<?xml version="1.0"?>
<?xml-stylesheet href="http://jsbsim.sourceforge.net/JSBSim.xsl" type="text/xsl"?>
<fdm_config name="Lockheed1049h" version="2.0" release="ALPHA"
            xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
            xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

  <fileheader>
    <author> Gary R. Neely </author>
    <filecreationdate> 15 December 2008 </filecreationdate>
    <version> 0.01 </version>
    <description> Lockheed1049h </description>

    <note>Super Constellation 1049-54 (first version).</note>
    <note>origin of metrics at nose tip.</note>
    <note>VRP at nose tip.</note>

    <limitation>gear height determined by 3D model, supposed at scale.</limitation>
    <limitation>emulation of fuel cross feed, tanks run out of fuel above X 3 speed-up.</limitation>
    <limitation>autopilot heading hold may lock to the right with roll.</limitation>

    <!--
        File:     Lockheed1049h.xml
        Author:   Aero-Matic v 0.71

Based heavily on FDM created for Lockheed1049.xml, author unknown
Details changed based on requirements for 1049h model.
Most credits should go to previous FDM author(s). -GRN

Inputs:
name:          Lockheed1049h
type:          multi-engine prop transport
max weight:    120000.0 lb
wing span:     123.0 ft
length:        113.6 ft
wing area:     1650 sq-ft
gear type:     tricycle
retractable?:  yes
# engines:     4
engine type:   piston
engine layout: wings
yaw damper?    no

Outputs:
wing loading:  72.73 lb/sq-ft
CL-alpha:      4.9 per radian
CL-0:          0.24
CL-max:        1.4
CD-0:          0.025
K:             0.039
    -->

    <reference
        refID="FAA certificate, 6a5"
        author="FAA"
        title="http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgMakeModel.nsf/MainFrame?OpenFrameSet"
        date="14 May 1952"/>
    <documentation>
      MAC : 176 in., leading edge at station 628.8 in.

      CG range : 21-32 % at takeoff.

      Main surfaces (booster on)   : Elevator  40 deg up,     20 deg down.
      Aileron   25 deg up,     10 deg down.
      Rudder    30 deg right,  30 deg left.

      Tabs (main surfaces neutral) : Elevator  22 deg up,     22 deg down.
      Aileron   12 deg up,     12 deg down.
      Rudder    25 deg right,  25 deg left.

      Flaps : 41 deg.

      Tanks 2 and 3 (inboard) : 790 gal each, 9480 lb.
      1 and 4 (middle) : 1555 gal each, 18660 lb.
      2a and 3a (outboard) : 565 gal each, 6780 lb.
      5 (center section) : 730 gal, 4380 lb.

      A total of 6550 US gal : note that is 1 US gal = 6 lb !
    </documentation>
    <documentation>
      - http://www.hq.nasa.gov/office/pao/History/SP-468/app-a2.htm :

      Drag CD0 (L-1049G) : 0.0211.
    </documentation>
    <documentation>
      - http://naca.larc.nasa.gov/reports/1932/naca-tn-419/ :
      Wind-tunnel tests of the Fowler variable-area wing,
      Fred E. Weick and Robert C. Platt, May 1932.
    </documentation>
    <documentation>
      - http://www.eflightmanual.com/ :
      Lockheed flight manual.
    </documentation>
  </fileheader>

  <metrics>
    <documentation>
      Aero reference point is from nose tip origin (arbitrary origin).

      VRP, where the FDM computes the movement, at the nose tip (0,0,0),

      Eye point location, so that pilot is at 195 - 110.2 = 84.8 in. from nose tip.

      Both VRP and Eye location entries in the same frame than CG and aero reference point (same unit).

      Htailarm : distance from CG to horizontal tail tip.
      Vtailarm : distance from CG to vertical tail tip.

      Wing incidence reduces roll speed.
    </documentation>
    <wingarea unit="FT2"> 1650 </wingarea>
    <wingspan unit="FT"> 123 </wingspan>
    <chord unit="FT"> 14.67 </chord>                                               <!-- aeromatic 13.41 -->
    <htailarea unit="FT2"> 436.58 </htailarea>                                     <!-- aeromatic 264.00 -->
    <htailarm unit="FT"> 25 </htailarm>                                            <!-- aeromatic 56.80 -->
    <vtailarea unit="FT2"> 403.2 </vtailarea>                                      <!-- aeromatic 297.00 -->
    <vtailarm unit="FT"> 16.8 </vtailarm>                                          <!-- added (turbulence) -->
    <wing_incidence unit="DEG"> 3.9 </wing_incidence>                              <!-- aeromatic none (0.0) -->
    <!-- AC_LV        56.80                               unit ? -->
    <location name="AERORP" unit="IN">
      <x> 681.6 </x>
      <y> 0 </y>
      <z> 0 </z>
    </location>
    <location name="EYEPOINT" unit="IN">
      <x> 84.8 </x>
      <y> -24 </y>
      <z> 65 </z>
    </location>
    <location name="VRP" unit="IN">
      <x> 0 </x>
      <y> 0 </y>
      <z> 0 </z>
    </location>
  </metrics>

