-sas-active">
              <default value="0.0"/>
              <test logic="AND" value="1">
                  aero/alpha-rad ge -0.175438596491228
                  aero/alpha-rad le  0.2631578947368421
                  fcs/roll-sas-enable ne 0.0
              </test>
              <output>fcs/roll-sas-active</output>
          </switch>
          <scheduled_gain name="fcs/roll-rate-limiter">
      <input>fcs/aileron-cmd-norm</input>
      <table>
        <independentVar lookup="row">velocities/p-aero-rad_sec</independentVar>
         <tableData>
            -6.2    -1.0
            -1.4     0.0
             1.4     0.0
             6.2    -1.0
         </tableData>
      </table>
      <gain>fcs/roll-sas-active</gain>
       <output>fcs/roll-rate-limiter</output>
   </scheduled_gain>

<!-- aileron: +/- 5deg : +/- 33 deg/sec -->
   <summer name="Roll Trim Sum">
      <input>fcs/aileron-cmd-norm</input>
      <input>fcs/roll-trim-cmd-norm</input>
      <input>fcs/roll-trim-sas-cmd-norm</input>
                <input>fcs/roll-rate-limiter</input>
      <clipto>
        <min> -1 </min>
        <max>  1 </max>
      </clipto>
   </summer>


    <switch name="Roll Trim Actuator"> 
        <default value="fcs/roll-trim-sum"/> 
        <test value="fcs/roll-trim-actuator"> 
        systems/hydraulics/flight-system-pressure ne 1
        </test>
        <output>fcs/roll-trim-actuator</output>
    </switch> 

        <switch name="fcs/spoiler-differential-cmd">
            <description>Differential spoiler due to stick deflection</description>
            <default value="0"/>

            <test value="fcs/roll-trim-actuator">
                fcs/wing-sweep-cmd le 0.9117647058823529
                systems/hydraulics/combined-system-pressure ne 0
           </test>
            <output>fcs/spoiler-differential-cmd</output>
        </switch>
            <kinematic name="fcs/spoiler-differential-pos">
      <input>fcs/spoiler-differential-cmd</input>
      <traverse>
          <setting>
              <position>-1</position>
              <time>0.22</time> <!-- F14AAD-1 Figure 2-61 250 deg/sec sweep rate -->
          </setting>
          <setting>
              <position>1</position>
              <time>0.22</time> <!-- F14AAD-1 Figure 2-61 15 deg/sec sweep rate  -->
          </setting>
      </traverse>
                <output>fcs/spoiler-differential-pos</output>
   </kinematic>
                

    <aerosurface_scale name="Left Aileron Control">
        <input>fcs/roll-trim-actuator</input>
        <range>
        <min> -0.22807 </min>
        <max>  0.22807 </max>
        </range>
        <output>fcs/left-aileron-pos-rad</output>
    </aerosurface_scale>

   <aerosurface_scale name="Right Aileron Control">
      <input>fcs/roll-trim-actuator</input>
      <range>
        <min> -0.22807 </min>
        <max>  0.22807 </max>
      </range>
      <output>fcs/right-aileron-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="left aileron normalization">
      <input>fcs/left-aileron-pos-rad</input>
      <domain>
        <min> -0.22807 </min>
        <max>  0.22807 </max>
      </domain>
      <range>
        <min> -1 </min>
        <max>  1 </max>
      </range>
      <output>fcs/left-aileron-pos-norm</output>
   </aerosurface_scale>

   <aerosurface_scale name="right aileron normalization">
      <input>fcs/right-aileron-pos-rad</input>
      <domain>
        <min> -0.22807 </min>
        <max>  0.22807 </max>
      </domain>
      <range>
        <min> -1 </min>
        <max>  1 </max>
      </range>
      <output>fcs/right-aileron-pos-norm</output>
   </aerosurface_scale>



<!-- 
 * In the DMS model the static yawing moment coefficient was treated as
 * a function of three variables: alpha, beta, and stab deflection. 
 * The unusual influence of stabilator deflection on directional stability arises from
 * an interaction between the engine inlet shed vortex and the vertical and 
 * horizontal stabilizers, [Ref. 10].
 * Examination of the data indicated that this effect could be modeled as a yawing 
 * moment increment which was a function of alpha and stab deflection with a lookup
 * table using sin(8.2 beta). (See DCNDS)
 *-->
     <fcs_function name="aero/cn-sin-82beta">
       <function>
         <sin>
         <product>
             <property>aero/beta-rad</property>
             <value>8.2</value>
         </product>
        </sin>
       </function>
       <output>aero/cn-sin-82beta</output>
     </fcs_function>

<!-- yaw damper only active when in range alpha +/10 deg -->
   <switch name="fcs/yaw-damper-active">
       <default value="0.0"/>
       <test logic="AND" value="1">
            aero/alpha-rad ge -0.175438596491228
            aero/alpha-rad le  0.175438596491228
            fcs/yaw-damper-enable ne 0.0
        </test>
        <output>fcs/yaw-damper-active</output>
    </switch>

<!-- rudder limits +/-30deg 40 deg/sec-->
<!-- stabilizer limits +/7deg 30 deg/sec-->

   <pure_gain name="Pilot G">
      <input>accelerations/n-pilot-z-norm</input>
      <gain>-1</gain>
      <output>/accelerations/pilot-gdamped</output>
   </pure_gain>

   <scheduled_gain name="Yaw Damper Rate">
      <input>velocities/r-aero-rad_sec</input>
      <table>
        <independentVar lookup="row">velocities/ve-kts</independentVar>
         <tableData>
            30     0.00
            60     2.00
         </tableData>
      </table>
      <gain>fcs/yaw-damper-active</gain>
   </scheduled_gain>

   <switch name="fcs/pitch-damper-active">
       <default value="0.0"/>
       <test logic="AND" value="1">
            aero/alpha-rad ge -0.175438596491228
            aero/alpha-rad le  0.2631578947368421
            fcs/elevator-cmd-norm ge -0.15
            fcs/elevator-cmd-norm le 0.15
            fcs/pitch-damper-enable ne 0.0
        </test>
        <output>fcs/pitch-damper-active</output>
    </switch>

   <scheduled_gain name="Pitch Damper Rate">
<!-- Figure 2-57 F14AAD-1  -->
      <input>velocities/q-aero-rad_sec</input>
      <table>
        <independentVar lookup="row">velocities/ve-kts</independentVar>
         <tableData>
            30     0.00
            60     1
         </tableData>
      </table>
      <gain>fcs/pitch-damper-active</gain>
        <min> -0.2857142857142857 </min>
        <max>  0.2857142857142857 </max>
   </scheduled_gain>



  <summer name="Rudder Command Sum">
      <input>fcs/rudder-cmd-norm</input>
      <input>fcs/yaw-trim-cmd-norm</input>
      <clipto>
        <min> -1 </min>
        <max>  1 </max>
      </clipto>
   </summer>

   <summer name="Rudder Sum">
      <input>fcs/rudder-command-sum</input>
      <input>fcs/yaw-damper-rate</input>
      <clipto>
        <min> -1.1 </min>
        <max>  1.1 </max>
      </clipto>
   </summer>

<switch name="fcs/rudder-actuator-pos"> 
  <default value="fcs/rudder-sum"/> 
  <test value="fcs/rudder-actuator-pos"> 
    systems/hydraulics/flight-system-pressure ne 1
  </test> 
</switch> 
    <kinematic name="Rudder Control">
      <input>fcs/rudder-actuator-pos</input>
      <traverse>
          <setting>
              <position>-0.35</position>
              <time>0.90</time> <!-- based on 30 deg/sec -->
          </setting>
          <setting>
              <position>0.35</position>
              <time>0.90</time> <!-- based on 30 deg/sec -->
          </setting>
      </traverse>
      <output>fcs/rudder-pos-rad</output>
  </kinematic>

   <aerosurface_scale name="rudder normalization">
      <input>fcs/rudder-pos-rad</input>
      <domain>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </domain>
      <range>
        <min> -1 </min>
        <max>  1 </max>
      </range>
      <output>fcs/rudder-pos-norm</output>
   </aerosurface_scale>



      <switch name="fcs/flap-total-dmd">
          <default value="0"/>
          <test value="fcs/flap-total-dmd">
              systems/hydraulics/combined-system-pressure ne 1
          </test>
          <test value="fcs/flap-cmd-norm">
              fcs/flap-cmd-norm ne 0
              systems/hydraulics/combined-system-pressure ne 0
              fcs/wing-sweep-pos-deg le 50
          </test>
          <test value="systems/cadc/manuv-flap-extension-cmd">
              systems/cadc/manuv-flap-extension-cmd ne 0
              systems/hydraulics/combined-system-pressure ne 0
              fcs/wing-sweep-pos-deg le 50
          </test>
          <!--<clipto>
              <min> 0 </min>
              <max>  1 </max>
          </clipto>-->
          <output>fcs/flap-total-dmd</output>
      </switch>

      <switch name="fcs/aux-flap-total-dmd">
          <default value="0"/>
          <test value="fcs/aux-flap-total-dmd">
              systems/hydraulics/combined-system-pressure ne 1
          </test>
          <test value="fcs/flap-cmd-norm">
              fcs/flap-cmd-norm ne 0
              systems/hydraulics/combined-system-pressure ne 0
              fcs/wing-sweep-pos-deg le 22
          </test>
          <!--<clipto>
              <min> 0 </min>
              <max>  1 </max>
          </clipto>-->
          <output>fcs/aux-flap-total-dmd</output>
      </switch>

      <switch name="fcs/slat-total-dmd">
          <default value="0"/>
          <test value="fcs/slat-total-dmd">
              systems/hydraulics/combined-system-pressure ne 1
          </test>

          <test value="1">
              fcs/flap-total-dmd ge 0.5
              systems/hydraulics/combined-system-pressure ne 0
              fcs/wing-sweep-pos-deg le 50
          </test>

          <test value="fcs/slat-cmd">
              fcs/slat-cmd ne 0
              systems/hydraulics/combined-system-pressure ne 0
              fcs/wing-sweep-pos-deg le 50
          </test>
          <test value="systems/cadc/manuv-slat-extension-cmd">
              systems/cadc/manuv-slat-extension-cmd ne 0
              systems/hydraulics/combined-system-pressure ne 0
              fcs/wing-sweep-pos-deg le 50
          </test>
          <!--<clipto>
              <min> 0 </min>
              <max>  1 </max>
          </clipto>-->
          <output>fcs/slat-total-dmd</output>
      </switch>


   <kinematic name="Flaps Control">
         <input>fcs/flap-total-dmd</input>
     <traverse>
       <setting>
          <position>  0 </position>
          <time>      0 </time>
       </setting>
       <setting>
          <position> 10 </position>
          <time>    0.4 </time>
       </setting>
       <setting>
<!-- 01-F14AAD-1 figure 2-50 35 degrees  -->
          <position> 25 </position>
          <time>    1.0 </time>
       </setting>
       <setting>
<!-- 01-F14AAD-1 figure 2-50 35 degrees  -->
          <position> 35 </position>
          <time>    1.5 </time>
       </setting>
     </traverse>
     <output>fcs/flap-pos-deg</output>
   </kinematic>
   <kinematic name="Flaps Control">
         <input>fcs/aux-flap-total-dmd</input>
     <traverse>
       <setting>
          <position>  0 </position>
          <time>      0 </time>
       </setting>
       <setting>
          <position> 10 </position>
          <time>    0.4 </time>
       </setting>
       <setting>
<!-- 01-F14AAD-1 figure 2-50 35 degrees  -->
          <position> 25 </position>
          <time>    1.0 </time>
       </setting>
       <setting>
<!-- 01-F14AAD-1 figure 2-50 35 degrees  -->
          <position> 35 </position>
          <time>    1.5 </time>
       </setting>
     </traverse>
     <output>fcs/aux-flap-pos-deg</output>
   </kinematic>

