<?xml version="1.0" encoding="UTF-8"?>
<zeroGuiIn>
    <component>
        <name>Engine</name>
        <disciplines>
            <discipline>
                <name>Inertia</name>
                <parameters>
                    <parameter>
                        <name>massIY</name>
                        <description>
							the mass moment of inertia in Y 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>massIX</name>
                        <description>
							the mass moment of inertia in X 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>massIZ</name>
                        <description>
							the mass moment of inertia in Z 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
            <discipline>
                <name>Geometry</name>
                <parameters>
                    <parameter>
                        <name>yEngine</name>
                        <description>
							spanwise location of the engine 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>xEngine</name>
                        <description>
							x-wise location of the engine 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>wetArea</name>
                        <description>
							wetted area of the engine 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>lEngine</name>
                        <description>
							length of the engine  
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>dEngine</name>
                        <description>
							diameter of the engine 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
            <discipline>
                <name>Propulsion</name>
                <parameters>
                    <parameter>
                        <name>thrustTWDat</name>
                        <description>
							Scaling factor for TWDat derived from current thrust00 in CPACS and
							current thrustTO from VAMPzero 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>etaCompr</name>
                        <description>
							Compressor efficiency 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>etaTransm</name>
                        <description>
							Transmission efficiency 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>thrustCR</name>
                        <description>
							cruise thrust  
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>mDotEngine</name>
                        <description>
							mass flow rate through the engine 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>etaTurb</name>
                        <description>
							Turbine efficiency 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>sfcCR</name>
                        <description>
							SFC for cruise Condition  
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>etaTherm</name>
                        <description>
							Thermal efficiency 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>thrustTO</name>
                        <description>
							takeoff thrust 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>nEngine</name>
                        <description>
							Number of Engines 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>TET</name>
                        <description>
							Turbine Entry Temperature
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>etaFan</name>
                        <description>
							Fan efficiency 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>bypassRatio</name>
                        <description>
							bypass ratio for the engine 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>etaProp</name>
                        <description>
							Propulsive efficiency 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>OPR</name>
                        <description>
							Overall Pressure Ratio 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>sfcLOI</name>
                        <description>
							SFC for Loiter Condition 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
            <discipline>
                <name>Mass</name>
                <parameters>
                    <parameter>
                        <name>mEngine</name>
                        <description>
							Engine Mass 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
            <discipline>
                <name>Cog</name>
                <parameters>
                    <parameter>
                        <name>posCoG</name>
                        <description>
							posCoG from the engine 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
            <discipline>
                <name>Aerodynamic</name>
                <parameters>
                    <parameter>
                        <name>formFactor</name>
                        <description>
							form factor for the engine 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>reynoldsNr</name>
                        <description>
							reynoldsnumber relative to the engine length 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cD0c</name>
                        <description>
							Calculates the zero lift drag coefficient component-wise 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cfLAM</name>
                        <description>
							laminar friction coefficient 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cfTURB</name>
                        <description>
							turbulent friction coefficient 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
        </disciplines>
    </component>
    <component>
        <name>Atmosphere</name>
        <disciplines>
            <discipline>
                <name>Fl1500</name>
                <parameters>
                    <parameter>
                        <name>sigmaFL1500</name>
                        <description>
							sigma at FL1500 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>aFL1500</name>
                        <description>
							speed of sound at FL1500 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>rhoFL1500</name>
                        <description>
							density 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>TASFL1500</name>
                        <description>
							true airspeed at FL1500 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>MaFL1500</name>
                        <description>
							machNumber at FL1500 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>qFL1500</name>
                        <description>
							q at FL1500 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>nyFL1500</name>
                        <description>
							ny at FL1500 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>EASFL1500</name>
                        <description>
							equivalent airspeed at FL1500 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>hFL1500</name>
                        <description>
							height at FL1500 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>TFL1500</name>
                        <description>
							temperature at TFL1500 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>myFL1500</name>
                        <description>
							my at FL1500 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
            <discipline>
                <name>Airport</name>
                <parameters>
                    <parameter>
                        <name>TAP</name>
                        <description>
							temperature at airport level 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>rhoAP</name>
                        <description>
							density at airport height 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>aAP</name>