  <mass_balance>
    <documentation>
      CG is from nose tip origin (arbitrary origin).
    </documentation>
    <ixx unit="SLUG*FT2"> 2.16504e+06 </ixx>
    <iyy unit="SLUG*FT2"> 2.20927e+06 </iyy>
    <izz unit="SLUG*FT2"> 4.32038e+06 </izz>
    <ixy unit="SLUG*FT2"> 0 </ixy>
    <ixz unit="SLUG*FT2"> 0 </ixz>
    <iyz unit="SLUG*FT2"> 0 </iyz>
    <emptywt unit="LBS"> 80706 </emptywt>
    <location name="CG" unit="IN">
      <x> 681.6 </x>
      <y> 0 </y>
      <z> -34.1 </z>
    </location>
    <pointmass name="Pilot">
      <weight unit="LBS">180</weight>
      <location unit="IN">
	<x>190</x>
	<y>-40</y>
	<z>0</z>
      </location>
    </pointmass>
    <pointmass name="Copilot">
      <weight unit="LBS">180</weight>
      <location unit="IN">
	<x>190</x>
	<y>40</y>
	<z>0</z>
      </location>
    </pointmass>
    <pointmass name="Flight Engineer">
      <weight unit="LBS">180</weight>
      <location unit="IN">
	<x>226</x>
	<y>40</y>
	<z>0</z>
      </location>
    </pointmass>
    <pointmass name="Main Cabin A">
      <weight unit="LBS">0</weight>
      <location unit="IN">
	<x>300</x>
	<y>0</y>
	<z>0</z>
      </location>
    </pointmass>
    <pointmass name="Main Cabin B">
      <weight unit="LBS">0</weight>
      <location unit="IN">
	<x>392</x>
	<y>0</y>
	<z>0</z>
      </location>
    </pointmass>
    <pointmass name="Main Cabin C">
      <weight unit="LBS">0</weight>
      <location unit="IN">
	<x>477</x>
	<y>0</y>
	<z>0</z>
      </location>
    </pointmass>
    <pointmass name="Main Cabin D">
      <weight unit="LBS">0</weight>
      <location unit="IN">
	<x>546</x>
	<y>0</y>
	<z>0</z>
      </location>
    </pointmass>
    <pointmass name="Main Cabin E">
      <weight unit="LBS">0</weight>
      <location unit="IN">
	<x>620</x>
	<y>0</y>
	<z>0</z>
      </location>
    </pointmass>
    <pointmass name="Main Cabin F">
      <weight unit="LBS">0</weight>
      <location unit="IN">
	<x>694</x>
	<y>0</y>
	<z>0</z>
      </location>
    </pointmass>
    <pointmass name="Main Cabin G">
      <weight unit="LBS">0</weight>
      <location unit="IN">
	<x>842</x>
	<y>0</y>
	<z>0</z>
      </location>
    </pointmass>
    <pointmass name="Main Cabin H">
      <weight unit="LBS">0</weight>
      <location unit="IN">
	<x>842</x>
	<y>0</y>
	<z>0</z>
      </location>
    </pointmass>
    <pointmass name="Main Cabin I">
      <weight unit="LBS">0</weight>
      <location unit="IN">
	<x>916</x>
	<y>0</y>
	<z>0</z>
      </location>
    </pointmass>
    <pointmass name="Main Cabin J">
      <weight unit="LBS">0</weight>
      <location unit="IN">
	<x>989</x>
	<y>0</y>
	<z>0</z>
      </location>
    </pointmass>
    <pointmass name="Main Cabin K">
      <weight unit="LBS">0</weight>
      <location unit="IN">
	<x>1089</x>
	<y>0</y>
	<z>0</z>
      </location>
    </pointmass>
    <pointmass name="Main Cabin L">
      <weight unit="LBS">0</weight>
      <location unit="IN">
	<x>1198</x>
	<y>0</y>
	<z>0</z>
      </location>
    </pointmass>
    <pointmass name="Lower Cargo Hold A">
      <weight unit="LBS">0</weight>
      <location unit="IN">
	<x>402</x>
	<y>0</y>
	<z>0</z>
      </location>
    </pointmass>
    <pointmass name="Lower Cargo Hold B">
      <weight unit="LBS">0</weight>
      <location unit="IN">
	<x>558</x>
	<y>0</y>
	<z>0</z>
      </location>
    </pointmass>
    <pointmass name="Lower Cargo Hold C">
      <weight unit="LBS">0</weight>
      <location unit="IN">
	<x>821</x>
	<y>0</y>
	<z>0</z>
      </location>
    </pointmass>
    <pointmass name="Lower Cargo Hold D">
      <weight unit="LBS">0</weight>
      <location unit="IN">
	<x>1004</x>
	<y>0</y>
	<z>0</z>
      </location>
    </pointmass>
  </mass_balance>