   <aerosurface_scale name="flap normalization">
      <input>fcs/flap-pos-deg</input>
      <domain>
        <min>  0 </min>
        <max> 35 </max>
      </domain>
      <range>
        <min> 0 </min>
        <max> 1 </max>
      </range>
      <output>fcs/flap-pos-norm</output>
   </aerosurface_scale>

   <aerosurface_scale name="aux flap normalization">
      <input>fcs/aux-flap-pos-deg</input>
      <domain>
        <min>  0 </min>
        <max> 35 </max>
      </domain>
      <range>
        <min> 0 </min>
        <max> 1 </max>
      </range>
      <output>fcs/aux-flap-pos-norm</output>
   </aerosurface_scale>


   <kinematic name="Slats Control">
     <input>fcs/slat-total-dmd</input>
     <traverse>
       <setting>
          <position>  0 </position>
          <time>      0 </time>
       </setting>
       <setting>
          <position>  1 </position>
          <time>      1 </time>
       </setting>
     </traverse>
     <output>fcs/slat-cmd-norm</output>
   </kinematic>

   <aerosurface_scale name="Slat normalization">
      <input>fcs/slat-cmd-norm</input>
      <domain>
        <min>  0 </min>
        <max>  1 </max>
      </domain>
      <range>
        <min> 0 </min>
        <max> 17 </max>
      </range>
      <output>fcs/slat-pos-norm-deg</output>
   </aerosurface_scale>
      <switch name="gear/gear-dmd-norm">
          <default value="1"/>
          <test value="1"> <!-- always force gear down when on ground - to prevent inadvertant retraction -->
                position/aircraft-on-ground ne 0
          </test>
          <test value="gear/gear-dmd-norm">
              systems/hydraulics/combined-system-pressure ne 1
          </test>
          <test value="gear/gear-cmd-norm">
              systems/hydraulics/combined-system-pressure ne 0
          </test>
          <!--<clipto>
              <min> 0 </min>
              <max>  1 </max>
          </clipto>-->
          <output>gear/gear-dmd-norm</output>
      </switch>
   <kinematic name="Gear Control">
     <input>gear/gear-dmd-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>

      <switch name="fcs/speedbrake-dmd-norm">
          <default value="0"/>
          <test value="fcs/speedbrake-dmd-norm">
              systems/hydraulics/combined-system-pressure ne 1
          </test>
          <test value="fcs/speedbrake-cmd-norm">
              systems/hydraulics/combined-system-pressure ne 0
          </test>
          <!--<clipto>
              <min> 0 </min>
              <max>  1 </max>
          </clipto>-->
          <output>fcs/speedbrake-dmd-norm</output>
      </switch>

   <kinematic name="Speedbrake Control">
     <input>fcs/speedbrake-dmd-norm</input>
     <traverse>
       <setting>
          <position> 0 </position>
          <time>     0 </time>
       </setting>
       <!--<setting>
          <position> 0.3 </position>
          <time>     0.5 </time>
       </setting>
       <setting>
          <position> 0.6 </position>
          <time>     0.5 </time>
       </setting>-->
       <setting>
          <position> 1 </position>
          <time>     1.5 </time>
       </setting>
     </traverse>
     <output>fcs/speedbrake-pos-norm</output>
   </kinematic>

            <fcs_function name="aero/alpha-indicated-deg">
                <description>ARI nose probe; ref ADA101648 p84; alpha_true = .8122 alphaNOSEPROBE + .797deg</description>
                <function>
                    <product>
                        <sum>
                            <property> aero/alpha-deg </property>
                            <value> -0.797 </value>
                        </sum>
                        <value>1.231223836</value>
                    </product>
                </function>
            </fcs_function>
            <fcs_function name="aero/aero-rp-x-in">
              <function>
                  <description>Centre of pressure due to mach and wingsweep angle</description>
                  <!-- MAC is 16% cbar . cbar is 9.8ft giving us 18.81in as offset to %MAC -->
                  <sum>
                      <table>
                          <independentVar lookup="row">velocities/mach</independentVar>
                          <independentVar lookup="column">fcs/wing-sweep-cmd</independentVar>
                          <!-- mach 2.40 with wingsweep 22deg isn't in the envelope -->
                          <tableData>
                                    0.294117647       1.0
<!--                              0.00    -419           -429.1
                              2.40    -421           -429.6
                              0.00    -409           -419.1
                              2.40    -411           -419.6
-->
                                0.00    419           429.1
                                2.40    421           449.6
                          </tableData>
                      </table>
                  </sum>
              </function>
                <output>metrics/aero-rp-x-in</output>
          </fcs_function>

          <fcs_function name="aero/cadc-control-effectivity-factor">
              <function>
                  <description>High speeds CADC control effectivity limitation of rudder and stabilator</description>
                  <sum>
                      <table>
                          <independentVar lookup="row">velocities/mach</independentVar>
                          <!-- mach 2.40 with wingsweep 22deg isn't in the envelope -->
                          <tableData>
                              0.00  1.0
                                1.00  0.6
                                2.40  0.3
                          </tableData>
                      </table>
                  </sum>
              </function>
          </fcs_function>

          <!-- need %Cg in chord for moments [Xcg - Xref)/100] -->
          <summer name="cg-x-offset-chord-in">
              <input> inertia/cg-x-in</input>
              <input> -metrics/aero-rp-x-in</input>
              <output>inertia/cg-x-offset-chord-in</output>
          </summer>

        <pure_gain name="cg-x-chord-percent">
            <description>Percent offset of the CoP from the CG</description>
              <input>inertia/cg-x-offset-chord-in</input>
              <gain> -0.01</gain>
              <clipto>
                  <min> -1 </min>
                  <max> 1 </max>
              </clipto>
              <output> inertia/cg-x-mac-percent </output>
          </pure_gain>

        <fcs_function name="aero/two-vt">
            <function>
                <product>
                    <value>2</value>
                    <property>velocities/vt-fps</property>
                </product>
            </function>
            <clipto>
                <min> 0.0000000001 </min>
                <max>  4000 </max>
            </clipto>
            <output>aero/two-vt</output>
        </fcs_function>
        <fcs_function name="aero/cbarq-2vo">
                <description>For denormalization</description>
                <function>
                    <quotient>
                        <product>
                            <property>metrics/cbarw-ft</property>
                            <property>velocities/q-aero-rad_sec</property>
                        </product>
                        <!-- over -->
                       <property>aero/two-vt</property>
                    </quotient>
                </function>
                <clipto>
                    <min> -2.01 </min>
                    <max>  2.01 </max>
                </clipto>
                <output>aero/cbarq-2vo</output>
            </fcs_function>


        <fcs_function name="aero-cos-alpha">
              <function>
                  <product>
                      <cos>
                          <property>aero/alpha-rad</property>
                      </cos>
                  </product>
              </function>
              <output>aero/cos-alpha</output>
          </fcs_function>

       <fcs_function name="aero-sin-alpha">
              <function>
                  <product>
                      <sin>
                          <property>aero/alpha-rad</property>
                      </sin>
                  </product>
              </function>
              <output>aero/sin-alpha</output>
          </fcs_function>


      </channel>
  </flight_control>

<!--The roll(L) and yaw(N) moments are due to aerodynamics only, while
   the pitch(Z), includes a thrust term. These are given by.
   L = dynamic pressure * Wing Area * Reference Span * CL
   M = dynamic pressure * Wing Area * chord * CM + ZjT
   N = dynamic pressure * Wing Area * Reference Span * CN
   -->
 <aerodynamics>

<!-- rudimentary figures based of N2 and using values from NAVAIR 01-F14AAD-1 -->
   <function name="propulsion/engine[0]/EGT-R">
     <description>Engine 0 EGT Rankine</description>
     <sum>
       <property>atmosphere/T-R</property>
       <table>
         <independentVar>propulsion/engine[0]/n1</independentVar>
         <tableData>
          0	0.0
          20	0.0
          30	541.7
          49	541.7
          62	631.7
          78	1171.7
          95	1405.7
          99.9  1684.7
          104	1684.7
         </tableData>
       </table>
     </sum>
   </function>
   <function name="propulsion/engine[1]/EGT-R">
     <description>Engine 0 EGT Rankine</description>
     <sum>
       <property>atmosphere/T-R</property>
       <table>
         <independentVar>propulsion/engine[1]/n1</independentVar>
         <tableData>
          0	0.0
          20	0.0
          30	541.7
          49	541.7
          62	631.7
          78	1171.7
          95	1405.7
          99.9  1684.7
          104	1684.7
         </tableData>
       </table>
     </sum>
   </function>