                        <description>
							speed of sound on airport level 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>sigmaAP</name>
                        <description>
							sigma at Airport height 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>hAP</name>
                        <description>
							height at the airport 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
            <discipline>
                <name>Cruise</name>
                <parameters>
                    <parameter>
                        <name>nyCR</name>
                        <description>
							ny at cruise condition 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>TASCR</name>
                        <description>
							true airspeed at cruise condition 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>EASCR</name>
                        <description>
							equivalent airspeed at cruise 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>qCR</name>
                        <description>
							Staudruck 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>rhoCR</name>
                        <description>
							density 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>TCR</name>
                        <description>
							temperature at cruise condition 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>aCR</name>
                        <description>
							speed of sound at cruise level 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>myCR</name>
                        <description>
							my at Cruise Condition 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>MaCR</name>
                        <description>
							machnumber at cruise condition 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>hCR</name>
                        <description>
							height at cruise 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>sigmaCR</name>
                        <description>
							sigma at cruise condition 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
        </disciplines>
    </component>
    <component>
        <name>Htpairfoil</name>
        <disciplines>
            <discipline>
                <name>Aerodynamic</name>
                <parameters>
                    <parameter>
                        <name>clMAX</name>
                        <description>
							the airfoils maximum lift coefficient  
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>aType</name>
                        <description>
							The Airfoil Type 0. for symmetric, 1. for cambered
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>tc</name>
                        <description>
							Thickness to Chord Ratio 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>reynoldsNr</name>
                        <description>
							Reynolds number at this airfoil 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>ctm</name>
                        <description>
							chord position of maximum thickness between 0. and 1. 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
        </disciplines>
    </component>
    <component>
        <name>Vtpairfoil</name>
        <disciplines>
            <discipline>
                <name>Aerodynamic</name>
                <parameters>
                    <parameter>
                        <name>clMAX</name>
                        <description>
							the airfoils maximum lift coefficient  
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>aType</name>
                        <description>
							The Airfoil Type 0. for symmetric, 1. for cambered
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>tc</name>
                        <description>
							Thickness to Chord Ratio 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>reynoldsNr</name>
                        <description>
							Reynolds number at this airfoil 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>ctm</name>
                        <description>
							chord position of maximum thickness between 0. and 1. 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
        </disciplines>
    </component>
    <component>
        <name>Wingtipairfoil</name>
        <disciplines>
            <discipline>
                <name>Aerodynamic</name>
                <parameters>
                    <parameter>
                        <name>clMAX</name>
                        <description>
							the airfoils maximum lift coefficient  
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>aType</name>
                        <description>
							The Airfoil Type 0. for symmetric, 1. for cambered
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>tc</name>
                        <description>
							Thickness to Chord Ratio 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>reynoldsNr</name>
                        <description>
							Reynolds number at this airfoil 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>ctm</name>
                        <description>
							chord position of maximum thickness between 0. and 1. 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
        </disciplines>
    </component>
    <component>
        <name>Landinggear</name>
        <disciplines>
            <discipline>
                <name>Mass</name>
                <parameters>
                    <parameter>
                        <name>mLandingGear</name>
                        <description>
							mass of the Landing Gear 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
        </disciplines>
    </component>
    <component>
        <name>Vtp</name>
        <disciplines>
            <discipline>
                <name>Geometry</name>
                <parameters>
                    <parameter>
                        <name>cMAC</name>
                        <description>
							mean aerodynamic chord of the wing 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>refArea</name>
                        <description>
							reference area for the vertical tail  
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>taperRatio</name>
                        <description>
							taper ratio of the wing 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>xMAC</name>
                        <description>
							x location of the mean aerodynamic chord of the wing
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cTip</name>
                        <description>
							tip chord of the Wing
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>phiTE</name>
                        <description>
							trailing edge sweep angle  
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>span</name>
                        <description>
							wing span 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cVT</name>
                        <description>
							vertical tail volume coefficent 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cRoot</name>
                        <description>
							root chord of the wing
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>expArea</name>
                        <description>
							exposed area of the vtp 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>xRoot</name>
                        <description>
							position of the vertical tail 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>wetArea</name>
                        <description>
							wetted area of a wing
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>dihedral</name>
                        <description>
							Wing Dihedral Angle 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>lVT</name>
                        <description>