  <ground_reactions>
    <documentation>
      - gear height determined by 3D model, supposed at scale.
      - additonal contact points for crash detection, when gear retracted.
    </documentation>
    <contact type="BOGEY" name="NOSE_LG">
      <location unit="IN">
        <x>150</x>
        <y>0</y>
        <z>-145</z> <!-- 149.7 -->
      </location>
      <static_friction> 0.95 </static_friction>
      <dynamic_friction> 0.6 </dynamic_friction>
      <rolling_friction> 0.02 </rolling_friction>
      <spring_coeff unit="LBS/FT"> 36000 </spring_coeff> <!-- 36000 -->
      <damping_coeff unit="LBS/FT/SEC"> 14000 </damping_coeff> <!-- 12000 -->
      <max_steer unit="DEG"> 70 </max_steer>
      <brake_group> NONE </brake_group>
      <retractable>1</retractable>
    </contact>
    <contact type="BOGEY" name="LEFT_MLG">
      <location unit="IN">
        <x> 710 </x> <!-- 685.2 -->
        <y>-187.8</y>
        <z>-131</z> <!-- 136.1 -->
      </location>
      <static_friction> 0.8 </static_friction>
      <dynamic_friction> 0.5 </dynamic_friction>
      <rolling_friction> 0.02 </rolling_friction>
      <spring_coeff unit="LBS/FT"> 140000 </spring_coeff> <!-- 120000 -->
      <damping_coeff unit="LBS/FT/SEC"> 30000 </damping_coeff> <!-- 24000 -->
      <max_steer unit="DEG"> 0.0 </max_steer>
      <brake_group> LEFT </brake_group>
      <retractable>1</retractable>
    </contact>
    <contact type="BOGEY" name="RIGHT_MLG">
      <location unit="IN">
        <x> 710 </x>
        <y>187.8</y>
        <z>-131</z> <!-- 136.1 -->
      </location>
      <static_friction> 0.8 </static_friction>
      <dynamic_friction> 0.5 </dynamic_friction>
      <rolling_friction> 0.02 </rolling_friction>
      <spring_coeff unit="LBS/FT"> 140000 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC"> 30000 </damping_coeff>
      <max_steer unit="DEG"> 0.0 </max_steer>
      <brake_group> RIGHT </brake_group>
      <retractable>1</retractable>
    </contact>
    <contact type="STRUCTURE" name="NOSE_TIP">
      <location unit="IN">
        <x> 0 </x>
        <y> 0 </y>
        <z> 0 </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"> 36000 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC"> 12000 </damping_coeff>
      <max_steer unit="DEG"> 0.0 </max_steer>
      <brake_group> NONE </brake_group>
      <retractable>0</retractable>
    </contact>
    <contact type="STRUCTURE" name="LEFT_TIP">
      <location unit="IN">
        <x>664</x>
        <y>-732.3</y>
        <z>66.9</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"> 120000 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC"> 24000 </damping_coeff>
      <max_steer unit="DEG"> 0.0 </max_steer>
      <brake_group> NONE </brake_group>
      <retractable>0</retractable>
    </contact>
    <contact type="STRUCTURE" name="RIGHT_TIP">
      <location unit="IN">
        <x>664</x>
        <y>732.3</y>
        <z>66.9</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"> 120000 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC"> 24000 </damping_coeff>
      <max_steer unit="DEG"> 0.0 </max_steer>
      <brake_group> NONE </brake_group>
      <retractable>0</retractable>
    </contact>
    <contact type="STRUCTURE" name="TAIL_TIP">
      <location unit="IN">
        <x>1397.4</x>
        <y>0</y>
        <z>76.8</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"> 120000 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC"> 24000 </damping_coeff>
      <max_steer unit="DEG"> 0.0 </max_steer>
      <brake_group> NONE </brake_group>
      <retractable>0</retractable>
    </contact>
  </ground_reactions>