   <function name="aero/coefficients/Cmach">
<!--    <description>Mach factor (all except drag) (NASA-TM-84643 Figure 3)</description> -->
    <description>Mach factor (all except drag) (NASA-TM-84643 Figure 3 Clalpha) and values for AOA derived from NASA-aaia-2000-0900 Figure 4</description>
    <product>
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <independentVar lookup="column">velocities/mach</independentVar>
            <tableData>
                       0.0  0.2     0.6         0.9         1.1         1.3         1.5         1.8         2.1         2.6         3.0
                       -20	1.00000000	1.00000000	0.96610485	1.23950808	1.41632259	1.34327421	1.13294356	0.93062904	0.76851372	0.58968226	0.51614275
                       -15	1.00000000	1.00000000	0.96116198	1.23316641	1.40907629	1.33640164	1.12714710	0.92586768	0.76458179	0.58666528	0.51350202
                       -10	1.00000000	1.00000000	0.99142346	1.27199174	1.45344001	1.37847726	1.16263449	0.95501794	0.78865408	0.60513601	0.52966925
                        -5	1.00000000	1.00000000	0.96759116	1.24141501	1.41850155	1.34534078	1.13468655	0.93206078	0.76969605	0.59058947	0.51693681
<!--                         0	1.00000000	1.00000000	1.19797000	1.53699000	1.75624000	1.66566000	1.40485000	1.15398000	0.95295700	0.73120600	0.64001700-->
                         4	1.00000000	1.00000000	0.95837601	1.22959201	1.40499202	1.33252801	1.12388001	0.92318401	0.76236561	0.58496481	0.51201361
                         8	1.00000000	1.00000000	0.99142346	1.27199174	1.45344001	1.37847726	1.16263449	0.95501794	0.78865408	0.60513601	0.52966925
                        12	1.00000000	1.00000000	0.96759116	1.24141501	1.41850155	1.34534078	1.13468655	0.93206078	0.76969605	0.59058947	0.51693681
                        16	1.00000000	1.00000000	0.98015728	1.25753729	1.43692365	1.36281274	1.14942274	0.94416546	0.77969210	0.59825946	0.52365028
                        20	1.00000000	1.00000000	0.96074823	1.23263556	1.40846972	1.33582635	1.12666189	0.92546912	0.76425265	0.58641274	0.51328097
                        24	1.00000000	1.00000000	0.96503140	1.23813085	1.41474891	1.34178168	1.13168474	0.92959501	0.76765981	0.58902706	0.51556926
                        28	1.00000000	1.00000000	0.96044147	1.23224199	1.40802001	1.33539984	1.12630217	0.92517363	0.76400864	0.58622551	0.51311708
                        32	1.00000000	1.00000000	0.96642959	1.23992472	1.41679867	1.34372573	1.13332438	0.93094186	0.76877204	0.58988048	0.51631624
                        40	1.00000000	1.00000000	0.95223257	1.22171001	1.39598566	1.32398617	1.11667565	0.91726616	0.75747865	0.58121503	0.50873147
                        45	1.00000000	1.00000000	0.95617790	1.22677185	1.40176956	1.32947176	1.12130231	0.92106662	0.76061706	0.58362314	0.51083926
                        50	1.00000000	1.00000000	0.95837601	1.22959201	1.40499202	1.33252801	1.12388001	0.92318401	0.76236561	0.58496481	0.51201361
            </tableData>
          </table>
       </product>
    </function>
    <function name="aero/coefficients/CdTNK">
    <description>Incremental Cd due to external tanks</description>
    <product>
          <property>fcs/external-tanks-fitted</property>
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
                    0.4 	0.0005
                    0.6 	0.0005
                    0.7 	0.0005
                    0.8 	0.0005
                    0.85	0.0011
                    0.9 	0.0065
                    0.94	0.0074
                    0.98	0.0077
                    1   	0.0078
                    1.1 	0.0079
                    1.2 	0.0080
                    2   	0.0081
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/coefficients/ClSweepFactor">
    <description>Wing sweep factor from norm of 22 (NASA-TM-D-6909)</description>
    <product>
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <independentVar lookup="column">fcs/wing-sweep-pos-deg</independentVar>
            <tableData>
                        0   	          22	      50	      58
                   0	1.000000	1.000000	0.791274    0.653661
                  10	1.000000	1.000000	0.829267	0.700928
                  15	1.000000	1.000000	0.953910	0.860083
                  20	1.000000	1.000000	0.960603	0.910701
                  25	1.000000	1.000000	0.958058	0.969330
                  30	1.000000	1.000000	1.027476	0.955345
                  35	1.000000	1.000000	1.088021	0.994762
                  40	1.000000	1.000000	1.083636	1.049773
                  45	1.000000	1.000000	1.066517	1.066517
                  50	1.000000	1.000000	0.910848	0.936149
                  55	1.000000	1.000000	0.921275	0.914270
            </tableData>
          </table>
       </product>
    </function>
    <function name="aero/coefficients/ClBAS">
    <description>Cl BASIC AFWAL-TR-80-3141 PartIII - Figure 36 </description>
    <product>
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <independentVar lookup="column">aero/beta-deg</independentVar>
            <tableData>
                              -20        -15        -10         -5          0          5         10         15         20 
               -55  -1.3463540  -1.3852470  -1.3945640  -1.4176920  -1.4273690  -1.4176920  -1.3945640  -1.3852470  -1.3463540
               -50  -1.4760110  -1.4999080  -1.5213490  -1.5467930  -1.5809450  -1.5467930  -1.5213190  -1.4999080  -1.4760110
               -45  -1.5671970  -1.6102240  -1.6171880  -1.6520130  -1.6689840  -1.6520130  -1.6171880  -1.6102240  -1.5671970
               -40  -1.6664090  -1.6917280  -1.7122880  -1.7481220  -1.7718120  -1.7481220  -1.7122880  -1.6917280  -1.6664090
               -35  -1.7330310  -1.7703260  -1.8407520  -1.8705200  -1.9301090  -1.8705200  -1.8407520  -1.7703260  -1.7330310
               -30  -1.7201080  -1.7904460  -1.8528920  -1.8981360  -1.9270530  -1.8981360  -1.8528920  -1.7904460  -1.7201080
               -25  -1.6404500  -1.6989470  -1.7400030  -1.7662890  -1.7744220  -1.7662890  -1.7400030  -1.6989470  -1.6404500
               -20  -1.4394210  -1.5154020  -1.5632960  -1.5696730  -1.6031600  -1.5696730  -1.5632960  -1.5154020  -1.4394210
               -15  -1.2135860  -1.2448890  -1.2844040  -1.2762190  -1.2789460  -1.2762190  -1.2844040  -1.2448890  -1.2135860
               -10  -0.9215569  -0.9808749  -1.0017560  -1.0194540  -1.0129430  -1.0194540  -1.0017560  -0.9808749  -0.9215569
                -5  -0.5286301  -0.5746194  -0.6024052  -0.6185578  -0.5813407  -0.6185578  -0.6024052  -0.5746194  -0.5286301
                 0      0.06145000 0.14705000 0.10985000 0.14555000 0.07760000 0.14555000 0.10985000 0.14705000 0.06145000 
                 5      0.52863010 0.57461940 0.60240520 0.61855780 0.58134070 0.61855780 0.60240520 0.57461940 0.52863010 
                 10     0.92155690 0.98087490 1.00175600 1.01945400 1.01294300 1.01945400 1.00175600 0.98087490 0.92155690 
                 15     1.21358600 1.24488900 1.28440400 1.27621900 1.27894600 1.27621900 1.28440400 1.24488900 1.21358600 
                 20     1.43942100 1.51540200 1.56329600 1.56967300 1.60316000 1.56967300 1.56329600 1.51540200 1.43942100 
                 25     1.64045000 1.69894700 1.74000300 1.76628900 1.77442200 1.76628900 1.74000300 1.69894700 1.64045000 
                 30     1.72010800 1.79044600 1.85289200 1.89813600 1.92705300 1.89813600 1.85289200 1.79044600 1.72010800 
                 35     1.73303100 1.77032600 1.84075200 1.87052000 1.93010900 1.87052000 1.84075200 1.77032600 1.73303100 
                 40     1.66640900 1.69172800 1.71228800 1.74812200 1.77181200 1.74812200 1.71228800 1.69172800 1.66640900 
                 45     1.56719700 1.61022400 1.61718800 1.65201300 1.66898400 1.65201300 1.61718800 1.61022400 1.56719700 
                 50     1.47601100 1.49990800 1.52134900 1.54679300 1.58094500 1.54679300 1.52131900 1.49990800 1.47601100 
                 55     1.34635400 1.38524700 1.39456400 1.41769200 1.42736900 1.41769200 1.39456400 1.38524700 1.34635400 
            </tableData>
          </table>
       </product>
    </function>

     <function name="aero/coefficients/DClSLM">
         <description>Delta Cl due to mean slat position</description>
         <product>
             <table>
                 <independentVar lookup="row">aero/alpha-deg</independentVar>
                 <independentVar lookup="column">fcs/slat-pos-norm-deg</independentVar>
                 <tableData>
                        	   0   	   8	     17
                        -20	0.0000	-0.0355	-0.0321
                        -15	0.0000	-0.0321	-0.0256
                        -10	0.0000	-0.0256	-0.0203
                        -5	0.0000	-0.0203	-0.0116
                         0	0.0000	-0.0116	0.0016
                         5	0.0000	0.0016	0.0116
                        10	0.0000	0.0116	0.0203
                        15	0.0000	0.0203	0.0256
                        20	0.0000	0.0256	0.0321
                        25	0.0000	0.0321	0.0355
                        30	0.0000	0.0355	0.0385
                        35	0.0000	0.0385	0.0386
                        40	0.0000	0.0386	0.0354
                        45	0.0000	0.0354	0.0334
                        50	0.0000	0.0334	0.0316
                        55	0.0000	0.0316	0.0285
                 </tableData>
          </table>
       </product>
    </function>
    <function name="aero/coefficients/ClDFM">
    <description>Delta Cl due to mean flap position</description>
    <product>
          <table>
            <independentVar lookup="row">fcs/flap-pos-deg</independentVar>
            <independentVar lookup="column">aero/alpha-deg</independentVar>
            <tableData>
                            	-20     	  -5	      0 	  5 	 10 	 25 	 50
                     0	 0.00000	 0.00000	0.00000	0.00000	0.00000	0.00000	0.00000
                         10	-0.01400	-0.13160	0.13440	0.13160	0.12880	0.10920	0.01400
                         35	-0.09016	-0.25872	0.25480	0.25872	0.29872	0.21560	0.22540
                         50	-0.24500	-0.60200	0.59500	0.60200	0.58800	0.46200	0.24500
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/coefficients/ClDAFM">
    <description>Delta Cl due to mean aux flap position</description>
    <product>
          <table>
            <independentVar lookup="row">fcs/aux-flap-pos-deg</independentVar>
            <independentVar lookup="column">aero/alpha-deg</independentVar>
            <tableData>
                                   	 -20     	  -5	      0 	  5 	 10 	 25 	 50
                     0	 0.00000	 0.00000	0.00000	0.00000	0.00000	0.00000	0.00000
                    10	-0.00600	-0.05640	0.05760	0.05640	0.05520	0.04680	0.00600
                           35	-0.03864	-0.11088	0.10920	0.11088	0.11088	0.09240	0.09660
                    50	-0.10500	-0.25800	0.25500	0.25800	0.25200	0.19800	0.10500
            </tableData>
          </table>
       </product>
    </function>

        <function name="aero/coefficients/ClDSpL">
            <description>Delta Cl due to left spoiler deflection - Figure 8, NASA-TB D-8236 </description>
<!-- F14-AAD-1, 14.12.7; fully deployed No.4 spoiler at 200 kts 20,000 feet 25deg/sec roll rate at 22deg, 4deg/sec wings at 62deg -->
    <product>
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
                    <independentVar lookup="column">fcs/spoiler-left-pos</independentVar>
            <tableData>
	                        0             	35     	55
                       -10	0.00000000	 0.00000000	 0.00000000
                        -5	0.00000000	 0.15275742	 0.37718051
                         0	0.00000000	-0.01293512	-0.03761468
                         5	0.00000000	-0.07568472	-0.24971231
                        10	0.00000000	 0.00000000	 0.00000000
            </tableData>
          </table>
            </product>
        </function>

        <function name="aero/coefficients/ClDSpR">
            <description>Delta Cl due to right spoiler deflection - Figure 8, NASA-TB D-8236 </description>
            <product>
                <table>
                    <independentVar lookup="row">aero/alpha-deg</independentVar>
                    <independentVar lookup="column">fcs/spoiler-right-pos</independentVar>
            <tableData>
	                        0             	35     	55
                       -10	0.00000000	 0.00000000	 0.00000000
                        -5	0.00000000	 0.15275742	 0.37718051
                         0	0.00000000	-0.01293512	-0.03761468
                         5	0.00000000	-0.07568472	-0.24971231
                        10	0.00000000	 0.00000000	 0.00000000
            </tableData>
                </table>
            </product>
        </function>

        <function name="aero/coefficients/ClDasym">
            <description>Delta Cl due to wing asymmetry</description>
            <product>
                <property>aero/wing-asymmetry</property> <!-- sqr to remove the sign (value either -1, 0 or 1 -->
                <property>aero/wing-asymmetry</property>
                <property>aero/coefficients/ClBAS</property>
                <value>-0.3</value>
       </product>
    </function>

