<!-- http://www.sijet.com/page727822 -->
<!-- http://www.sijet.com/performance-chart -->
<!-- http://www.sijet.com/download/Sijet_2012_RE-Engining.pdf?inline -->
<!-- https://en.wikipedia.org/wiki/Williams_FJ44 -->
<!-- http://www.williams-int.com/products/fj44-3 -->

<airplane mass="8060">

  <approach speed="106" aoa="7" fuel="0.2">
    <control-setting axis="/controls/engines/engine[0]/throttle-lever" value="0.3"/>
    <control-setting axis="/controls/engines/engine[1]/throttle-lever" value="0.3"/>
    <control-setting axis="/controls/engines/engine[0]/condition" value="1.0"/>
    <control-setting axis="/controls/engines/engine[1]/condition" value="1.0"/>
    <control-setting axis="/controls/flight/flaps" value="1"/>
    <control-setting axis="/controls/gear/gear-down" value="1"/>
    <solve-weight idx="0" weight="117"/>
    <solve-weight idx="1" weight="169"/>
    <solve-weight idx="2" weight="768"/>
    <solve-weight idx="3" weight="0"/>
  </approach>

  <cruise speed="370" alt="43000" fuel="0.87"> <!-- 162 indicated -->
    <control-setting axis="/controls/flight/elevator-trim" value="0.0"/>
    <control-setting axis="/controls/engines/engine[0]/throttle-lever" value="1.0"/>
    <control-setting axis="/controls/engines/engine[1]/throttle-lever" value="1.0"/>
    <control-setting axis="/controls/engines/engine[0]/condition" value="1.0"/>
    <control-setting axis="/controls/engines/engine[1]/condition" value="1.0"/>
    <control-setting axis="/controls/flight/flaps" value="0.0"/>
    <control-setting axis="/controls/gear/gear-down" value="0"/>
    <solve-weight idx="0" weight="117"/>
    <solve-weight idx="1" weight="169"/>
    <solve-weight idx="2" weight="768"/>
    <solve-weight idx="3" weight="0"/>
  </cruise>

  <!-- 15.9m (1674 pixels) wingspan, 105.28 pixels/meter -->
  <!-- 0,0,0 ref point is at the nose -->
  <!-- -X is towards the rear, +Y is left, +Z is up --> 

  <cockpit x="-2.75" y="0.38" z="0.91"/>

  <fuselage ax="0.00" ay="0" az="0" bx="-3.68" by="0" bz="0"
            width="0.95" taper="0.4" midpoint="1.0"/><!--nose-->
  <fuselage ax="-2.66" ay="0" az="0" bx="-4.42" by="0" bz="0"
            width="1.8" taper="1" midpoint="0"/><!--cockpit-->
  <fuselage ax="-4.0" ay="0" az="-0.5" bx="-8" by="0" bz="-0.5"
            width="1.0" taper="1" midpoint="0"/><!--fuselage-->
  <fuselage ax="-8.32" ay="0" az="0.495" bx="-13.73" by="0" bz="0.79"
            width="1.6" taper="0" midpoint="0"/><!--tail cone -->
  <!-- engines --> 
  <fuselage ax="-8.00" ay="-1.29" az="0.786" bx="-9.9" by="-1.290" bz="0.786"
            width="0.88" taper="0.8" midpoint="0.5"/>
  <fuselage ax="-8.00" ay="1.29" az="0.786" bx="-9.9" by="1.290" bz="0.786"
            width="0.88" taper="0.8" midpoint="0.5"/>
  <!--weight/contacts positioning-->
  <fuselage ax="-1.6" ay="-0.35" az="-0.3" bx="-9.34" by="-0.35" bz="-0.3"
            width="0.6" taper="1" midpoint="0.5"/>
  <fuselage ax="-1.6" ay="0" az="-0.3" bx="-9.34" by="0" bz="-0.3"
            width="0.6" taper="1" midpoint="0.5"/>
  <fuselage ax="-1.6" ay="0.35" az="-0.3" bx="-9.34" by="0.35" bz="-0.3"
            width="0.6" taper="1" midpoint="0.5"/>