  <propulsion>
    <engine file="WrightCyclone-972TC18DA3">
      <location unit="IN">
        <x> 681.6 </x>
        <y> -358 </y>
        <z> -40 </z>
      </location>
      <orient unit="DEG">
        <roll> 0.0 </roll>
        <pitch> 0 </pitch>
        <yaw> 0 </yaw>
      </orient>
      <feed>0</feed> <!-- Eng 1 fuel line buffer -->
      <thruster file="HamiltonStd43E60-6901A">
        <location unit="IN">
          <x> 681.6 </x>
          <y> -358 </y>
          <z> -40 </z>
        </location>
        <orient unit="DEG">
          <roll> 0.0 </roll>
          <pitch> 0.0 </pitch>
          <yaw> 0.0 </yaw>
        </orient>
      </thruster>
    </engine>
    <engine file="WrightCyclone-972TC18DA3">
      <location unit="IN">
        <x> 681.6 </x>
        <y> -168 </y>
        <z> -40 </z>
      </location>
      <orient unit="DEG">
        <roll> 0.0 </roll>
        <pitch> 0 </pitch>
        <yaw> 0 </yaw>
      </orient>
      <feed>1</feed> <!-- Eng 2 fuel line buffer -->
      <thruster file="HamiltonStd43E60-6901A">
        <location unit="IN">
          <x> 681.6 </x>
          <y> -168 </y>
          <z> -40 </z>
        </location>
        <orient unit="DEG">
          <roll> 0.0 </roll>
          <pitch> 0.0 </pitch>
          <yaw> 0.0 </yaw>
        </orient>
      </thruster>
    </engine>
    <engine file="WrightCyclone-972TC18DA3">
      <location unit="IN">
        <x> 681.6 </x>
        <y> 168 </y>
        <z> -40 </z>
      </location>
      <orient unit="DEG">
        <roll> 0.0 </roll>
        <pitch> 0 </pitch>
        <yaw> 0 </yaw>
      </orient>
      <feed>2</feed> <!-- Eng 3 fuel line buffer -->
      <thruster file="HamiltonStd43E60-6901A">
        <location unit="IN">
          <x> 681.6 </x>
          <y> 168 </y>
          <z> -40 </z>
        </location>
        <orient unit="DEG">
          <roll> 0.0 </roll>
          <pitch> 0.0 </pitch>
          <yaw> 0.0 </yaw>
        </orient>
      </thruster>
    </engine>
    <engine file="WrightCyclone-972TC18DA3">
      <location unit="IN">
        <x> 681.6 </x>
        <y> 358 </y>
        <z> -40 </z>
      </location>
      <orient unit="DEG">
        <roll> 0.0 </roll>
        <pitch> 0 </pitch>
        <yaw> 0 </yaw>
      </orient>
      <feed>3</feed> <!-- Eng 4 fuel line buffer -->
      <thruster file="HamiltonStd43E60-6901A">
        <location unit="IN">
          <x> 681.6 </x>
          <y> 358 </y>
          <z> -40 </z>
        </location>
        <orient unit="DEG">
          <roll> 0.0 </roll>
          <pitch> 0.0 </pitch>
          <yaw> 0.0 </yaw>
        </orient>
      </thruster>
    </engine>

    <documentation>

      Tank Indexes and corresponding tanks:
      [ 0,  1,  2,  3, 4, 5, 6, 7, 8,  9, 10, 11, 12]
      B1, B2, B3, B4, 1, 2, 3, 4, 5, 1A, 2A, 3A, 4A
      +------------+  +---------------------------+
      Line Buffers             True Tanks

      See Nasal/Lockheed1049h-fuel.nas for more information about the tank/fuel system.
      Do not set tank capacity/contents to 0 or JSBsim will freak under FG 1.9+.