     <function name="aero/coefficients/ClUC">
         <description>Cl increment due to gear</description>
         <product>
             <property>gear/gear-pos-norm</property>
             <table>
                 <independentVar lookup="row">aero/alpha-deg</independentVar>
                 <tableData>
                     -10	 -0.00
                     0 	 -0.0012
                     8 	 -0.0010
                     12    -0.0004
                     14    -0.0002
                     16    -0.0001
                     18    -0.000
                 </tableData>
             </table>
         </product>
     </function>

     <function name="aero/coefficients/ClDS1">
         <description>ClDS1 AFWAL-TR-80-3141 PartIII - Figure 38</description>
         <product>
             <property>aero/cadc-control-effectivity-factor</property>
             <table>
                 <independentVar lookup="row">aero/alpha-deg</independentVar>
                 <tableData>
                     -65  0.0065000
                     -55  0.0065000
                     -50  0.0070000
                     -45  0.0060000
                     -40  0.0045000
                     -35  0.0115000
                     -30  0.0130000
                     -25  0.0145000
                     -20  0.0165000
                     -15  0.0150000
                     -10  0.0135000
                     -5  0.0125000
                     0 0.01650000
                     5 0.01250000
                     10 0.01350000
                     15 0.01500000
                     20 0.01650000
                     25 0.01450000
                     30 0.01300000
                     35 0.01150000
                     40 0.00450000
                     45 0.00600000
                     50 0.00700000
                     55 0.00650000
                 </tableData>
             </table>
         </product>
     </function>

     <function name="aero/coefficients/ClDS2">
            <description>ClDS2 AFWAL-TR-80-3141 PartIII - Figure 39</description>
         <product>
             <property>aero/cadc-control-effectivity-factor</property>
             <table>
                 <independentVar lookup="row">aero/alpha-deg</independentVar>
                 <tableData>
                     -60  -0.00550000
                     -55  -0.00550000
                     -50  -0.00800000
                     -45  -0.01100000
                     -40  -0.01200000
                     -30  0.01250000
                     -10  -0.01150000
                     -5 -0.00350000
                     0  0.00650000
                     5  0.00950000
                     10  0.01150000
                     15  0.01250000
                     20  0.01200000
                     25  0.01250000
                     30  0.01250000
                     35  0.01350000
                     40  0.01200000
                     45  0.01100000
                     50  0.00800000
                     55  0.00550000
                 </tableData>
             </table>
         </product>
     </function>
     <function name="aero/coefficients/DClDS1">
         <description>DClDS1</description>
         <product>
             <property>fcs/stabilizer-1p-factor</property>
             <property>aero/coefficients/ClDS1</property>
             <property>fcs/elevator-pos-deg</property>
         </product>
     </function>
     <function name="aero/coefficients/DClDS2">
         <description>DClDS2</description>
         <product>
             <property>fcs/stabilizer-2p-factor</property>
             <sum>
                 <product>
                     <value>-10</value>
                     <property>aero/coefficients/ClDS1</property>
                 </product>
                 <product>
                     <sum>
                         <value>10</value>
                         <property>fcs/elevator-pos-deg</property>
                     </sum>
                     <property>aero/coefficients/ClDS2</property>
                 </product>
             </sum>
         </product>
     </function>
     <function name="aero/coefficients/Cl">
         <sum>
             <property>aero/coefficients/ClBAS</property>
             <property>aero/coefficients/DClDS1</property>
             <property>aero/coefficients/DClDS2</property>
             <property>aero/coefficients/ClUC</property>
             <property>aero/coefficients/ClDFM</property>
             <property>aero/coefficients/ClDAFM</property>
             <property>aero/coefficients/DClSLM</property>
                <property>aero/coefficients/ClDSpL</property>
                <property>aero/coefficients/ClDSpR</property>
                <property>aero/coefficients/ClDasym</property>
         </sum>
     </function>
     <function name="aero/coefficients/CdUC">
    <description>Cd increment due to gear</description>
    <product>
          <property>gear/gear-pos-norm</property>
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <tableData>
                -10 0
                        -5	0.00017
                        0	0.00001
                        5	0.00005
                10  0
            </tableData>
          </table>
       </product>
    </function>
    <function name="aero/coefficients/CdDSp">
    <description>CD increment due to spoiler deflection</description>
    <product>
          <sum>
            <property>fcs/spoiler-left-pos</property>
            <property>fcs/spoiler-right-pos</property>
          </sum>
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <tableData>
                -10 0
                        -5  0.00055
                        0	0.000572727
                        5	0.00055
                10	0
            </tableData>
          </table>
       </product>
    </function>
    <function name="aero/coefficients/CdDBRK">
       <description>Drag due to speedbrakes</description>
         <product>
           <property>fcs/speedbrake-pos-norm</property>
           <table>
             <independentVar lookup="row">aero/alpha-deg</independentVar>
             <tableData>
                 -25	0.0210
                 -20	0.0210
                 -15	0.0414	
                  -5	0.0650
                   0	0.0784
                   5	0.0650
                  15	0.0514	
                  25	0.0210
                  40	0.0210
             </tableData>
           </table>
         </product>
    </function>
   <function name="aero/coefficients/CdMach">
            <description>Drag increment due to mach (NASA-TP-2580 Figure 16)</description>
    <product>
          <property>Factor1</property>
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
                <!-- This follows the basic shape to provide a factor that has been tuned to match known performance characteristics and may well be wrong 
                              based on tp2580 but tuned to meet F14-AAD-1 -->
                        0.20	0.00000
                        0.80	0.02472
                        0.84	0.02772
                        0.90	0.02520
                        0.94	0.05736
                        0.98	0.07676
                        0.99	0.08288
                        1.00	0.08495
                        1.03	0.05483
                        1.20	0.05102
                        1.25	0.03375
                        1.70	0.02500
                        2.00	0.02260
                        2.17	0.02190
                        2.47	0.02179
            </tableData>
          </table>
       </product>
    </function>

     <function name="aero/coefficients/CdBAS">
    <description>CdBAS</description>
    <product>
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <independentVar lookup="column">aero/beta-deg</independentVar>
            <tableData>
                               -20        -15        -10         -5          0          5         10         15         20 
                 -55  1.9057060  1.9638670  1.9824910  2.0215360  2.0346590  2.0215360  1.9824910  1.9638670  1.9057060
                 -50  1.7487740  1.7823090  1.8147060  1.8496190  1.8904750  1.8496190  1.8147060  1.7823090  1.7487740
                 -45  1.5633070  1.6125570  1.6255330  1.6640350  1.6835510  1.6640350  1.6255330  1.6125570  1.5633070
                 -40  1.3982170  1.4247500  1.4480080  1.4831660  1.5048720  1.4831660  1.4480080  1.4247500  1.3982170
                 -35  1.2114060  1.2437470  1.2945860  1.3212890  1.3625860  1.3212890  1.2945860  1.2437470  1.2114060
                 -30  0.9869851  1.0310580  1.0684970  1.0958310  1.1130460  1.0958310  1.0684970  1.0310580  0.9869851
                 -25  0.7523102  0.7825773  0.8042048  0.8174002  0.8211373  0.8174002  0.8042048  0.7825773  0.7522102
                 -20  0.5123598  0.5432075  0.5629274  0.5651420  0.5772239  0.5651420  0.5629274  0.5432075  0.5123598
                 -15  0.3116691  0.3275625  0.3448796  0.3454817  0.3463160  0.3454817  0.3448796  0.3275625  0.3116691
                 -10  0.1407652  0.1565048  0.1624715  0.1677752  0.1678456  0.1677752  0.1624715  0.1565048  0.1407652
                  -5  0.0433883  0.0478133  0.0532055  0.0561746  0.0581886  0.0561746  0.0532035  0.0478133  0.0433883
                 0      0.01700000 0.01705000 0.02160000 0.02295000 0.02520000 0.02295000 0.02160000 0.01705000 0.01700000 
                 5      0.04338825 0.04781333 0.05320554 0.05617464 0.05818861 0.05617464 0.05320354 0.04781333 0.04338825 
                 10     0.14076520 0.15650480 0.16247150 0.16777520 0.16784560 0.16777520 0.16247150 0.15650480 0.14076520 
                 15     0.31166910 0.32756250 0.34487960 0.34548170 0.34631600 0.34548170 0.34487960 0.32756250 0.31166910 
                 20     0.51235980 0.54320750 0.56292740 0.56514200 0.57722390 0.56514200 0.56292740 0.54320750 0.51235980 
                 25     0.75231020 0.78257730 0.80420480 0.81740020 0.82113730 0.81740020 0.80420480 0.78257730 0.75221020 
                 30     0.98698510 1.03105800 1.06849700 1.09583100 1.11304600 1.09583100 1.06849700 1.03105800 0.98698510 
                 35     1.21140600 1.24374700 1.29458600 1.32128900 1.36258600 1.32128900 1.29458600 1.24374700 1.21140600 
                 40     1.39821700 1.42475000 1.44800800 1.48316600 1.50487200 1.48316600 1.44800800 1.42475000 1.39821700 
                 45     1.56330700 1.61255700 1.62553300 1.66403500 1.68355100 1.66403500 1.62553300 1.61255700 1.56330700 
                 50     1.74877400 1.78230900 1.81470600 1.84961900 1.89047500 1.84961900 1.81470600 1.78230900 1.74877400 
                 55     1.90570600 1.96386700 1.98249100 2.02153600 2.03465900 2.02153600 1.98249100 1.96386700 1.90570600 
            </tableData>
          </table>
       </product>
    </function>
    <function name="aero/coefficients/CdDSLM">
    <description>Delta Cd due to mean slat position</description>
    <product>
          <table>
                    <independentVar lookup="row">aero/alpha-deg</independentVar>
                    <independentVar lookup="column">fcs/slat-pos-norm-deg</independentVar>
            <tableData>
                            	     0       8	    17
                        -20 	0.0000	0.0082	0.0057
                        -15 	0.0000	0.0057	0.0035
                        -10 	0.0000	0.0035	0.0017
                         -5 	0.0000	0.0017	0.0006
                          0 	0.0000	0.0006	0.0002
                          5 	0.0000	0.0002	0.0006
                         10 	0.0000	0.0006	0.0017
                         15 	0.0000	0.0017	0.0035
                         20 	0.0000	0.0035	0.0057
                         25 	0.0000	0.0057	0.0082
                         30 	0.0000	0.0082	0.0110
                         35 	0.0000	0.0110	0.0132
                         40 	0.0000	0.0132	0.0148
                         45 	0.0000	0.0148	0.0166
                         50 	0.0000	0.0166	0.0185
                         55 	0.0000	0.0185	0.0202
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/coefficients/CdDFM">
    <description>Delta Cd due to mean flap position</description>
    <product>
          <table>
            <independentVar lookup="row">fcs/flap-pos-deg</independentVar>
            <independentVar lookup="column">aero/alpha-deg</independentVar>
            <tableData>
                            	-20 	 -5 	  0 	  5 	 10 	 25	 50
                       0	0.00000	0.00000	0.00000	0.00000	0.00000	0.00000	0.00000
                      10	0.01400	0.02268	0.01932	0.02268	0.02548	0.02856	0.09590
                      35	0.09016	0.06894	0.06222	0.06894	0.09862	0.14286	0.55734
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/coefficients/CdDAFM">
    <description>Delta Cd due to mean flap position</description>
    <product>
          <table>
            <independentVar lookup="row">fcs/aux-flap-pos-deg</independentVar>
            <independentVar lookup="column">aero/alpha-deg</independentVar>
            <tableData>
                            	-20 	 -5 	  0 	  5 	 10 	 25 	 50
                       0	0.00000	0.00000	0.00000	0.00000	0.00000	0.00000	0.00000
                      10	0.00600	0.00972	0.00828	0.00972	0.01092	0.01224	0.04110
                      35	0.03864	0.02954	0.02666	0.02954	0.04226	0.06122	0.23886
            </tableData>
          </table>
       </product>
    </function>