							lever for the vertical tail 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>zRoot</name>
                        <description>
							zPosition at vtp Root
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>yMAC</name>
                        <description>
							wing mean aerodynamic chord's y location
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>phi25</name>
                        <description>
							quarter chord sweep  
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>tcAVG</name>
                        <description>
							average thickness to chord ratio of the wing 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>phiLE</name>
                        <description>
							leading edge sweep of a wing element 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>aspectRatio</name>
                        <description>
							aspect ratio of a vtp 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
            <discipline>
                <name>Aerodynamic</name>
                <parameters>
                    <parameter>
                        <name>cLalpha</name>
                        <description>
							cL depending on alpha 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>formFactor</name>
                        <description>
							form factor for the wing 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cLMAX</name>
                        <description>
							max cL for the wing 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cD0c</name>
                        <description>
							zero lift drag componentwise for the wing  
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>reynoldsNr</name>
                        <description>
							Reynolds number 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cfLAM</name>
                        <description>
							laminar friction coefficient 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cfTURB</name>
                        <description>
							turbulent friction coefficient 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
            <discipline>
                <name>Mass</name>
                <parameters>
                    <parameter>
                        <name>mVtp</name>
                        <description>
							vertical tail mass 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
            <discipline>
                <name>Cog</name>
                <parameters>
                    <parameter>
                        <name>posCoG</name>
                        <description>
							Calculates the coordinates of the vtp center of gravity location
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
        </disciplines>
    </component>
    <component>
        <name>Aircraft</name>
        <disciplines>
            <discipline>
                <name>Sizing</name>
                <parameters>
                    <parameter>
                        <name>wsMAX</name>
                        <description>
							maximum Wing Loading 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>twCLIMB</name>
                        <description>
							Thrust to Weight ratio for ClimbSegments
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>twTO</name>
                        <description>
							Thrust to Weight ratio for takeoff
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>wsTO</name>
                        <description>
							Wing Loading for Takeoff  
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>wsL</name>
                        <description>
							Wing Loading for Landing Condition 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
            <discipline>
                <name>Mass</name>
                <parameters>
                    <parameter>
                        <name>oIM</name>
                        <description>
							Operator Item Mass 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>oEM</name>
                        <description>
							max Operating Empty Weight 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>mZFW</name>
                        <description>
							max zero Fuel Weight 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>mTOM</name>
                        <description>
							The maximum Takeoff-Weight for an Aircraft 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>mLM</name>
                        <description>
							The maximum Landing-Weight for an Aircraft 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
            <discipline>
                <name>Cog</name>
                <parameters>
                    <parameter>
                        <name>posNP</name>
                        <description>
							Position of the Neutral Point relative to cMAC
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>posCoG</name>
                        <description>
							Position of the Center of Gravity relative to cMAC
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
            <discipline>
                <name>Aerodynamic</name>
                <parameters>
                    <parameter>
                        <name>cDCR</name>
                        <description>
							Drag coefficient for cruise condiotion 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cLCR</name>
                        <description>
							Cruise lift coefficient 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cLMAX</name>
                        <description>
							Airplane clean CLmax  
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>loDLOI</name>
                        <description>
							Lift-over-drag ratio for loiter 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>loDCLIMB</name>
                        <description>
							Lift over Drag ratio for ClimbSegments
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>loDTO</name>
                        <description>
							Lift-over-drag ratio for takeoff 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cLL</name>
                        <description>
							Maximum Landing Lift Coefficent 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>loDCR</name>
                        <description>
							Lift over Drag Ratio for the Cruise Condition
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cD0</name>
                        <description>
							Zero-lift drag of the airplane 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cLTO</name>
                        <description>
							Maximum Takeoff Lift Coefficent  
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
            <discipline>
                <name>Performance</name>
                <parameters>
                    <parameter>
                        <name>gammaCLIMB</name>
                        <description>
							gradient for ClimbSegments
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>timeCLIMB</name>
                        <description>
							time in climb segment 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>rangeType</name>
                        <description>
							RangeType: 0= shortRange, 1= mediumRange, 2= longRange, 3 = verylongRange
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>distDESCENT</name>
                        <description>
							distance in descent segment 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>desRange</name>
                        <description>
							The design range for the aircraft 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>distRES</name>
                        <description>
							distance in the reserver segment
