<?xml version='1.0' encoding='UTF-8'?>
<cmdows xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance" xsi:noNamespaceSchemaLocation="https://bitbucket.org/imcovangent/cmdows/raw/master/schema/0.9/cmdows.xsd">
  <header>
    <creator>unknown</creator>
    <description>not provided</description>
    <timestamp>2018-11-28T18:03:18.163123</timestamp>
    <fileVersion>1.0</fileVersion>
    <cmdowsVersion>0.9</cmdowsVersion>
    <updates>
      <update>
        <modification>KADMOS export of a repository connectivity graph (RCG).</modification>
        <creator>unknown</creator>
        <timestamp>2018-11-28T18:03:18.163123</timestamp>
        <fileVersion>1.0</fileVersion>
        <cmdowsVersion>0.9</cmdowsVersion>
      </update>
    </updates>
    <organization>
      <contacts>
        <contact uID="imcovangent">
          <name>Imco van Gent</name>
          <email>i.vangent@tudelft.nl</email>
          <company>TU Delft</company>
        </contact>
      </contacts>
    </organization>
  </header>
  <executableBlocks>
    <designCompetences>
      <designCompetence uID="HANGAR[AGILE_AC_wing]">
        <label>HANGAR[AGILE_AC_wing]</label>
        <instanceID>1</instanceID>
        <ID>HANGAR</ID>
        <modeID>AGILE_AC_wing</modeID>
        <version>1.0</version>
        <metadata>
          <generalInfo>
            <description>The mode in which the wing of the AGILE DC1 aircraft is initialized for TUD wing analysis.</description>
          </generalInfo>
        </metadata>
      </designCompetence>
      <designCompetence uID="Q3D[VDE]">
        <label>Q3D[VDE]</label>
        <instanceID>1</instanceID>
        <ID>Q3D</ID>
        <modeID>VDE</modeID>
        <version>1.0</version>
        <metadata>
          <generalInfo>
            <description>ViscousDragEstimation: In this mode Q3D analyses the lifting surface for the aerodynamic coefficients at a given flightLoadCase. A visouc analysis is performed to get the right drag value.</description>
          </generalInfo>
        </metadata>
      </designCompetence>
      <designCompetence uID="HANGAR[AGILE_AC]">
        <label>HANGAR[AGILE_AC]</label>
        <instanceID>1</instanceID>
        <ID>HANGAR</ID>
        <modeID>AGILE_AC</modeID>
        <version>1.0</version>
        <metadata>
          <generalInfo>
            <description>The mode in which the full AGILE DC1 aircraft at fidelity level L0 is initialized.</description>
          </generalInfo>
        </metadata>
      </designCompetence>
      <designCompetence uID="SCAM[wing_spar_morph]">
        <label>SCAM[wing_spar_morph]</label>
        <instanceID>1</instanceID>
        <ID>SCAM</ID>
        <modeID>wing_spar_morph</modeID>
        <version>1.0</version>
        <metadata>
          <generalInfo>
            <description>Adjustment of the wing front and rear spar positions.</description>
          </generalInfo>
        </metadata>
      </designCompetence>
      <designCompetence uID="SMFA">
        <label>SMFA</label>
        <instanceID>1</instanceID>
        <ID>SMFA</ID>
        <modeID>Main</modeID>
        <version>1.0</version>
        <metadata>
          <generalInfo>
            <description>The main and only mode of SMFA.</description>
          </generalInfo>
        </metadata>
      </designCompetence>
      <designCompetence uID="SCAM[wing_length_morph]">
        <label>SCAM[wing_length_morph]</label>
        <instanceID>1</instanceID>
        <ID>SCAM</ID>
        <modeID>wing_length_morph</modeID>
        <version>1.0</version>
        <metadata>
          <generalInfo>
            <description>Adjustment of total lenght of all the wing segments.</description>
          </generalInfo>
        </metadata>
      </designCompetence>
      <designCompetence uID="PHALANX[Full_Simple]">
        <label>PHALANX[Full_Simple]</label>
        <instanceID>1</instanceID>
        <ID>PHALANX</ID>
        <modeID>Full_Simple</modeID>
        <version>1.0</version>
        <metadata>
          <generalInfo>
            <description>sfull refers to the EOMs and means that full analysis is done (lat and long). simple refers to engine analysis, where approximate values are used</description>
          </generalInfo>
        </metadata>
      </designCompetence>
      <designCompetence uID="GACA[mainWingFuelTankVol]">
        <label>GACA[mainWingFuelTankVol]</label>
        <instanceID>1</instanceID>
        <ID>GACA</ID>