     <function name="aero/coefficients/CdDS1">
         <description>CdDS1</description>
         <product>
             <property>aero/cadc-control-effectivity-factor</property>
             <table>
                 <independentVar lookup="row">aero/alpha-deg</independentVar>
                 <tableData>
                    -65  0.01400000
                    -55  0.01400000
                    -10  0.00180000
                     -5 -0.00030000
                      0 -0.00120000
                      5 0.00030000
                     10 0.00180000
                     15 0.00400000
                     20 0.00620000
                     25 0.00750000
                     30 0.00950000
                     35 0.01050000
                     40 0.00750000
                     45 0.00900000
                     50 0.01250000
                     55 0.01400000
                 </tableData>
             </table>
         </product>
     </function>

     <function name="aero/coefficients/CdDS2">
         <description>CdDS2</description>
         <product>
             <property>aero/cadc-control-effectivity-factor</property>
             <table>
                 <independentVar lookup="row">aero/alpha-deg</independentVar>
                 <tableData>
                     -65 0.00900000
                     -55 0.00900000
                     -30 0.00600000
                     -10 -0.00100000
                     -5 -0.00030000
                      0 -0.00330000
                      5 -0.00250000
                     10 -0.00100000
                     15 0.00050000
                     20 0.00200000
                     25 0.00400000
                     30 0.00600000
                     35 0.00850000
                     40 0.00950000
                     45 0.01100000
                     50 0.01050000
                     55 0.00900000
                 </tableData>
             </table>
         </product>
     </function>

     <function name="aero/coefficients/DCdDS1">
         <description>DCdDS1</description>
         <product>
             <property>fcs/stabilizer-1p-factor</property>
             <property>aero/coefficients/CdDS1</property>
             <property>fcs/elevator-pos-deg</property>
         </product>
     </function>
     
     <function name="aero/coefficients/DCdDS2">
         <description>DCdDS2</description>
         <product>
             <property>fcs/stabilizer-2p-factor</property>
             <sum>
                 <product>
                     <value>-10</value>
                     <property>aero/coefficients/CdDS1</property>
                 </product>
                 <product>
                     <sum>
                         <value>10</value>
                         <property>fcs/elevator-pos-deg</property>
                     </sum>
                     <property>aero/coefficients/CdDS2</property>
                 </product>
             </sum>
         </product>
     </function>
        <function name="aero/coefficients/CdDasym">
            <description>Delta Cl due to wing asymmetry</description>
            <product>
                <property>aero/wing-asymmetry</property> <!-- sqr to remove the sign (value either -1, 0 or 1 -->
                <property>aero/wing-asymmetry</property>
                <property>aero/coefficients/CdBAS</property>
                <value>-0.3</value>
            </product>
        </function>
     
     <function name="aero/coefficients/Cd">
             <sum>
                    <property>aero/coefficients/CdMach</property>
                 <property>aero/coefficients/CdBAS</property>
                 <property>aero/coefficients/DCdDS1</property>
                 <property>aero/coefficients/DCdDS2</property>
                 <property>aero/coefficients/CdUC</property>
                 <property>aero/coefficients/CdDFM</property>
                 <property>aero/coefficients/CdDAFM</property>
                 <property>aero/coefficients/CdDSLM</property>
                 <property>aero/coefficients/CdDBRK</property>
                 <property>aero/coefficients/CdTNK</property>
                 <property>aero/coefficients/CdDSp</property>
                    <property>aero/coefficients/CdDasym</property>
             </sum>
     </function>


     <function name="aero/coefficients/CyBAS">
         <description>CyBAS</description>
         <product>
             <table>
                 <independentVar lookup="row">aero/alpha-deg</independentVar>
                 <independentVar lookup="column">aero/beta-deg</independentVar>
                 <tableData>
                                    -20     -15     -10      -5       0        5          10          15         20
                        -20 	0.20490	0.15870	0.10830	0.05500	0.00000	-0.05500	-0.10830	-0.15870	-0.20490
                        -11 	0.20490	0.15870	0.10830	0.05500	0.00000	-0.05500	-0.10830	-0.15870	-0.20490
                        -10 	0.28855	0.20370	0.14100	0.06940	0.00000	-0.06940	-0.14100	-0.20370	-0.28855
                          0 	0.29415	0.21760	0.14620	0.06380	0.00000	-0.06380	-0.14620	-0.21760	-0.29415
                          5 	0.30055	0.22180	0.14645	0.07015	0.00000	-0.07015	-0.14645	-0.22180	-0.30055
                         10 	0.28855	0.20370	0.14100	0.06940	0.00000	-0.06940	-0.14100	-0.20370	-0.28855
                         15 	0.24630	0.16780	0.11240	0.05945	0.00000	-0.05945	-0.11240	-0.16780	-0.24630
                         20 	0.20490	0.15870	0.10830	0.05500	0.00000	-0.05500	-0.10830	-0.15870	-0.20490
                         25 	0.18955	0.15275	0.11775	0.06045	0.00000	-0.06045	-0.11775	-0.15275	-0.18955
                         30 	0.21465	0.17815	0.13310	0.07580	0.00000	-0.07580	-0.13310	-0.17815	-0.21465
                         35 	0.23860	0.18665	0.14605	0.07135	0.00000	-0.07135	-0.14605	-0.18665	-0.23860
                         40 	0.25660	0.20260	0.14505	0.07680	0.00000	-0.07680	-0.14505	-0.20260	-0.25660
                         45 	0.26760	0.22235	0.16075	0.09275	0.00000	-0.09275	-0.16075	-0.22235	-0.26760
                         50 	0.27370	0.22075	0.15150	0.07865	0.00000	-0.07865	-0.15150	-0.22075	-0.27370
                         55 	0.24915	0.19150	0.13150	0.07155	0.00000	-0.07155	-0.13150	-0.19150	-0.24915
                 </tableData>
             </table>
         </product>
     </function>
     <function name="aero/coefficients/CyP">
    <description>CyP</description>
    <product>
          <property>aero/bi2vel</property>
          <property>velocities/p-aero-rad_sec</property>
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <tableData>
                    -20	-0.15960
                    -15	-0.15960
                    -10	-0.12500
                     -5	 0.00000
                      0 0.14900000
                      5 0.26860000
                     10 0.12500000
                     15 0.15960000
                     20 0.32640000
                     25 0.38000000
                     30 0.67990000
                     35 0.56030000
                     40 0.93200000
                     45 0.13920000
                     50 -0.69600000
                     55 -0.38180000
                </tableData>
          </table>
       </product>
    </function>
    <function name="aero/coefficients/CyR">
    <description>CyR</description>
    <product>
          <property>aero/bi2vel</property>
          <property>velocities/r-aero-rad_sec</property>
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <tableData>
                    -25	 0.82000
                    -20	 0.82000
                    -15	 0.80000
                    -10	 0.60000
                    -5	 0.56840
                      0 0.56840000
                      5 0.53560000
                     10 0.49960000
                     15 0.67820000
                     20 0.52950000
                     25 0.27120000
                     30 -0.73430000
                     35 -1.31730000
                     40 -2.05310000
                     45 -0.76880000
                     50 -0.28850000
                     55 -0.12060000
            </tableData>
          </table>
       </product>
    </function>
    <function name="aero/coefficients/CyDA">
    <description>CyDA</description>
    <product>
          <property>fcs/left-aileron-pos-deg</property>
          <property>aero/cadc-control-effectivity-factor</property>
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <tableData>
                     -5 -0.00095000
                      0 -0.00095000
                      5 -0.00100000
                     10 -0.00085000
                     15 -0.00065000
                     20 -0.00030000
                     25 0.00010000
                     30 0.00060000
                     35 0.00160000
                     40 0.00240000
                     45 0.00250000
                     50 0.00255000
                     55 0.00265000
            </tableData>
          </table>
       </product>
    </function>
    <function name="aero/coefficients/CyDR">
    <description>CyDR</description>
    <product>
          <property>fcs/rudder-pos-deg</property>
          <property>aero/cadc-control-effectivity-factor</property>
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <independentVar lookup="column">aero/beta-deg</independentVar>
            <tableData>
                               -20        -15        -10         -5          0          5         10         15         20 
                -10     0.00450000 0.00485000 0.00520000 0.00530000 0.00530000 0.00530000 0.00520000 0.00485000 0.00430000 
                -5      0.00450000 0.00485000 0.00520000 0.00530000 0.00530000 0.00530000 0.00520000 0.00485000 0.00430000 
                 0      0.00480000 0.00520000 0.00560000 0.00560000 0.00560000 0.00560000 0.00560000 0.00520000 0.00480000 
                 5      0.00450000 0.00485000 0.00520000 0.00530000 0.00530000 0.00530000 0.00520000 0.00485000 0.00430000 
                 10     0.00430000 0.00450000 0.00480000 0.00495000 0.00510000 0.00500000 0.00480000 0.00450000 0.00420000 
                 15     0.00370000 0.00400000 0.00430000 0.00450000 0.00470000 0.00450000 0.00430000 0.00400000 0.00370000 
                 20     0.00330000 0.00355000 0.00380000 0.00400000 0.00420000 0.00400000 0.00380000 0.00355000 0.00330000 
                 25     0.00280000 0.00305000 0.00330000 0.00350000 0.00370000 0.00350000 0.00330000 0.00305000 0.00280000 
                 30     0.00230000 0.00250000 0.00270000 0.00289000 0.00310000 0.00290000 0.00270000 0.00250000 0.00230000 
                 35     0.00160000 0.00180000 0.00200000 0.00220000 0.00240000 0.00220000 0.00200000 0.00180000 0.00160000 
                 40     0.00100000 0.00110000 0.00120000 0.00135000 0.00150000 0.00135000 0.00120000 0.00110000 0.00100000 
                 45     0.00030000 0.00035000 0.00040000 0.00045000 0.00050000 0.00045000 0.00040000 0.00035000 0.00030000 
                 50     0.00000000 0.00000000 0.00000000 0.00000000 0.00000000 0.00000000 0.00000000 0.00000000 0.00000000 
                 55     0.00000000 0.00000000 0.00000000 0.00000000 0.00000000 0.00000000 0.00000000 0.00000000 0.00000000 
            </tableData>
          </table>
       </product>
    </function>
<!--
    <function name="aero/coefficients/CyDSP">
    <description>Yaw increment due to spoilers</description>
    <product>
          <sum>
            <property>fcs/spoiler-left-pos</property>
            <property>fcs/spoiler-right-pos</property>
          </sum>
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <tableData>
                      0 0.00000000
                      5 0.00000000
                     10 0.00000000
                     15 0.00000000
                     20 0.00000000
                     25 0.00000000
                     30 0.00000000
                     35 0.00000000
                     40 0.00000000
                     45 0.00000000
                     50 0.00000000
                     55 0.00000000
            </tableData>
          </table>
       </product>
    </function>
-->
    <function name="aero/coefficients/Cy">
    <sum>
          <property>aero/coefficients/CyBAS</property>
          <property>aero/coefficients/CyP</property>
          <property>aero/coefficients/CyR</property>
          <property>aero/coefficients/CyDA</property>
          <property>aero/coefficients/CyDR</property>
       </sum>
    </function>
    <function name="aero/coefficients/CLBAS">
    <description>CLBAS</description>
    <product>
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <independentVar lookup="column">aero/beta-deg</independentVar>
            <tableData>
                               -20        -15        -10         -5          0          5         10         15         20 
                -45     0.06100000 0.04600000 0.03050000 0.01500000 0.00000000 -0.01500000 -0.03050000 -0.04600000 -0.06100000 
                -35     0.04750000 0.03600000 0.02450000 0.01250000 0.00000000 -0.01250000 -0.02450000 -0.03600000 -0.04750000 
                -30     0.04900000 0.03766667 0.02533333 0.01366667 0.00000000 -0.01366667 -0.02533333 -0.03766667 -0.04900000 
                -20     0.05500000 0.04100000 0.02700000 0.01600000 0.00000000 -0.01600000 -0.02700000 -0.04100000 -0.05500000 
                -15     0.04700000 0.03650000 0.02650000 0.01350000 0.00000000 -0.01350000 -0.02650000 -0.03650000 -0.04700000 
                -10     0.03100000 0.02600000 0.02100000 0.01050000 0.00000000 -0.01050000 -0.02100000 -0.02600000 -0.03100000 
                -5      0.02500000 0.01700000 0.01350000 0.00650000 0.00000000 -0.00650000 -0.01350000 -0.01700000 -0.02050000 