    </documentation>

    <tank type="FUEL">    <!-- Eng 1 line buffer, index 0 --> 
      <location unit="IN">
        <x> 681.6 </x>
        <y> -280 </y>
        <z> -34.08 </z>
      </location>
      <capacity unit="LBS"> 12 </capacity>
      <contents unit="LBS"> 12 </contents>
    </tank>
    <tank type="FUEL">    <!-- Eng 2 line buffer, index 1 --> 
      <location unit="IN">
        <x> 681.6 </x>
        <y> -100 </y>
        <z> -50 </z>
      </location>
      <capacity unit="LBS"> 12 </capacity>
      <contents unit="LBS"> 12 </contents>
    </tank>
    <tank type="FUEL">    <!-- Eng 3 line buffer, index 2 --> 
      <location unit="IN">
        <x> 681.6 </x>
        <y> 100 </y>
        <z> -50 </z>
      </location>
      <capacity unit="LBS"> 12 </capacity>
      <contents unit="LBS"> 12 </contents>
    </tank>
    <tank type="FUEL">    <!-- Eng 4 line buffer, index 3 --> 
      <location unit="IN">
        <x> 681.6 </x>
        <y> 280 </y>
        <z> -34.08 </z>
      </location>
      <capacity unit="LBS"> 12 </capacity>
      <contents unit="LBS"> 12 </contents>
    </tank>

    <tank type="FUEL">    <!-- Tank 1, index 4 --> 
      <location unit="IN">
        <x> 689  </x>
        <y> -280 </y>
        <z> -34.08 </z>
      </location>
      <capacity unit="LBS"> 9330 </capacity>
      <contents unit="LBS"> 9330 </contents>
    </tank>
    <tank type="FUEL">    <!-- Tank 2, index 5 --> 
      <location unit="IN">
        <x> 692 </x>
        <y> -100 </y>
        <z> -50 </z>
      </location>
      <capacity unit="LBS"> 4740 </capacity>
      <contents unit="LBS"> 4740 </contents>
    </tank>
    <tank type="FUEL">    <!-- Tank 3, index 6 --> 
      <location unit="IN">
        <x> 692 </x>
        <y> 100 </y>
        <z> -50 </z>
      </location>
      <capacity unit="LBS"> 4740 </capacity>
      <contents unit="LBS"> 4740 </contents>
    </tank>
    <tank type="FUEL">    <!-- Tank 4, index 7 --> 
      <location unit="IN">
        <x> 689 </x>
        <y> 280 </y>
        <z> -34.08 </z>
      </location>
      <capacity unit="LBS"> 9330 </capacity>
      <contents unit="LBS"> 9330 </contents>
    </tank>

    <tank type="FUEL">    <!-- Tank 5, index 8 --> 
      <location unit="IN">
        <x> 694 </x>
        <y> 0 </y>
        <z> -90 </z>
      </location>
      <capacity unit="LBS"> 4380 </capacity>
      <contents unit="LBS"> 4380 </contents>
    </tank>

    <tank type="FUEL">    <!-- Tank 1A, index 9 (not used) --> 
      <location unit="IN">
        <x> 688 </x>
        <y> -740.7 </y>
        <z> -34.08 </z>
      </location>
      <capacity unit="LBS"> 6 </capacity> <!-- 3654 -->
      <contents unit="LBS"> 0 </contents>
    </tank>
    <tank type="FUEL">    <!-- Tank 2A, index 10 --> 
      <location unit="IN">
        <x> 687 </x>
        <y> -450 </y>
        <z> -34.08 </z>
      </location>
      <capacity unit="LBS"> 3390 </capacity>
      <contents unit="LBS"> 3390 </contents>
    </tank>
    <tank type="FUEL">    <!-- Tank 3A, index 11 --> 
      <location unit="IN">
        <x> 687 </x>
        <y> 450 </y>
        <z> -34.08 </z>
      </location>
      <capacity unit="LBS"> 3390 </capacity>
      <contents unit="LBS"> 3390 </contents>
    </tank>
    <tank type="FUEL">    <!-- Tank 4A, index 12 (not used) --> 
      <location unit="IN">
        <x> 688 </x>
        <y> 740.7 </y>
        <z> -34.08 </z>
      </location>
      <capacity unit="LBS"> 6 </capacity> <!-- 3654 -->
      <contents unit="LBS"> 0 </contents>
    </tank>
  </propulsion>

  <system file="pushback"/>
  <external_reactions>
    <force name="pushback" frame="BODY">
      <location unit="IN">
        <x>    150 </x>
        <y>    0.0 </y>
        <z>  -145.0 </z>
      </location>
      <direction>
        <x>1</x>
        <y>0</y>
        <z>0</z>
      </direction>
    </force>
  </external_reactions>