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>altCR</name>
                        <description>
							Cruise Altitude 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>IASCLIMB</name>
                        <description>
							indicated airspeed at climb
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>IASDESCENT</name>
                        <description>
							indicated airspeed at descent
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>sTOFL</name>
                        <description>
							TO Field Length 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>gammaDESCENT</name>
                        <description>
							gradient for descent segment
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>timeRES</name>
                        <description>
							Reserve time 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>distCLIMB</name>
                        <description>
							distance in climb segment 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>timeCR</name>
                        <description>
							time during cruise segment 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>distCR</name>
                        <description>
							distance during cruise segment 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>machCR</name>
                        <description>
							Cruise Mach Number 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>sLFL</name>
                        <description>
							Landing Field Length 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>timeDESCENT</name>
                        <description>
							time in descent segment 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
            <discipline>
                <name>Main</name>
                <parameters>
                    <parameter>
                        <name>uID</name>
                        <description>Default Doc</description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
            <discipline>
                <name>Inertia</name>
                <parameters>
                    <parameter>
                        <name>massIY</name>
                        <description>
							The mass moment of inertia in Y 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>massIX</name>
                        <description>
							The mass moment of inertia in X 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>massIZ</name>
                        <description>
							The mass moment of inertia in Z 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
        </disciplines>
    </component>
    <component>
        <name>Pylon</name>
        <disciplines>
            <discipline>
                <name>Mass</name>
                <parameters>
                    <parameter>
                        <name>mPylon</name>
                        <description>
							description 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
        </disciplines>
    </component>
    <component>
        <name>Fuselage</name>
        <disciplines>
            <discipline>
                <name>Geometry</name>
                <parameters>
                    <parameter>
                        <name>ltail</name>
                        <description>
							length of fuselage tail section 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>lfus</name>
                        <description>
							fuselage length  
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>lcabin</name>
                        <description>
							length of the cabin section 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>dfus</name>
                        <description>
							fuselage diameter 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>wetArea</name>
                        <description>
							wetted area of the fuselage 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>loverlay</name>
                        <description>
							overlay between cabin and tailcone. i.e. the distance from the beginning
							of the tail cone to the rear pressure bulkhead 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>lnose</name>
                        <description>
							length of the fuselage nose section 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>lcockpit</name>
                        <description>
							length of the cockpit section 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
            <discipline>
                <name>Aerodynamic</name>
                <parameters>
                    <parameter>
                        <name>formFactor</name>
                        <description>
							form factor for the fuselage 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>reynoldsNr</name>
                        <description>
							Reynolds number relative to the fuselage length 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cD0c</name>
                        <description>
							zero lift drag componentwise for the fuselage 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cfLAM</name>
                        <description>
							laminar friction coefficient 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cfTURB</name>
                        <description>
							turbulent friction coefficient 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
            <discipline>
                <name>Mass</name>
                <parameters>
                    <parameter>
                        <name>mFurn</name>
                        <description>
							furnishings mass    
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>mFuselage</name>
                        <description>
							total fuselage Mass 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>mStructure</name>
                        <description>
							fuselage structure mass from the area 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
            <discipline>
                <name>Cog</name>
                <parameters>
                    <parameter>
                        <name>posCoG</name>
                        <description>
							fuselage center of gravity location 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
            <discipline>
                <name>Cabin</name>
                <parameters>
                    <parameter>
                        <name>nPaxR</name>
                        <description>
							number of pax abreast  
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>nClasses</name>
                        <description>
							Number of Classes 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cargoDeck</name>
                        <description>
							layout for the cargoDeck  
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>refLayout</name>
                        <description>
							defines the critical layout for the cabin design
							is a steering factor for JoeFuMo 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>nRow</name>
                        <description>
							number of seat rows in the cabin 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>nAisle</name>
                        <description>
							number of aisles  
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>refAbreast</name>
                        <description>
							reference number of pax abreast due to number of pax per row and aisles
							needed for JoeFuMo 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
        </disciplines>
    </component>
    <component>
        <name>Htp</name>
        <disciplines>
            <discipline>
                <name>Geometry</name>
                <parameters>