                 0      0.00950000 0.00800000 0.00600000 0.00300000 0.00000000 -0.00300000 -0.00600000 -0.00800000 -0.00950000 
                 5      0.02500000 0.01700000 0.01350000 0.00650000 0.00000000 -0.00650000 -0.01350000 -0.01700000 -0.02050000 
                 10     0.03100000 0.02600000 0.02100000 0.01050000 0.00000000 -0.01050000 -0.02100000 -0.02600000 -0.03100000 
                 15     0.04700000 0.03650000 0.02650000 0.01350000 0.00000000 -0.01350000 -0.02650000 -0.03650000 -0.04700000 
                 20     0.05500000 0.04100000 0.02700000 0.01600000 0.00000000 -0.01600000 -0.02700000 -0.04100000 -0.05500000 
                 25     0.05250000 0.03933333 0.02616667 0.01483333 0.00000000 -0.01483333 -0.02616667 -0.03933333 -0.05250000 
                 30     0.04900000 0.03766667 0.02533333 0.01366667 0.00000000 -0.01366667 -0.02533333 -0.03766667 -0.04900000 
                 35     0.04750000 0.03600000 0.02450000 0.01250000 0.00000000 -0.01250000 -0.02450000 -0.03600000 -0.04750000 
                 40     0.05200000 0.03900000 0.02550000 0.01300000 0.00000000 -0.01300000 -0.02550000 -0.03900000 -0.05200000 
                 45     0.06100000 0.04600000 0.03050000 0.01500000 0.00000000 -0.01500000 -0.03050000 -0.04600000 -0.06100000 
                 50     0.06450000 0.04850000 0.03300000 0.01650000 0.00000000 -0.01650000 -0.03300000 -0.04850000 -0.06450000 
                 55     0.06500000 0.04950000 0.03350000 0.01650000 0.00000000 -0.01650000 -0.03350000 -0.04950000 -0.06500000 
            </tableData>
          </table>
       </product>
    </function>
    <function name="aero/coefficients/CLP">
    <description>CLP</description>
    <product>
          <property>aero/bi2vel</property>
          <property>velocities/p-aero-rad_sec</property>
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <tableData>
                    -10	-0.4100
                     -5	-0.4057
                      0 -0.40160000
                      5 -0.40570000
                     10 -0.20000000
                     15 -0.08000000
                     20 -0.08000000
                     25 -0.20000000
                     30 -0.27000000
                     35 -0.22830000
                     40 -0.18630000
                     45 -0.11040000
                     50 -0.03610000
                     55 -0.08910000
            </tableData>
          </table>
       </product>
    </function>
    <function name="aero/coefficients/CLR">
    <description>CLR</description>
    <product>
          <property>aero/bi2vel</property>
          <property>velocities/r-aero-rad_sec</property>
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <tableData>
                     -5	-0.0522
                      0 0.00800000
                      5 0.05220000
                     10 0.08380000
                     15 0.07890000
                     20 0.23100000
                     25 0.23840000
                     30 0.32000000
                     35 0.32000000
                     40 0.25450000
                     45 0.07250000
                     50 -0.04340000
                     55 -0.58800000
            </tableData>
          </table>
       </product>
    </function>
    <function name="aero/coefficients/CLDA">
    <description>CLDA</description>
    <product>
          <property>fcs/left-aileron-pos-deg</property>
          <property>aero/cadc-control-effectivity-factor</property>
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <independentVar lookup="column">aero/beta-deg</independentVar>
            <tableData>
                               -20        -15        -10         -5          0          5         10         15         20 
                 0      0.00079000 0.00079000 0.00079000 0.00079000 0.00079000 0.00079000 0.00079000 0.00079000 0.00079000 
                 5      0.00079000 0.00079000 0.00079000 0.00079000 0.00079000 0.00079000 0.00079000 0.00079000 0.00079000 
                 10     0.00079000 0.00079000 0.00079000 0.00079000 0.00079000 0.00079000 0.00079000 0.00079000 0.00079000 
                 15     0.00062000 0.00066000 0.00071250 0.00077750 0.00080500 0.00077750 0.00071250 0.00066000 0.00062000 
                 20     0.00048250 0.00057500 0.00066000 0.00074750 0.00075500 0.00074750 0.00066000 0.00057500 0.00048250 
                 25     0.00031000 0.00046500 0.00053000 0.00060500 0.00064500 0.00060500 0.00053000 0.00046500 0.00031000 
                 30     0.00023500 0.00034750 0.00039000 0.00044000 0.00048500 0.00044000 0.00039000 0.00034750 0.00023000 
                 35     0.00016750 0.00022000 0.00021750 0.00021500 0.00023500 0.00021500 0.00021750 0.00022000 0.00016750 
                 40     0.00009250 0.00014250 0.00012250 0.00014000 0.00012000 0.00014000 0.00012250 0.00014250 0.00009250 
                 45     0.00017250 0.00013750 0.00011500 0.00011750 0.00014000 0.00011750 0.00011500 0.00013750 0.00017250 
                 50     0.00014500 0.00013750 0.00018250 0.00024250 0.00022000 0.00024250 0.00018250 0.00013750 0.00014500 
                 55     0.00017500 0.00021000 0.00027750 0.00033000 0.00035000 0.00033000 0.00027750 0.00021000 0.00017500 
            </tableData>
          </table>
       </product>
    </function>
        <function name="aero/coefficients/CLDasym">
            <description>Delta CL due to wing asymmetry</description>
            <product>
                <property>aero/wing-asymmetry</property>
                <property>aero/coefficients/ClSweepFactor</property>
                <value>0.076</value>
            </product>
        </function>

<!-- AFWAL-TR-80-3141 part III: p55; no effect from spoilers above 10degrees alpha -->
    <function name="aero/coefficients/CLDSp">
    <description>Delta CL due differential spoiler deflection</description>
    <product>
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <independentVar lookup="column">fcs/wing-sweep-cmd</independentVar>
            <tableData>
                      0.28         0.4          0.911
                -55	  0.00000000   0.0000000   0.0000000
                -15	  0.00179000   0.0017100   0.0002864
                  0	  0.00129000   0.0012100   0.0002864
                 10	  0.00119000   0.0011100   0.0001864
                 15	  0.00000000   0.0000000   0.0000000
            </tableData>
          </table>
       </product>
    </function>
    <function name="aero/coefficients/CLDSpR">
    <description>Delta CL due differential right spoiler deflection</description>
       <product>
          <property>aero/coefficients/CLDSp</property>
          <table>
            <independentVar lookup="row">fcs/spoiler-right-pos-deg</independentVar>
            <tableData>
0 0
3 1
55 55
            </tableData>
          </table>
       </product>
    </function>
    <function name="aero/coefficients/CLDSpL">
    <description>Delta CL due differential left spoiler deflection</description>
    <product>
                <property>aero/coefficients/CLDSp</property>
          <table>
            <independentVar lookup="row">fcs/spoiler-left-pos-deg</independentVar>
            <tableData>
0 0
3 -1
55 -55
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/coefficients/CLDR">
    <description>CLDR</description>
    <product>
          <property>fcs/rudder-pos-deg</property>
          <property>aero/cadc-control-effectivity-factor</property>
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <independentVar lookup="column">aero/beta-deg</independentVar>
            <tableData>
                               -20        -15        -10         -5          0          5         10         15         20 
                 0      0.00009600 0.00010400 0.00011200 0.00011200 0.00011200 0.00011200 0.00011200 0.00010400 0.00009600 
                 5      0.00009000 0.00009700 0.00010400 0.00010400 0.00010800 0.00010600 0.00010400 0.00009700 0.00009000 
                 10     0.00008400 0.00009000 0.00009600 0.00009900 0.00010200 0.00009900 0.00009600 0.00009000 0.00008400 
                 15     0.00007400 0.00008000 0.00008600 0.00009000 0.00009400 0.00009000 0.00008600 0.00008000 0.00007400 
                 20     0.00006600 0.00007100 0.00007600 0.00008000 0.00008400 0.00008000 0.00007600 0.00007100 0.00006600 
                 25     0.00005600 0.00006100 0.00006600 0.00007000 0.00007400 0.00007000 0.00006600 0.00006100 0.00005600 
                 30     0.00004500 0.00005000 0.00005400 0.00005800 0.00006200 0.00005800 0.00005400 0.00005000 0.00004600 
                 35     0.00003200 0.00003600 0.00004000 0.00004400 0.00004800 0.00004400 0.00004000 0.00003600 0.00003200 
                 40     0.00002000 0.00002200 0.00002400 0.00002700 0.00003000 0.00002700 0.00002400 0.00002200 0.00002000 
                 45     0.00000600 0.00000700 0.00000800 0.00000900 0.00001000 0.00000900 0.00000800 0.00000700 0.00000600 
                 50     0.00000000 0.00000000 0.00000000 0.00000000 0.00000000 0.00000000 0.00000000 0.00000000 0.00000000 
                 55     0.00000000 0.00000000 0.00000000 0.00000000 0.00000000 0.00000000 0.00000000 0.00000000 0.00000000 
            </tableData>
          </table>
       </product>
    </function>
     <function name="aero/coefficients/CLDasym">
         <description>Delta CL due to wing asymmetry</description>
         <product>
             <property>aero/wing-asymmetry</property>
             <value>0.00912</value>
         </product>
     </function>

     <function name="aero/coefficients/CL">
    <sum>
          <property>aero/coefficients/CLBAS</property>
          <property>aero/coefficients/CLP</property>
          <property>aero/coefficients/CLR</property>
          <property>aero/coefficients/CLDA</property>
          <property>aero/coefficients/CLDR</property>
          <property>aero/coefficients/CLDSpL</property>
          <property>aero/coefficients/CLDSpR</property>
                <property>aero/coefficients/CLDasym</property>
       </sum>
    </function>