  <flight_control name="Lockheed1049-54">
    <channel name="Pitch">

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

      <aerosurface_scale name="Elevator Control">
        <input>fcs/pitch-trim-sum</input>
        <gain>0.01745</gain>
        <range>
          <documentation>
            replaced -0.35/0.35 by -6/16 deg real.
          </documentation>
          <min>-6</min>
          <max>16</max>
        </range>
        <output>fcs/elevator-pos-rad</output>
      </aerosurface_scale>
      <aerosurface_scale name="Elevator Position Normalizer">
        <input>fcs/pitch-trim-sum</input>
        <range>
          <min>-1</min>
          <max>1</max>
        </range>
        <output>fcs/elevator-pos-norm</output>
      </aerosurface_scale>

    </channel>
    <channel name="Roll">

      <summer name="Roll Trim Sum">
        <input>fcs/aileron-cmd-norm</input>
        <input>fcs/roll-trim-cmd-norm</input>
        <clipto>
          <min>-1</min>
          <max>1</max>
        </clipto>
      </summer>

      <aerosurface_scale name="Left Aileron Control">
        <input>fcs/roll-trim-sum</input>
        <gain>0.01745</gain>
        <range>
          <documentation>
            replaced -0.35/0.35 by -10/25 deg real.
          </documentation>
          <min>-10</min>
          <max>25</max>
        </range>
        <output>fcs/left-aileron-pos-rad</output>
      </aerosurface_scale>
      <aerosurface_scale name="Left Aileron Position Normalizer">
        <input>fcs/roll-trim-sum</input>
        <range>
          <min>-1</min>
          <max>1</max>
        </range>
        <output>fcs/left-aileron-pos-norm</output>
      </aerosurface_scale>

      <aerosurface_scale name="Right Aileron Control">
        <input>-fcs/roll-trim-sum</input>
        <gain>0.01745</gain>
        <range>
          <documentation>
            replaced -0.35/0.35 by -10/25 deg real.
          </documentation>
          <min>-10</min>
          <max>25</max>
        </range>
        <output>fcs/right-aileron-pos-rad</output>
      </aerosurface_scale>
      <aerosurface_scale name="Right Aileron Position Normalizer">
        <input>fcs/roll-trim-sum</input>
        <range>
          <min>-1</min>
          <max>1</max>
        </range>
        <output>fcs/right-aileron-pos-norm</output>
      </aerosurface_scale>

    </channel>
    <channel name="Yaw">

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

      <aerosurface_scale name="Rudder Control">
        <input>fcs/rudder-command-sum</input>
        <gain>0.01745</gain>
        <range>
          <documentation>
            replaced -0.35/0.35 by -30/30 deg real.
          </documentation>
          <min>-30</min>
          <max>30</max>
        </range>
        <output>fcs/rudder-pos-rad</output>
      </aerosurface_scale>
      <aerosurface_scale name="Rudder Position Normalizer">
        <input>fcs/rudder-command-sum</input>
        <range>
          <min>-1</min>
          <max>1</max>
        </range>
        <output>fcs/rudder-pos-norm</output>
      </aerosurface_scale>

    </channel>
    <channel name="Aeromechanical">

      <kinematic name="Flaps Control">
        <input>fcs/flap-cmd-norm</input>
        <traverse>
          <documentation>
            - replaced 30 deg by 41 deg real.
            - add the 10 deg detent, because of the initial translation (Fowler flap).
            - add the 35 deg detent, because 60 %, 66 %, 80 % and 100 %.
          </documentation>
          <setting>
            <position>0</position>
            <time>0</time>
          </setting>
          <setting>
            <position>10</position>
            <time>5</time>
          </setting>
          <setting>
            <position>27</position>
            <time>4</time>
          </setting>
          <setting>
            <position>35</position>
            <time>4</time>
          </setting>
          <setting>
            <position>41</position>
            <time>3</time>
          </setting>
        </traverse>
        <output>fcs/flap-pos-deg</output>
      </kinematic>
      <aerosurface_scale name="Flap Position Normalizer">
        <input>fcs/flap-pos-deg</input>
        <domain>
          <min>0</min>
          <max>41</max>
        </domain>
        <range>
          <min>0</min>
          <max>1</max>
        </range>
        <output>fcs/flap-pos-norm</output>
      </aerosurface_scale>

