<?xml version="1.0" encoding="UTF-8"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<!--
**************************************************************************

Beagle Pup 100 (B.121 Series 1)

Copyright (c) 2015 Richard Senior

This program is free software: you can redistribute it and/or modify
it under the terms of the GNU General Public License as published by
the Free Software Foundation, either version 2 of the License, or
(at your option) any later version.

This program is distributed in the hope that it will be useful,
but WITHOUT ANY WARRANTY; without even the implied warranty of
MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE.  See the
GNU General Public License for more details.

You should have received a copy of the GNU General Public License
along with this program.  If not, see <http://www.gnu.org/licenses/>.

**************************************************************************
-->

<fdm_config name="Beagle-121-1" version="2.0" release="ALPHA"
  xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
  xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

  <fileheader>
    <author>Richard Senior (Aeromatic v3.3.8)</author>
    <filecreationdate>25 Nov 2016</filecreationdate>
    <version>0.2</version>
    <description>Beagle 121 Series 1 (Pup 100)</description>
  </fileheader>

<!--
  File:     pup100.xml
  Inputs:
    name:          pup100
    type:          Single engine Glider, Small Commuter
    stall speed:   62.00kts
    max weight:    1600.00 lb
    length:        22.92 ft
    wing:
     span:         31.00 ft
     area:         119.50 sq-ft
     mean chord:   3.82 ft
     aspect ratio: 8.04:1
     taper ratio:  0.56:1
     incidence:    2.00 degrees
     dihedral:     6.67 degrees
     sweep:        3.00 degrees

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

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

  Outputs:
    wing loading:       13.39 lb/sq-ft
     - thickness ratio: 5.78%
    payload:            280.20 lbs
    CL-alpha:           5.43 per radian
    CL-0:               0.22
    CL-max:             1.03
    CD-0:               0.02
    K:                  0.04
    Mcrit:              0.70
-->

  <metrics>
    <wingarea  unit="FT2">  119.50 </wingarea>
    <wingspan  unit="FT" >   31.00 </wingspan>
    <wing_incidence unit="DEG"> 2.00 </wing_incidence>
    <chord     unit="FT" >    3.82 </chord>
    <htailarea unit="FT2">    27.50 </htailarea>
    <htailarm  unit="FT" >    11.86 </htailarm>
    <vtailarea  unit="FT2">   21.70 </vtailarea>
    <vtailarm  unit="FT" >    12.34 </vtailarm>
    <location name="AERORP" unit="IN">
      <x>  86.00 </x>
      <y>   0.00 </y>
      <z>  -3.50 </z>
    </location>
    <location name="EYEPOINT" unit="IN">
      <x>  82.00 </x>
      <y> -18.00 </y>
      <z>  20.00 </z>
    </location>
    <location name="VRP" unit="IN">
      <x>0</x>
      <y>0</y>
      <z>0</z>
    </location>
  </metrics>

  <mass_balance>
    <ixx unit="SLUG*FT2">    589.07 </ixx>
    <iyy unit="SLUG*FT2">    572.46 </iyy>
    <izz unit="SLUG*FT2">   1078.08 </izz>
    <!-- Quoted empty weight (1083) minus engine (220), which is below -->
    <emptywt unit="LBS" >    863.00 </emptywt>
    <location name="CG" unit="IN">
      <x>  72.00 </x>
      <y>   0.00 </y>
      <z> -9.00 </z>
    </location>
    <pointmass name="Engine">
      <description>Engine and associated components</description>
      <weight unit="LBS">220</weight>
      <location name="POINTMASS" unit="IN">
        <x>  32.00 </x>
        <y>   0.00 </y>
        <z>  -2.00 </z>
      </location>
    </pointmass>
    <pointmass name="Pilot">
      <description>Pilot</description>
      <weight unit="LBS">170</weight>
      <location name="POINTMASS" unit="IN">
        <x>  92.00 </x>
        <y> -12.00 </y>
        <z>  -7.00 </z>
      </location>
    </pointmass> 
    <pointmass name="Co-Pilot">
      <description>Co-Pilot</description>
      <weight unit="LBS">0</weight>
      <location name="POINTMASS" unit="IN">
        <x>  92.00 </x>
        <y>  12.00 </y>
        <z>  -7.00 </z>
      </location>
    </pointmass> 
    <pointmass name="Rear Seat">
      <description>Rear Seat</description>
      <weight unit="LBS">0</weight>
      <location name="POINTMASS" unit="IN">
        <x> 122.00 </x>
        <y>   0.00 </y>
        <z>  -4.00 </z>
      </location>
    </pointmass> 
  </mass_balance>

  <ground_reactions file="pup-ground-reactions"/>

  <propulsion>

    <engine file="Continental_0-200-A">
      <location unit="IN">
        <x>  28.98 </x>
        <y>   0.00 </y>
        <z>   0.00 </z>
      </location>
      <orient unit="DEG">
        <pitch> 0.00 </pitch>
        <roll>  0.00 </roll>
        <yaw>   0.00 </yaw>
      </orient>
      <feed>0</feed>
      <thruster file="McCauley_1A105-SCM-7053">
        <sense> 1 </sense>
        <location unit="IN">
          <x>  10.73 </x>
          <y>   0.00 </y>
          <z>   0.00 </z>
        </location>
        <orient unit="DEG">
          <pitch> 0.00 </pitch>
          <roll>  0.00 </roll>
          <yaw>   0.00 </yaw>
        </orient>
      </thruster>
    </engine>

    <!-- Fuel manifold, fuel pump, etc. -->
    <tank type="FUEL" number="0">
      <location unit="IN">
        <x>  41.00 </x>
        <y>   0.00 </y>
        <z>   0.00 </z>
      </location>
      <capacity unit="LBS">1.00</capacity>
      <contents unit="LBS">0.00</contents>
    </tank>

    <tank type="FUEL" number="1">
      <location unit="IN">
        <x>  79.00 </x>
        <y> -48.00 </y>
        <z> -11.00 </z>
      </location>
      <capacity unit="LBS">  95.18 </capacity>
      <contents unit="LBS">  23.80 </contents>
    </tank>

    <tank type="FUEL" number="2">
      <location unit="IN">
        <x>  79.00 </x>
        <y>  48.00 </y>
        <z> -11.00 </z>
      </location>
      <capacity unit="LBS">  95.18 </capacity>
      <contents unit="LBS">  23.80 </contents>
    </tank>

  </propulsion>

  <system file="analysis"/>
  <system file="crash-detect"/>
  <system file="fuel"/>

  <!-- Required for aeromatic generated FDM -->
  <system name="Landing Gear">
    <channel name="Landing Gear">
      <switch name="fcs/gear-no-wow">
        <default value="1"/>
        <test logic="AND" value="0">
          gear/unit[1]/WOW eq 1
          gear/unit[2]/WOW eq 1
        </test>
      </switch>
    </channel>
  </system>

  <flight_control name="FCS: BeaglePup-121-1" file="pup-flight-control"/>
  <aerodynamics file="pup-aerodynamics"/>

</fdm_config>