        <modeID>mainWingFuelTankVol</modeID>
        <version>1.0</version>
        <metadata>
          <generalInfo>
            <description>Determination of the volume of the fuel tank in the wing.</description>
          </generalInfo>
        </metadata>
      </designCompetence>
      <designCompetence uID="PHALANX[Symmetric_Lookup]">
        <label>PHALANX[Symmetric_Lookup]</label>
        <instanceID>1</instanceID>
        <ID>PHALANX</ID>
        <modeID>Symmetric_Lookup</modeID>
        <version>1.0</version>
        <metadata>
          <generalInfo>
            <description>symmetric refers to the EOMs and means that no lateral analysis is done. Lookup refers to engine performance maps, where exact values are looked up.</description>
          </generalInfo>
        </metadata>
      </designCompetence>
      <designCompetence uID="SCAM[wing_sweep_morph]">
        <label>SCAM[wing_sweep_morph]</label>
        <instanceID>1</instanceID>
        <ID>SCAM</ID>
        <modeID>wing_sweep_morph</modeID>
        <version>1.0</version>
        <metadata>
          <generalInfo>
            <description>Adjustment of the sweep angle of each wing segment.</description>
          </generalInfo>
        </metadata>
      </designCompetence>
      <designCompetence uID="PHALANX[Symmetric_Simple]">
        <label>PHALANX[Symmetric_Simple]</label>
        <instanceID>1</instanceID>
        <ID>PHALANX</ID>
        <modeID>Symmetric_Simple</modeID>
        <version>1.0</version>
        <metadata>
          <generalInfo>
            <description>symmetric refers to the EOMs and means that no lateral analysis is done. simple refers to engine analysis, where approximate values are used</description>
          </generalInfo>
        </metadata>
      </designCompetence>
      <designCompetence uID="Q3D[FLC]">
        <label>Q3D[FLC]</label>
        <instanceID>1</instanceID>
        <ID>Q3D</ID>
        <modeID>FLC</modeID>
        <version>1.0</version>
        <metadata>
          <generalInfo>
            <description>FlightLoadCase: In this case Q3D only performs the inviscid VLM analysis in order to provide the loads per wing strip in an aeroDataSetForLoads associated with the flightLoadCase. These loads can then be used for further analysis.</description>
          </generalInfo>
        </metadata>
      </designCompetence>
      <designCompetence uID="PROTEUS">
        <label>PROTEUS</label>
        <instanceID>1</instanceID>
        <ID>PROTEUS</ID>
        <modeID>Main</modeID>
        <version>1.0</version>
        <metadata>
          <generalInfo>
            <description>Add description here.</description>
          </generalInfo>
        </metadata>
      </designCompetence>
      <designCompetence uID="SCAM[wing_taper_morph]">
        <label>SCAM[wing_taper_morph]</label>
        <instanceID>1</instanceID>
        <ID>SCAM</ID>
        <modeID>wing_taper_morph</modeID>
        <version>1.0</version>
        <metadata>
          <generalInfo>
            <description>Adjustment of the tip chord length of each wing segment w.r.t. the wing root chord using a taper ratio value.</description>
          </generalInfo>
        </metadata>
      </designCompetence>
      <designCompetence uID="INITIATOR">
        <label>INITIATOR</label>
        <instanceID>1</instanceID>
        <ID>INITIATOR</ID>
        <modeID>Main</modeID>
        <version>1.0</version>
        <metadata>
          <generalInfo>
            <description>Add description here.</description>
          </generalInfo>
        </metadata>
      </designCompetence>
      <designCompetence uID="SCAM[wing_dihedral_morph]">
        <label>SCAM[wing_dihedral_morph]</label>
        <instanceID>1</instanceID>
        <ID>SCAM</ID>
        <modeID>wing_dihedral_morph</modeID>
        <version>1.0</version>
        <metadata>
          <generalInfo>
            <description>Adjustment of the full wing dihedral to a single new value.</description>
          </generalInfo>
        </metadata>
      </designCompetence>
      <designCompetence uID="Q3D[APM]">
        <label>Q3D[APM]</label>
        <instanceID>1</instanceID>
        <ID>Q3D</ID>
        <modeID>APM</modeID>
        <version>1.0</version>
        <metadata>
          <generalInfo>