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

      <kinematic name="Speedbrake Control">
        <input>fcs/speedbrake-cmd-norm</input>
        <traverse>
          <setting>
            <position>0</position>
            <time>0</time>
          </setting>
          <setting>
            <position>1</position>
            <time>1</time>
          </setting>
        </traverse>
        <output>fcs/speedbrake-pos-norm</output>
      </kinematic>
    </channel>
  </flight_control>
  <aerodynamics>
    <documentation>
      created to smooth takeoff roll.
    </documentation>
    <function name="aero/function/kCLge">
      <description>Change_in_lift_due_to_ground_effect</description>
      <product>
        <table>
          <independentVar>aero/h_b-mac-ft</independentVar>
          <tableData>
            0.0000	1.2000	
            0.1000	1.1500	
            0.1500	1.0900	
            0.2000	1.0200	
            1.1000	1.0000	
          </tableData>
        </table>
      </product>
    </function>

    <axis name="DRAG">
      <documentation>
        added.
      </documentation>
      <function name="aero/coefficient/CDo">
        <description>Drag_at_zero_lift</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <value>0.0211</value>
        </product>
      </function>
      <documentation>
        - renamed from CDo.
        - substracted Cdo 0.0211.
      </documentation>
      <function name="aero/coefficient/CDalpha">
        <description>Drag_due_to_alpha</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar>aero/alpha-rad</independentVar>
            <tableData>
              -1.5700	1.4789	
              -0.2600	0.0289	
              0.0000	0.0039	
              0.2600	0.0289	
              1.5700	1.4789	
            </tableData>
          </table>
        </product>
      </function>
      <function name="aero/coefficient/CDi">
        <description>Induced_drag</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>aero/cl-squared</property>
          <value>0.0390</value>
        </product>
      </function>
      <function name="aero/coefficient/CDmach">
        <description>Drag_due_to_mach</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar>velocities/mach</independentVar>
            <tableData>
              0.0000	0.0000	
              0.7000	0.0000	
              1.1000	0.0230	
              1.8000	0.0150	
            </tableData>
          </table>
        </product>
      </function>
      <function name="aero/coefficient/CDflap">
        <description>Drag_due_to_flaps</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>fcs/flap-cmd-norm</property>
          <value>0.0350</value>
        </product>
      </function>
      <function name="aero/coefficient/CDgear">
        <description>Drag_due_to_gear</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>gear/gear-pos-norm</property>
          <value>0.0230</value>
        </product>
      </function>
      <documentation>
        0.0250 becomes 0.0 : disable speedbrake.
      </documentation>
      <function name="aero/coefficient/CDsb">
        <description>Drag_due_to_speedbrakes</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>fcs/speedbrake-pos-norm</property>
          <value>0.0</value>
        </product>
      </function>
      <function name="aero/coefficient/CDbeta">
        <description>Drag_due_to_sideslip</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar>aero/beta-rad</independentVar>
            <tableData>
              -1.5000	1.2300	
              -0.2600	0.0500	
              0.0000	0.0000	
              0.2600	0.0500	
              1.5700	1.2300	
            </tableData>
          </table>
        </product>
      </function>
      <function name="aero/coefficient/CDde">
        <description>Drag_due_to_Elevator_Deflection</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <abs><property>fcs/elevator-pos-norm</property></abs>
          <value>0.0350</value>
        </product>
      </function>
    </axis>

    <axis name="SIDE">
      <function name="aero/coefficient/CYb">
        <description>Side_force_due_to_beta</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>aero/beta-rad</property>
          <value>-1.0000</value>
        </product>
      </function>
    </axis>

    <axis name="LIFT">
      <documentation>
        created.
      </documentation>
      <function name="aero/coefficient/CLo">
        <description>Lift_at_zero_alpha</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>aero/function/kCLge</property>
          <value>0.2400</value>
        </product>
      </function>
      <documentation>
        substracted CLo 0.240.
      </documentation>
      <function name="aero/coefficient/CLalpha">
        <description>Lift_due_to_alpha</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>aero/function/kCLge</property>
          <table>
            <independentVar>aero/alpha-rad</independentVar>
            <tableData>
              -0.2000	-0.5000	                                     <!-- aeromatic -0.740 -->
              0.0000	0.0000	                                     <!-- aeromatic  0.240 -->
              0.2400	1.1600	                                     <!-- aeromatic  1.400 -->
              0.6000	0.4640	                                     <!-- aeromatic  0.704 -->
            </tableData>
          </table>
        </product>
      </function>
      <documentation>
        to respect the speed limits of gear and flaps, controls by flap angle,
        to get more lift at takeoff setting.