  <!-- L.E.MAC = -6.177 / 25% = -6.679-->			  
  <wing x="-7.0" y="0.87" z="-0.11" length ="7.10" chord ="2.77"
        sweep="0" dihedral="4" taper="0.34" camber="0.0" incidence="2.5"
        twist="-3.0">
    <stall aoa="15" width="18" peak="1.5"/>
    <flap0 start="0" end=".52" lift="1.5" drag="1.7"/>
    <flap1 start=".52" end=".88" lift="1.2" drag="1.1"/>
    <spoiler start="0.4" end="0.5" lift="0.2" drag="7.0"/>
    <control-input axis="/controls/flight/flaps" control="FLAP0"/>
    <control-speed control="FLAP0" transition-time="7"/>
    <control-output control="FLAP0" prop="/surface-positions/flap-pos-norm"/>
    <control-input axis="/controls/flight/aileron" control="FLAP1" split="true"/>
    <control-input axis="/controls/flight/aileron-trim" control="FLAP1"
                   split="true"/>
    <control-output control="FLAP1" side="left"
                    prop="/surface-positions/left-aileron-pos-norm"/>
    <control-output control="FLAP1" side="right"
                    prop="/surface-positions/right-aileron-pos-norm"/>
    <control-input axis="/controls/flight/speedbrake" control="SPOILER"/>
    <control-output control="SPOILER" prop="/surface-positions/speedbrake-pos-norm"/>
    <control-speed control="SPOILER" transition-time="1"/>
  </wing>

  <hstab x="-12.71" y="0.00" z="1.44" length ="2.98" chord ="1.46"
         sweep="0" dihedral="10" taper="0.53" camber="-0.025" effectiveness="2.0">
    <stall aoa="18" width="3" peak="1.4"/>
    <flap0 start="0" end="1" lift="1.6" drag="1.2"/>
    <control-input axis="/controls/flight/elevator" control="FLAP0"/>
    <control-input axis="/controls/flight/elevator-trim" control="FLAP0"/>
    <control-output control="FLAP0" prop="/surface-positions/elevator-pos-norm"/>
  </hstab>

  <vstab x="-12.58" y="0.00" z="0.97" length ="3.00" chord ="2.33"
         sweep="26" taper="0.46">
    <stall aoa="16" width="4" peak="1.5"/>
    <flap0 start="0" end="1" lift="1.5" drag="1.2"/>
    <control-input axis="/controls/flight/rudder" control="FLAP0" invert="true"/>
    <control-input axis="/controls/flight/rudder-trim" control="FLAP0"
                   invert="true"/>
    <control-output control="FLAP0" prop="/surface-positions/rudder-pos-norm"/>
  </vstab>

  <!-- 2 wet wing tanks 371 US gallons, ~366 US gallons usable each.
       If using Jet A (6.84 lbs/gal)    2537.64lbs, 2504lbs usable
       If using Jet A-1 (6.72 lbs/gal), 2493.12lbs, 2460lbs usable
       Here we must specify the full weight, not the usable weight.
       See Citation-II-set.xml for the unusable capacity.
  --> 
  <tank x="-7.18" y="1.5" z="0.0" capacity="2493.12" jet="true"/>
  <tank x="-7.18" y="-1.5" z="0.0" capacity="2493.12" jet="true"/>
  <tank x="-7.18" y="0" z="0" capacity="0"/>
  
  <gear x="-1.760" y="0.00" z="-0.976" compression=".4" retract-time="7">
    <control-input axis="/controls/flight/rudder" control="STEER" square="true"/>
    <control-input axis="/controls/gear/gear-down" control="EXTEND"/>
    <control-speed control="EXTEND" transition-time="7"/>
    <control-output control="EXTEND" prop="/gear/gear[0]/position-norm"/>
  </gear>