            <description>AeroPerformanceMap: In this case Q3D analyses the lifting surface for the range of Mach numbers, Reynold?s numbers, and angle of attacks specified in the aeroPerformanceMap. The tool then provides the lift, drag and (quarter-chord) moment coefficients of the complete wing.</description>
          </generalInfo>
        </metadata>
      </designCompetence>
      <designCompetence uID="MaCal">
        <label>MaCal</label>
        <instanceID>1</instanceID>
        <ID>MaCal</ID>
        <modeID>Main</modeID>
        <version>1.0</version>
        <metadata>
          <generalInfo>
            <description>Add description here.</description>
          </generalInfo>
        </metadata>
      </designCompetence>
      <designCompetence uID="EMWET">
        <label>EMWET</label>
        <instanceID>1</instanceID>
        <ID>EMWET</ID>
        <modeID>Main</modeID>
        <version>1.0</version>
        <metadata>
          <generalInfo>
            <description>The main and only mode of EMWET.</description>
          </generalInfo>
        </metadata>
      </designCompetence>
      <designCompetence uID="PHALANX[Full_Lookup]">
        <label>PHALANX[Full_Lookup]</label>
        <instanceID>1</instanceID>
        <ID>PHALANX</ID>
        <modeID>Full_Lookup</modeID>
        <version>1.0</version>
        <metadata>
          <generalInfo>
            <description>symmetric refers to the EOMs and means that no lateral analysis is done. Lookup refers to engine performance maps, where exact values are looked up.</description>
          </generalInfo>
        </metadata>
      </designCompetence>
      <designCompetence uID="SCAM[wing_root_chord_morph]">
        <label>SCAM[wing_root_chord_morph]</label>
        <instanceID>1</instanceID>
        <ID>SCAM</ID>
        <modeID>wing_root_chord_morph</modeID>
        <version>1.0</version>
        <metadata>
          <generalInfo>
            <description>Adjustment wing root chord length.</description>
          </generalInfo>
        </metadata>
      </designCompetence>
      <designCompetence uID="GACA[mainWingRefArea]">
        <label>GACA[mainWingRefArea]</label>
        <instanceID>1</instanceID>
        <ID>GACA</ID>
        <modeID>mainWingRefArea</modeID>
        <version>1.0</version>
        <metadata>
          <generalInfo>
            <description>Determination of the reference (projected) area of the main wing.</description>
          </generalInfo>
        </metadata>
      </designCompetence>
    </designCompetences>
    <mathematicalFunctions>
      <mathematicalFunction uID="OBJ">
        <label>OBJ</label>
        <functionType>regular</functionType>
        <inputs>
          <input>
            <parameterUID>/cpacs/vehicles[@uID="AGILE_DC1_vehicleID"]/aircraft/model[@uID="agile_v13_modelID"]/analyses/massBreakdown/designMasses/mTOM/mass</parameterUID>
            <equationLabel>mass</equationLabel>
          </input>
          <input>
            <parameterUID>/cpacs/toolspecific/oBJ/MTOW/mtow_ref</parameterUID>
            <equationLabel>mtow_ref</equationLabel>
          </input>
        </inputs>
        <outputs>
          <output>
            <parameterUID>/cpacs/mdodata/objectives/mtow/normalized_mtow</parameterUID>
            <equations uID="OBJ_equation">
              <equation language="Python">mass/mtow_ref</equation>
              <equation language="LaTeX">mass/mtow\_ref</equation>
              <equation language="MathML">&lt;math xmlns="http://www.w3.org/1998/Math/MathML"&gt;&lt;mi&gt;m&lt;/mi&gt;&lt;mi&gt;a&lt;/mi&gt;&lt;mi&gt;s&lt;/mi&gt;&lt;mi&gt;s&lt;/mi&gt;&lt;mo&gt;/&lt;/mo&gt;&lt;mi&gt;m&lt;/mi&gt;&lt;mi&gt;t&lt;/mi&gt;&lt;mi&gt;o&lt;/mi&gt;&lt;mi&gt;w&lt;/mi&gt;&lt;mi&gt;_&lt;/mi&gt;&lt;mi&gt;r&lt;/mi&gt;&lt;mi&gt;e&lt;/mi&gt;&lt;mi&gt;f&lt;/mi&gt;&lt;/math&gt;</equation>
            </equations>
          </output>
        </outputs>
      </mathematicalFunction>
      <mathematicalFunction uID="CNSTRNT_wingLoading">
        <label>CNSTRNT[wingLoading]</label>
        <functionType>regular</functionType>
        <inputs>
          <input>
            <parameterUID>/cpacs/vehicles[@uID="AGILE_DC1_vehicleID"]/aircraft/model[@uID="agile_v13_modelID"]/reference/area</parameterUID>
            <equationLabel>area</equationLabel>
          </input>
          <input>
            <parameterUID>/cpacs/toolspecific/cNSTRNT/wingLoading/maxWingLoading</parameterUID>
            <equationLabel>WSmax</equationLabel>
          </input>
          <input>