    <function name="aero/coefficients/CMBAS">
    <description>CMBAS</description>
    <product>
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <independentVar lookup="column">aero/beta-deg</independentVar>
            <tableData>
                          -20     -15     -10    -5       0        5           10          15          20
                -15	 0.14956560	0.10330000	0.07025313	0.05042500	0.04381563	0.05042500	0.07025313	0.10330000	0.14956560
                -10	 0.04367188	0.02247500	0.00733438	0.00175000	0.00477813	0.00175000	0.00733438	0.02247500	0.04367188
                 -5	 0.00000000	0.00000000	0.00000000	0.00000000	0.00000000	0.00000000	0.00000000	0.00000000	0.00000000
                  0	 0.06052187	0.06540000	0.06888437	0.07097500	0.07167180	0.07097500	0.06888437	0.06540000	0.06052187
                  5	 0.02583125	0.03173750	0.03595625	0.03848750	0.03933125	0.03848750	0.03595625	0.03173750	0.02583125
                 10	-0.04367188	-0.02247500	-0.00733438	0.00175000	0.00477813	0.00175000	-0.00733438	-0.02247500	-0.04367188
                 15	-0.14956560	-0.10330000	-0.07025313	-0.05042500	-0.04381563	-0.05042500	-0.07025313	-0.10330000	-0.14956560
                 20	-0.17724690	-0.12441880	-0.08668438	-0.06404375	-0.05649687	-0.06404375	-0.08668438	-0.12441880	-0.17724690
                 25	-0.22480940	-0.18799370	-0.16169690	-0.14591870	-0.14065940	-0.14591870	-0.16169690	-0.18799370	-0.22480940
                 30	-0.23872500	-0.23216250	-0.22747500	-0.22466250	-0.22372500	-0.22466250	-0.22747500	-0.23216250	-0.23872500
                 35	-0.30000000	-0.30000000	-0.30000000	-0.30000000	-0.30000000	-0.30000000	-0.30000000	-0.30000000	-0.30000000
                 40	-0.34905310	-0.37213130	-0.38861560	-0.39850630	-0.40180310	-0.39850630	-0.38861560	-0.37213130	-0.34905310
                 45	-0.42481870	-0.44612500	-0.46134380	-0.47047500	-0.47351880	-0.47047500	-0.46134380	-0.44612500	-0.42481870
                 50	-0.48083130	-0.51692500	-0.54270630	-0.55817500	-0.56333130	-0.55817500	-0.54270630	-0.51692500	-0.48083130
                 55	-0.54004060	-0.58320000	-0.61402810	-0.63252500	-0.63869060	-0.63252500	-0.61402810	-0.58320000	-0.54004060
            </tableData>
          </table>
       </product>
    </function>

     <function name="aero/coefficients/CMDS1">
         <description>CMDS1</description>
         <product>
             <property>aero/cadc-control-effectivity-factor</property>
             <table>
                 <independentVar lookup="row">aero/alpha-deg</independentVar>
                 <tableData>
                     -55  -0.0120000
                     -50  -0.0145000
                     -45  -0.0145000
                     -40  -0.0145000
                     -35  -0.0145000
                     -30  -0.0160000
                     -25  -0.0160000
                     -20  -0.0160000
                     -15  -0.0155000
                     -10  -0.0140000
                     -5  -0.0115000
                     0 -0.00900000
                     5 -0.01150000
                     10 -0.01400000
                     15 -0.01550000
                     20 -0.01600000
                     25 -0.01600000
                     30 -0.01600000
                     35 -0.01450000
                     40 -0.01450000
                     45 -0.01450000
                     50 -0.01450000
                     55 -0.01200000
                 </tableData>
             </table>
         </product>
     </function>

     <function name="aero/coefficients/CMDS2">
         <description>CMDS2</description>
         <product>
             <!-- stabilizer-1p will be 1 or -10 (-10 when applicable)
           the original equation was -10*CMDS1 +(stab-deg + 10) CMDS2
           -->
             <property>aero/cadc-control-effectivity-factor</property>
             <table>
                 <independentVar lookup="row">aero/alpha-deg</independentVar>
                 <tableData>
                     -55  0.00000000
                     -50  0.00050000
                     -45  0.00600000
                     -40  0.00400000
                     -35 -0.00100000
                     -30 -0.00750000
                     -25 -0.01330000
                     -20 -0.01700000
                     -15 -0.01900000
                     -10 -0.01900000
                      -5 -0.01850000
                       0 -0.01950000
                       5 -0.01850000
                      10 -0.01900000
                      15 -0.01900000
                      20 -0.01700000
                      25 -0.01330000
                      30 -0.00750000
                      35 -0.00100000
                      40  0.00400000
                      45  0.00600000
                      50  0.00050000
                      55  0.00000000
                 </tableData>
             </table>
         </product>
     </function>

     <function name="aero/coefficients/DCMDS1">
         <description>DCMDS1</description>
         <product>
             <property>fcs/stabilizer-1p-factor</property>
             <property>aero/coefficients/CMDS1</property>
             <property>fcs/elevator-pos-deg</property>
         </product>
     </function>

     <function name="aero/coefficients/DCMDS2">
         <description>DCMDS2</description>
         <product>
             <property>fcs/stabilizer-2p-factor</property>
             <!-- stabilizer-1p will be 1 or -10 (-10 when applicable)
           the original equation was -10*CMDS1 +(stab-deg + 10) CMDS2
           -->
             <sum>
                 <product>
                     <value>-10</value>
                     <property>aero/coefficients/CMDS1</property>
                 </product>
                 <product>
                     <sum>
                         <value>10</value>
                         <property>fcs/elevator-pos-deg</property>
                     </sum>
                     <property>aero/coefficients/CMDS2</property>
                 </product>
             </sum>
         </product>
     </function>

     <function name="aero/coefficients/DCMAIM">
    <description>Pitch moment increment due to aim missiles</description>
    <product>
          <property>fcs/aim-fitted</property>
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <independentVar lookup="column">aero/alpha-deg</independentVar>
            <tableData>
                            -6     	-5     	-4     	-3     	-2     	-1     	0     	1     	2     	3     	4     	5     	6     	7     	8     	9     	10     	20     
                    0.80	-0.0150	-0.0150	-0.0150	-0.0100	-0.0050	-0.0030	-0.0020	-0.0010	0.0000	0.0020	0.0030	0.0050	0.0100	0.0100	0.0050	0.0030	0.0000	0.0000
                    0.85	-0.0330	-0.0310	-0.0300	-0.0220	-0.0100	-0.0040	-0.0030	-0.0020	0.0000	0.0030	0.0060	0.0070	0.0080	0.0100	0.0100	0.0060	0.0040	0.0040
                    0.90	-0.0320	-0.0310	-0.0300	-0.0280	-0.0200	-0.0060	-0.0020	0.0000	0.0020	0.0040	0.0070	0.0070	0.0060	0.0160	0.0120	0.0120	0.0120	0.0120
            </tableData>
          </table>
       </product>
    </function>
    <function name="aero/coefficients/DCMB0">
    <description>DCMB0</description>
    <product>
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <tableData>
                      0 -0.05500000
                      5 -0.05500000
                     10 -0.05500000
                     15 -0.05500000
                     20 -0.05500000
                     25 -0.05500000
                     30 -0.05500000
                     35 -0.05500000
                     40 -0.05500000
                     45 -0.05500000
                     50 -0.05500000
                     55 -0.05500000
            </tableData>
          </table>
       </product>
    </function>
    <function name="aero/coefficients/CMQ">
    <description>CMQ</description>
    <product>
          <property>aero/cbarq-2vo</property>
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <tableData>
                -20	-14.129
                -5	-15.424
                0	-15.424
                5	-14.129
                10	-17.967
                15	-22.807
                20	-21.078
                25	-19.629
                30	-15.185
                35	-1.886
                40	-7.707
                45	-5.479
                50	-13.113
                55	-10.298
            </tableData>
          </table>
       </product>
    </function>
    <function name="aero/coefficients/CMBRK">
       <description>CM increment due speedbrakes</description>
         <product>
           <property>fcs/speedbrake-pos-norm</property>
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <tableData>
               -14   0
                -5   0.0219
                -3	 0
                 0	 0.0003
                 5	 0.0000
                 8	-0.0180
                12	-0.0220
                14	 0
            </tableData>
          </table>
         </product>
    </function>
    <function name="aero/coefficients/CMUC">
    <description>CM increment due to gear</description>
    <product>
          <property>gear/gear-pos-norm</property>
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <tableData>
                -10	 0.00000
                -4	 0.00000
                 0	-0.01750
                        5	-0.01000
                        10	-0.00250
                        20	 0.00000
            </tableData>
          </table>
       </product>
    </function>
    <function name="aero/coefficients/CMDSp">
    <description>CM increment due to spoiler deflection</description>
    <product>
          <sum>
            <property>fcs/spoiler-left-pos</property>
            <property>fcs/spoiler-right-pos</property>
          </sum>
            <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <tableData>
              -55	 0.0
              -50	 0.0
              -45	 0.0
              -40	 0.0
              -35	 0.0
              -30	 0.0
              -15	 0.0
              0	     -0.000001636 <!-- based on 0.1 of 0aoa CMDS1 at 55deg deflection-->
              10	 0.0
            </tableData>
          </table>
       </product>
    </function>
    <function name="aero/coefficients/CMDFM">
    <description>CM increment due to flap mean position</description>
    <product>
          <table>
            <independentVar lookup="row">fcs/flap-pos-deg</independentVar>
            <independentVar lookup="column">aero/alpha-deg</independentVar>
            <tableData>
	                       0	       5	     10 	      15	     20	         60
                 0	 0.00000	 0.00000	0.00000 	 0.00000	0.00000 	0.00000
                 5   0.01320	 0.00396	0.00589 	 0.00762	0.00798 	0.00342
                15   0.01520	 0.00456	0.00649 	 0.01045	0.00798 	0.00342
                        35	0.01696	0.01523	0.01355	0.01092	0.01148	0.01148
            </tableData>
          </table>
       </product>
    </function>
    <function name="aero/coefficients/CMDAFM">
    <description>CM increment due to flap mean position</description>
    <product>
          <table>
            <independentVar lookup="row">fcs/aux-flap-pos-deg</independentVar>
            <independentVar lookup="column">aero/alpha-deg</independentVar>
            <tableData>
	                       0	       5	     10 	      15	     20	         60
                 0	 0.00000	0.00000 	0.00000 	0.00000 	0.00000 	0.00000
                         5	0.00594	0.00178	0.00265	0.00343	0.00359	0.00154
                        15	0.00684	0.00205	0.00292	0.00470	0.00359	0.00154
                        35	0.00763	0.00685	0.00610	0.00491	0.00517	0.00517
            </tableData>
          </table>
       </product>
    </function>
     <function name="aero/coefficients/CM">
         <sum>
             <property>aero/coefficients/CMBAS</property>
             <property>aero/coefficients/DCMB0</property>
             <property>aero/coefficients/CMQ</property>
             <property>aero/coefficients/DCMDS1</property>
             <property>aero/coefficients/DCMDS2</property>
             <property>aero/coefficients/CMUC</property>
             <property>aero/coefficients/CMDFM</property>
             <property>aero/coefficients/CMDAFM</property>
             <property>aero/coefficients/CMBRK</property>
             <!--<property>aero/coefficients/CMDSLM</property> Slats are included in flaps (DFM) -->
             <property>aero/coefficients/CMDSp</property>
         </sum>
     </function>