  <gear x="-7.202" y="2.68" z="-1.0" compression=".3" retract-time="7">
    <control-input axis="/controls/gear/brake-left" control="BRAKE"/>
    <control-input axis="/controls/gear/brake-parking" control="BRAKE"/>
    <control-input axis="/controls/gear/gear-down" control="EXTEND"/>
    <control-speed control="EXTEND" transition-time="6.2"/>
    <control-output control="EXTEND" prop="/gear/gear[1]/position-norm"/>
  </gear>

  <gear x="-7.202" y="-2.68" z="-1.0" compression=".3" retract-time="7">
    <control-input axis="/controls/gear/brake-right" control="BRAKE"/>
    <control-input axis="/controls/gear/brake-parking" control="BRAKE"/>
    <control-input axis="/controls/gear/gear-down" control="EXTEND"/>
    <control-speed control="EXTEND" transition-time="6"/>
    <control-output control="EXTEND" prop="/gear/gear[2]/position-norm"/>
  </gear>

  <!-- Williams International FJ44-3 jet engines; NO REVERSERS INSTALLED OR NEEDED -->
  <!-- The n1, n2, thrust, epr numbers are tweaked to achieve the following:
       * at sea level, 0 knots, n1=104%, n2=96%: thrust=2820 lbf
  -->
  <jet x="-9.19" y="1.37"  z="0.76" mass="535" thrust="2963.39" tsfc="0.470" egt="973.15"
       n1-idle="45" n1-max="107" n2-idle="49.0" n2-max="99.8" spool-time="2.5" epr="2.7">
    <control-input axis="/controls/engines/engine[0]/throttle-lever" control="THROTTLE"
                   src0="0.2" dst0="0" src1="1" dst1="1"/>
  </jet>

  <jet x="-9.19" y="-1.37"  z="0.76" mass="535" thrust="2963.39" tsfc="0.470" egt="973.15"
       n1-idle="45" n1-max="107" n2-idle="49.0" n2-max="99.8" spool-time="2.5" epr="2.7">
    <control-input axis="/controls/engines/engine[1]/throttle-lever" control="THROTTLE"
                   src0="0.2" dst0="0" src1="1" dst1="1"/>
  </jet>

  <!-- The <ballast> tag doesn't add weight, but instead specifies the -->
  <!-- distribution of the overall weight. -->
  <!-- target CG is about -6.76 -->
  <ballast x="-12.0" y="0.0" z="2" mass="-1000"/>
  <ballast x="-3.0" y="0.0" z="-0.5" mass="1800"/>

  <!-- The <weight> tags add weight over and above the aircraft empty -->
  <!-- weight and fuel weight.  The sum of these values can be anything -->
  <!-- in the range of 0 to 10400 (max weight) minus 5722 (empty weight) -->
  <!-- minus fuel load.  I.e. the remaining available load for safe -->
  <!-- flying.  So if fuel fraction is 0.8, this sum can be in the range -->
  <!-- of 0 to (10400 - 5722 - 1920 = 2758.)  0 of course would mean -->
  <!-- ghost pilots, so it should be a bit more than that.  -->

  <!-- You can double check total gross weight at flight time by looking -->
  <!-- at /yasim/gross-weight-lbs in the property tree.  It should not ever -->
  <!-- exceed 10400 lbs. -->

  <!-- the /yasim/beech99/*-lbs propertis are initialized in the -->
  <!-- beech99-yasim-set.xml file and can be adjusted at run time. -->
  <weight x="-2.0" y="0" z="-0.5" mass-prop="/sim/weight[0]/weight-lb"/>
  <weight x="-4.0" y="0" z="-0.5" mass-prop="/sim/weight[1]/weight-lb"/>
  <weight x="-6.7" y="0" z="-0.5" mass-prop="/sim/weight[2]/weight-lb"/>
  <weight x="-9.0" y="0" z="-0.5" mass-prop="/sim/weight[3]/weight-lb"/>

</airplane>