            <parameterUID>/cpacs/vehicles[@uID="AGILE_DC1_vehicleID"]/aircraft/model[@uID="agile_v13_modelID"]/analyses/massBreakdown/designMasses/mTOM/mass</parameterUID>
            <equationLabel>MTOM</equationLabel>
          </input>
        </inputs>
        <outputs>
          <output>
            <parameterUID>/cpacs/mdodata/constraints/wingLoading/latestValue</parameterUID>
            <equations uID="wing_loading_equation">
              <equation language="Python">MTOM/area-WSmax</equation>
            </equations>
          </output>
        </outputs>
      </mathematicalFunction>
      <mathematicalFunction uID="CNSTRNT_fuelTankVolume">
        <label>CNSTRNT[fuelTankVolume]</label>
        <functionType>regular</functionType>
        <inputs>
          <input>
            <parameterUID>/cpacs/vehicles[@uID="AGILE_DC1_vehicleID"]/aircraft/model[@uID="agile_v13_modelID"]/analyses/massBreakdown/fuel/massDescription/mass</parameterUID>
            <equationLabel>fuelmass</equationLabel>
          </input>
          <input>
            <parameterUID>/cpacs/vehicles[@uID="AGILE_DC1_vehicleID"]/aircraft/model[@uID="agile_v13_modelID"]/wings/wing[@uID="MainWing_wingID"]/componentSegments/componentSegment[@uID="wing_Cseg"]/wingFuelTanks/wingFuelTank[@uID="MainWingFuelTank"]/volume/optimalVolume</parameterUID>
            <equationLabel>tankvol</equationLabel>
          </input>
          <input>
            <parameterUID>/cpacs/toolspecific/cNSTRNT/fuelTankVolume/fuelTankEfficiencyFactor</parameterUID>
            <equationLabel>etatank</equationLabel>
          </input>
          <input>
            <parameterUID>/cpacs/toolspecific/cNSTRNT/fuelTankVolume/fuelDensity</parameterUID>
            <equationLabel>rhofuel</equationLabel>
          </input>
        </inputs>
        <outputs>
          <output>
            <parameterUID>/cpacs/mdodata/constraints/fuelTankVolume/latestValue</parameterUID>
            <equations uID="fuel_tank_volume_equation">
              <equation language="Python">tankvol*etatank-fuelmass/rhofuel</equation>
            </equations>
          </output>
        </outputs>
      </mathematicalFunction>
    </mathematicalFunctions>
  </executableBlocks>
  <parameters>
    <parameter uID="/cpacs/vehicles[@uID=&quot;AGILE_DC1_vehicleID&quot;]/aircraft/model[@uID=&quot;agile_v13_modelID&quot;]/analyses/massBreakdown/fuel/massDescription/mass">
      <label>fuelMass</label>
      <instanceID>1</instanceID>
    </parameter>
    <parameter uID="/cpacs/toolspecific/cNSTRNT/fuelTankVolume/fuelTankEfficiencyFactor">
      <label>fuelEfficiencyFactor</label>
      <instanceID>1</instanceID>
    </parameter>
    <parameter uID="/cpacs/toolspecific/cNSTRNT/fuelTankVolume/fuelDensity">
      <label>fuelmass</label>
      <instanceID>1</instanceID>
    </parameter>
    <parameter uID="/cpacs/vehicles[@uID=&quot;AGILE_DC1_vehicleID&quot;]/aircraft/model[@uID=&quot;agile_v13_modelID&quot;]/wings/wing[@uID=&quot;MainWing_wingID&quot;]/componentSegments/componentSegment[@uID=&quot;wing_Cseg&quot;]/wingFuelTanks/wingFuelTank[@uID=&quot;MainWingFuelTank&quot;]/volume/optimalVolume">
      <label>fuelTankVolume</label>
      <instanceID>1</instanceID>
    </parameter>
    <parameter uID="/cpacs/mdodata/constraints/fuelTankVolume/latestValue">
      <label>fuelmass</label>
      <instanceID>1</instanceID>
    </parameter>
    <parameter uID="/cpacs/vehicles[@uID=&quot;AGILE_DC1_vehicleID&quot;]/aircraft/model[@uID=&quot;agile_v13_modelID&quot;]/analyses/massBreakdown/designMasses/mTOM/mass">
      <label>MTOM</label>
      <instanceID>1</instanceID>
    </parameter>
    <parameter uID="/cpacs/toolspecific/oBJ/MTOW/mtow_ref">
      <label>MTOMref</label>
      <instanceID>1</instanceID>
    </parameter>
    <parameter uID="/cpacs/mdodata/objectives/mtow/normalized_mtow">
      <label>MTOMnorm</label>
      <instanceID>1</instanceID>
    </parameter>
    <parameter uID="/cpacs/toolspecific/cNSTRNT/wingLoading/maxWingLoading">
      <label>maxWingLoading</label>
      <instanceID>1</instanceID>
    </parameter>
    <parameter uID="/cpacs/vehicles[@uID=&quot;AGILE_DC1_vehicleID&quot;]/aircraft/model[@uID=&quot;agile_v13_modelID&quot;]/reference/area">
      <label>wingArea</label>
      <instanceID>1</instanceID>
    </parameter>
    <parameter uID="/cpacs/mdodata/constraints/wingLoading/latestValue">
      <label>wingLoading</label>
      <instanceID>1</instanceID>
    </parameter>
  </parameters>
</cmdows>