                    <parameter>
                        <name>cMAC</name>
                        <description>
							mean aerodynamic chord of the wing 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>refArea</name>
                        <description>
							description 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>taperRatio</name>
                        <description>
							taper ratio of the wing 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>xMAC</name>
                        <description>
							x location of the mean aerodynamic chord of the wing
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cTip</name>
                        <description>
							tip chord of the Wing
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>phiTE</name>
                        <description>
							trailing edge sweep angle  
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>span</name>
                        <description>
							wing span 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cRoot</name>
                        <description>
							root chord of the wing
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>expArea</name>
                        <description>
							exposed area of the wing 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>xRoot</name>
                        <description>
							Calculates the position of the horizontal tail 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>wetArea</name>
                        <description>
							wetted area of a wing
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>dihedral</name>
                        <description>
							Wing Dihedral Angle 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>zRoot</name>
                        <description>
							zPosition at htp Root
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>yMAC</name>
                        <description>
							wing mean aerodynamic chord's y location
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>phi25</name>
                        <description>
							quarter chord sweep  
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>tcAVG</name>
                        <description>
							average thickness to chord ratio of the wing 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>phiLE</name>
                        <description>
							leading edge sweep of a wing element 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>lHT</name>
                        <description>
							lever for the horizontal tail 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cHT</name>
                        <description>
							horizontal tail volume coefficent 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>aspectRatio</name>
                        <description>
							aspect ratio of a htp 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
            <discipline>
                <name>Aerodynamic</name>
                <parameters>
                    <parameter>
                        <name>cLalpha</name>
                        <description>
							cL depending on alpha 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>formFactor</name>
                        <description>
							form factor for the wing 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cLMAX</name>
                        <description>
							max cL for the wing 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cD0c</name>
                        <description>
							zero lift drag componentwise for the wing  
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>reynoldsNr</name>
                        <description>
							Reynolds number 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cfLAM</name>
                        <description>
							laminar friction coefficient 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>detadalpha</name>
                        <description>
							Change in Eta due to Alpha 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cfTURB</name>
                        <description>
							turbulent friction coefficient 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
            <discipline>
                <name>Mass</name>
                <parameters>
                    <parameter>
                        <name>mHtp</name>
                        <description>
							mass of the horizontal tailplane
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
            <discipline>
                <name>Cog</name>
                <parameters>
                    <parameter>
                        <name>posCoG</name>
                        <description>
							description 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
        </disciplines>
    </component>
    <component>
        <name>Fuel</name>
        <disciplines>
            <discipline>
                <name>Mass</name>
                <parameters>
                    <parameter>
                        <name>mFuelMAX</name>
                        <description>
							Maximum fuel mass 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>mFM</name>
                        <description>
							The mission FuelMass for an Aircraft 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>mFuelRES</name>
                        <description>
							fuel mass for reserve segment
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>mFuelDESCENT</name>
                        <description>
							fuel used in descent segment 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>mFuelCR</name>
                        <description>
							fuel in cruise segment
							#@todo: calc mFuelCR: write documentation 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>mFuelTO</name>
                        <description>
							fuel mass for takeoff
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>mFuelCLIMB</name>
                        <description>
							fuel used in climb segment 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
        </disciplines>
    </component>
    <component>
        <name>Wing</name>
        <disciplines>
            <discipline>
                <name>Cpacs</name>
                <parameters>
                    <parameter>
                        <name>xTip</name>
                        <description>
							x position of the wings tip section 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cKink</name>
                        <description>
							chord at Kink location 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>yFuselage</name>
                        <description>
							y Position of the wing station at Fuselage Intersection
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>xFuselage</name>
                        <description>
							x Position of the wing station at Fuselage Intersection
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>xKink</name>
                        <description>
							x position of the wings kink section 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>zKink</name>
                        <description>
							z Position of the wing station at kink
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>zTip</name>
                        <description>
							z Position of the wing station at tip
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>zFuselage</name>
                        <description>
							z Coordinate of the Wing at Fuselage Intersection 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cFuselage</name>
                        <description>
							chord at Fuselage location 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>yKink</name>