        old : aero/qbar-psf|metrics/Sw-sqft|fcs/flap-pos-norm
      </documentation>
      <function name="aero/coefficient/dCLflap">
        <description>Delta_Lift_due_to_flaps</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>aero/function/kCLge</property>
          <table>
            <independentVar>fcs/flap-pos-deg</independentVar>
            <tableData>
              0.0000	0.0000
              10.0000	0.2100
              27.0000	0.3900
              35.0000	0.4600
              41.0000	0.5600
            </tableData>
          </table>
        </product>
      </function>
      <function name="aero/coefficient/dCLsb">
        <description>Delta_Lift_due_to_speedbrake</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>fcs/speedbrake-pos-norm</property>
          <value>0.0000</value>
        </product>
      </function>
      <function name="aero/coefficient/CLde">
        <description>Lift_due_to_Elevator_Deflection</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>fcs/elevator-pos-rad</property>
          <value>0.2000</value>
        </product>
      </function>
    </axis>

    <axis name="ROLL">
      <function name="aero/coefficient/Clb">
        <description>Roll_moment_due_to_beta</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/bw-ft</property>
          <property>aero/beta-rad</property>
          <value>-0.1000</value>
        </product>
      </function>
      <function name="aero/coefficient/Clp">
        <description>Roll_moment_due_to_roll_rate</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/bw-ft</property>
          <property>aero/bi2vel</property>
          <property>velocities/p-aero-rad_sec</property>
          <value>-0.4000</value>
        </product>
      </function>
      <function name="aero/coefficient/Clr">
        <description>Roll_moment_due_to_yaw_rate</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/bw-ft</property>
          <property>aero/bi2vel</property>
          <property>velocities/r-aero-rad_sec</property>
          <value>0.1500</value>
        </product>
      </function>
      <function name="aero/coefficient/Clda">
        <description>Roll_moment_due_to_aileron</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/bw-ft</property>
          <property>fcs/left-aileron-pos-rad</property>
          <table>
            <independentVar>velocities/mach</independentVar>
            <tableData>
              0.0000	0.1500	
              2.0000	0.0500	
            </tableData>
          </table>
        </product>
      </function>
      <function name="aero/coefficient/Cldr">
        <description>Roll_moment_due_to_rudder</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/bw-ft</property>
          <property>fcs/rudder-pos-rad</property>
          <value>0.0100</value>
        </product>
      </function>
    </axis>

    <axis name="PITCH">
      <function name="aero/coefficient/Cmalpha">
        <description>Pitch_moment_due_to_alpha</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/cbarw-ft</property>
          <property>aero/alpha-rad</property>
          <value>-0.4000</value>
        </product>
      </function>
      <function name="aero/coefficient/Cmde">
        <description>Pitch_moment_due_to_elevator</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/cbarw-ft</property>
          <property>fcs/elevator-pos-rad</property>
          <table>
            <independentVar>velocities/mach</independentVar>
            <tableData>
              0.0000	-1.0000	
              2.0000	-0.2500	
            </tableData>
          </table>
        </product>
      </function>
      <function name="aero/coefficient/Cmq">
        <description>Pitch_moment_due_to_pitch_rate</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/cbarw-ft</property>
          <property>aero/ci2vel</property>
          <property>velocities/q-aero-rad_sec</property>
          <value>-22.0000</value>
        </product>
      </function>
      <function name="aero/coefficient/Cmadot">
        <description>Pitch_moment_due_to_alpha_rate</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/cbarw-ft</property>
          <property>aero/ci2vel</property>
          <property>aero/alphadot-rad_sec</property>
          <value>-8.0000</value>
        </product>
      </function>
    </axis>

    <axis name="YAW">
      <function name="aero/coefficient/Cnb">
        <description>Yaw_moment_due_to_beta</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/bw-ft</property>
          <property>aero/beta-rad</property>
          <value>0.1200</value>
        </product>
      </function>
      <function name="aero/coefficient/Cnr">
        <description>Yaw_moment_due_to_yaw_rate</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/bw-ft</property>
          <property>aero/bi2vel</property>
          <property>velocities/r-aero-rad_sec</property>
          <value>-0.1500</value>
        </product>
      </function>
      <function name="aero/coefficient/Cndr">
        <description>Yaw_moment_due_to_rudder</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/bw-ft</property>
          <property>fcs/rudder-pos-rad</property>
          <value>-0.1000</value>
        </product>
      </function>
      <function name="aero/coefficient/Cnda">
        <description>Adverse_yaw</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/bw-ft</property>
          <property>fcs/left-aileron-pos-rad</property>
          <value>-0.0080</value>
        </product>
      </function>
    </axis>
  </aerodynamics>

  <system file="crash-detect"/>

</fdm_config>