    <function name="aero/coefficients/CNBAS">
    <description>CNBAS</description>
    <product>
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <independentVar lookup="column">aero/beta-deg</independentVar>
            <tableData>
                               -20        -15        -10         -5          0          5         10         15         20 
                 -10    -0.03900000 -0.03000000 -0.02150000 -0.01000000 0.00000000 0.01000000 0.02150000 0.03000000 0.03900000 
                 -5     -0.03900000 -0.03000000 -0.02150000 -0.01000000 0.00000000 0.01000000 0.02150000 0.03000000 0.03900000 
                 0      -0.04000000 -0.03050000 -0.02150000 -0.01000000 0.00000000 0.01000000 0.02150000 0.03050000 0.04000000 
                 5      -0.03900000 -0.03000000 -0.02150000 -0.01000000 0.00000000 0.01000000 0.02150000 0.03000000 0.03900000 
                 10     -0.03600000 -0.02570000 -0.01900000 -0.00950000 0.00000000 0.00950000 0.01900000 0.02750000 0.03600000 
                 15     -0.00850000 -0.00750000 -0.00600000 -0.00300000 0.00000000 0.00300000 0.00600000 0.00750000 0.00850000 
                 20     0.01000000 0.00700000 0.00400000 0.00200000 0.00000000 -0.00200000 -0.00400000 -0.00700000 -0.01000000 
                 25     0.02550000 0.01700000 0.00900000 0.00450000 0.00000000 -0.00450000 -0.00900000 -0.01700000 -0.02550000 
                 30     0.03800000 0.02800000 0.01800000 0.01100000 0.00000000 -0.01100000 -0.01800000 -0.02800000 -0.03800000 
                 35     0.04050000 0.03150000 0.02300000 0.01450000 0.00000000 -0.01450000 -0.02300000 -0.03150000 -0.04050000 
                 40     0.04500000 0.02950000 0.01900000 0.00850000 0.00000000 -0.00850000 -0.01900000 -0.02950000 -0.04050000 
                 45     0.04150000 0.03150000 0.02150000 0.01300000 0.00000000 -0.01300000 -0.02150000 -0.03150000 -0.04150000 
                 50     0.03600000 0.02800000 0.02050000 0.01450000 0.00000000 -0.01450000 -0.02050000 -0.02800000 -0.03600000 
                 55     0.02600000 0.02200000 0.01750000 0.01450000 0.00000000 -0.01450000 -0.01750000 -0.02200000 -0.02600000 
            </tableData>
          </table>
       </product>
    </function>
        <function name="aero/coefficients/CNDasym">
            <description>Delta CN due to wing asymmetry</description>
            <product>
                <property>aero/wing-asymmetry</property>
                <value>0.01293512</value>
            </product>
        </function>
    <function name="aero/coefficients/DCNDS">
    <description>DCNDS</description>
    <product>
          <property>fcs/elevator-pos-deg</property>
          <property>aero/cadc-control-effectivity-factor</property>
          <property>aero/cn-sin-82beta</property>
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <tableData>
                     -5 0.00011700
                      0 0.00011700
                      5 0.00011700
                     10 0.00015000
                     15 0.00018300
                     20 0.00021700
                     25 0.00025000
                     30 0.00026700
                     35 0.00013300
                     40 0.00008300
                     45 0.00005000
                     50 0.00005000
                     55 0.00005000
            </tableData>
          </table>
       </product>
    </function>
    <function name="aero/coefficients/CNP">
            <description>CNP, AFWAL, Revised TM-81833 Fig37.</description>
    <product>
          <property>aero/bi2vel</property>
          <property>velocities/p-aero-rad_sec</property>
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <tableData>
                    -10 -0.09470000
                     -5 -0.09470000
                      0 -0.03330000
                      5 -0.09470000
                     10 -0.10680000
                     15 -0.11890000
                     20 -0.13100000
                     25 -0.08000000
                     30 -0.01160000
                     35 0.14210000
                     40 0.10070000
                     45 -0.02980000
                     50 -0.09580000
                     55 -0.01340000
            </tableData>
          </table>
       </product>
    </function>
    <function name="aero/coefficients/CNR">
    <description>CNR</description>
    <product>
          <property>aero/bi2vel</property>
          <property>velocities/r-aero-rad_sec</property>
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <tableData>
                     -5 -0.11540000
                      0 -0.11540000
                      5 -0.12560000
                     10 -0.13800000
                     15 -0.20480000
                     20 -0.18970000
                     25 -0.19180000
                     30 -0.19720000
                     35 -0.29110000
                     40 -0.14490000
                     45 -0.04580000
                     50 0.04550000
                     55 -0.04410000
            </tableData>
          </table>
       </product>
    </function>
    <function name="aero/coefficients/CNDA">
    <description>CNDA</description>
    <product>
          <property>fcs/left-aileron-pos-deg</property>
          <property>aero/cadc-control-effectivity-factor</property>
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <tableData>
                      0 0.00025000
                      5 0.00025000
                     10 0.00017500
                     15 0.00007500
                     20 -0.00005000
                     25 -0.00022500
                     30 -0.00037500
                     35 -0.00052500
                     40 -0.00070000
                     45 -0.00082500
                     50 -0.00085000
                     55 -0.00092500
            </tableData>
          </table>
       </product>
    </function>
    <function name="aero/coefficients/CNDSP">

    <description>Yaw momement increment due to spoiler deflection</description>
    <product>
          <sum>
            <property>fcs/spoiler-left-pos</property>
            <property>fcs/spoiler-right-pos</property>
          </sum>
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <tableData>
                      0 0.00000000
                      5 0.00000000
                     10 0.00000000
                     15 0.00000000
                     20 0.00000000
                     25 0.00000000
                     30 0.00000000
                     35 0.00000000
                     40 0.00000000
                     45 0.00000000
                     50 0.00000000
                     55 0.00000000
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/coefficients/CNDR">
    <description>CNDR</description>
    <product>
          <property>fcs/rudder-pos-deg</property>
          <property>aero/cadc-control-effectivity-factor</property>
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <independentVar lookup="column">aero/beta-deg</independentVar>
            <tableData>
                               -20        -15        -10         -5          0          5         10         15         20 
                -5      -0.00103000 -0.00115000 -0.00127000 -0.00142000 -0.00158000 -0.00142000 -0.00127000 -0.00115000 -0.00103000 
                 0      -0.00103000 -0.00115000 -0.00127000 -0.00142000 -0.00158000 -0.00142000 -0.00127000 -0.00115000 -0.00103000 
                 5      -0.00104000 -0.00118000 -0.00130000 -0.00140000 -0.00150000 -0.00140000 -0.00130000 -0.00118000 -0.00107000 
                 10     -0.00102000 -0.00114000 -0.00127000 -0.00135000 -0.00144000 -0.00135000 -0.00127000 -0.00114000 -0.00102000 
                 15     -0.00085000 -0.00102000 -0.00120000 -0.00130000 -0.00140000 -0.00130000 -0.00120000 -0.00102000 -0.00085000 
                 20     -0.00063000 -0.00085000 -0.00107000 -0.00120000 -0.00134000 -0.00120000 -0.00107000 -0.00085000 -0.00063000 
                 25     -0.00048000 -0.00066000 -0.00084000 -0.00098000 -0.00112000 -0.00098000 -0.00084000 -0.00066000 -0.00048000 
                 30     -0.00042000 -0.00054000 -0.00067000 -0.00072000 -0.00077000 -0.00072000 -0.00067000 -0.00054000 -0.00042000 
                 35     -0.00033000 -0.00035000 -0.00037000 -0.00044000 -0.00052000 -0.00044000 -0.00037000 -0.00035000 -0.00033000 
                 40     -0.00020000 -0.00020000 -0.00020000 -0.00024000 -0.00029000 -0.00024000 -0.00020000 -0.00020000 -0.00020000 
                 45     -0.00004000 -0.00004000 -0.00004000 -0.00007000 -0.00011000 -0.00007000 -0.00004000 -0.00004000 -0.00004000 
                 50     0.00000000 0.00000000 0.00000000 0.00000000 0.00000000 0.00000000 0.00000000 0.00000000 0.00000000 
                 55     0.00000000 0.00000000 0.00000000 0.00000000 0.00000000 0.00000000 0.00000000 0.00000000 0.00000000 
            </tableData>
          </table>
       </product>
    </function>
    <function name="aero/coefficients/CN">
    <sum>
          <property>aero/coefficients/CNBAS</property>
          <property>aero/coefficients/DCNDS</property>
          <property>aero/coefficients/CNP</property>
          <property>aero/coefficients/CNR</property>
          <property>aero/coefficients/CNDA</property>
          <property>aero/coefficients/CNDR</property>
                <property>aero/coefficients/CNDasym</property>
       </sum>
    </function>
  <axis name="LIFT">
    <function name="aero/force/LIFT">
    <description>LIFT Force</description>
    <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>aero/coefficients/Cl</property>
          <property>aero/coefficients/Cmach</property>
          <property>aero/coefficients/ClSweepFactor</property>
       </product>
    </function>
  </axis>
  <axis name="DRAG">
    <function name="aero/force/DRAG">
    <description>DRAG Force</description>
    <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>aero/coefficients/Cd</property>
          <property>aero/coefficients/ClSweepFactor</property>
    </product>
    </function>
  </axis>
  <axis name="SIDE">
    <function name="aero/force/SIDE">
    <description>SIDE Force</description>
    <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>aero/coefficients/Cy</property>
          <property>aero/coefficients/Cmach</property>
       </product>
    </function>
  </axis>
  <axis name="ROLL">
    <function name="aero/force/ROLL">
    <description>ROLL Moment</description>
    <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/bw-ft</property>
          <property>aero/coefficients/CL</property>
          <property>aero/coefficients/Cmach</property>
       </product>
    </function>
  </axis>
  <axis name="PITCH">
    <function name="aero/force/PITCH">
    <description>PITCH Moment</description>
    <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/cbarw-ft</property>
          <property>aero/coefficients/CM</property>
          <property>aero/coefficients/Cmach</property>
       </product>
    </function>
  </axis>
  <axis name="YAW">
    <function name="aero/force/YAW">
    <description>YAW Moment</description>
    <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/bw-ft</property>
          <property>aero/coefficients/CN</property>
          <property>aero/coefficients/Cmach</property>
    </product>
    </function>
  </axis>

</aerodynamics>

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        <force name="catapult" frame="BODY">
      <location unit="IN">
                <x> 667 </x>
                <y>   0 </y>
                <z>   0 </z>
      </location>
      <direction>
                <x>   1 </x>
                <y>   0 </y>
                <z>   0 </z>
      </direction>
    </force>
    
    <force name="holdback" frame="BODY">
      <location unit="IN">
                <x> 667 </x>
                <y>   0 </y>
                <z>   0 </z>
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        <x>   -1.0 </x>
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        <z>    0.0 </z>
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    <force name="hook" frame="BODY">
      <location unit="IN">
                <x>  300 </x>
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        <x>  -0.9995 </x>
        <y>   0.0    </y>
        <z>   0.01 </z>
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                    <x> 667 </x>
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                    <z> -10 </z>
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        <x>  -0.9995 </x>
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        <z>   0.01 </z>
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            <location unit="IN">
                    <x> 667 </x>
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        <x>  -0.9995 </x>
        <y>   0.0    </y>
        <z>   0.01 </z>
      </direction>
        </force>


  </external_reactions>


</fdm_config>