                        <description>
							y Position of the wing station at kink
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
            <discipline>
                <name>Geometry</name>
                <parameters>
                    <parameter>
                        <name>cMAC</name>
                        <description>
							mean aerodynamic chord of the wing 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>refArea</name>
                        <description>
							reference Area of the Wing 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>taperRatio</name>
                        <description>
							taper ratio of the wing 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cTip</name>
                        <description>
							tip chord of the Wing
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>phiTE</name>
                        <description>
							trailing edge sweep angle  
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>span</name>
                        <description>
							wing span 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cRoot</name>
                        <description>
							root chord of the wing
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>expArea</name>
                        <description>
							exposed area of the wing 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>xRoot</name>
                        <description>
							pos is the x position of the root front position 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>wetArea</name>
                        <description>
							wetted area of a wing
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>dihedral</name>
                        <description>
							Wing Dihedral Angle 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>zRoot</name>
                        <description>
							zPosition at wing Root
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>xMAC</name>
                        <description>
							x location of the mean aerodynamic chord of the wing
							@todo: cpacsImport xMAC: implement
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>yMAC</name>
                        <description>
							wing mean aerodynamic chord's y location
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>phi25</name>
                        <description>
							quarter chord sweep 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>tcAVG</name>
                        <description>
							average thickness to chord ratio of the wing 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>phiLE</name>
                        <description>
							leading edge sweep of a wing element 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>aspectRatio</name>
                        <description>
							aspect ratio of a wing 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
            <discipline>
                <name>Mass</name>
                <parameters>
                    <parameter>
                        <name>mWing</name>
                        <description>
							mass for the Wing
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
            <discipline>
                <name>Cog</name>
                <parameters>
                    <parameter>
                        <name>posCoG</name>
                        <description>
							Wings Center of Gravity Location
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
            <discipline>
                <name>Aerodynamic</name>
                <parameters>
                    <parameter>
                        <name>cLalpha</name>
                        <description>
							cL depending on alpha 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>oswald</name>
                        <description>
							calculates the oswald factor for the wing 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>formFactor</name>
                        <description>
							form factor for the wing 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cLMAX</name>
                        <description>
							max cL for the wing 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cD0c</name>
                        <description>
							zero lift drag componentwise for the wing  
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>reynoldsNr</name>
                        <description>
							Reynolds number 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cfLAM</name>
                        <description>
							laminar friction coefficient 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>cfTURB</name>
                        <description>
							turbulent friction coefficient 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
        </disciplines>
    </component>
    <component>
        <name>Payload</name>
        <disciplines>
            <discipline>
                <name>Mass</name>
                <parameters>
                    <parameter>
                        <name>mCargo</name>
                        <description>
							mass of additional cargo 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>posCoG</name>
                        <description>
							Position of the Center of Gravity relative to cMAC
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>mPayload</name>
                        <description>
							Payload mass:Cargo and Passengers and Passenger Luggage 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>paxSeats</name>
                        <description>
							max number of available Seats SingleClass Layout 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>mPax</name>
                        <description>
							mass of all Passengers
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>mSinglePax</name>
                        <description>
							mass of a single passenger and its baggage 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
        </disciplines>
    </component>
    <component>
        <name>Wingrootairfoil</name>
        <disciplines>
            <discipline>
                <name>Aerodynamic</name>
                <parameters>
                    <parameter>
                        <name>clMAX</name>
                        <description>
							the airfoils maximum lift coefficient  
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>aType</name>
                        <description>
							The Airfoil Type 0. for symmetric, 1. for cambered
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>tc</name>
                        <description>
							Thickness to Chord Ratio 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>reynoldsNr</name>
                        <description>
							Reynolds number at this airfoil 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                    <parameter>
                        <name>ctm</name>
                        <description>
							chord position of maximum thickness between 0. and 1. 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
        </disciplines>
    </component>
    <component>
        <name>Systems</name>
        <disciplines>
            <discipline>
                <name>Mass</name>
                <parameters>
                    <parameter>
                        <name>mSystems</name>
                        <description>
							system mass 
                        </description>
                        <value>0.0</value>
                        <factor>1.0</factor>
                    </parameter>
                </parameters>
            </discipline>
        </disciplines>
    </component>
</zeroGuiIn>