<?xml version="1.0" encoding="UTF-8"?>

<!--

Normal rotor speed is 600 rpm with a Vmax of 1000 rpm,
and the blades have been tested up to 4000N static tensile strength,
with a maximum centrifugal load of five tons at 300 rpm in a 3-G pull-up maneuver.

Vne:	95 kts
Max Cruise: 80 kts
Economy Cruise:  70 kts
Best Climb: 52 kts

Rotor Diameter: 7 m
Rotorblade Chord:180 mm
Fuselage Length: 3.5 m
Height: 2.0 m
Wheel Track: 1.7 m
Propeller Diameter: 1.2 m
Rotor Disk Area: 38.5 sqm
Empty Weight: 167 kg
Gross Weight: 290 kg
Max Disc Loading: 7.5 kg/sqm
Max Power Loading: 3.9 kg/hp
Vne: 170 kmh
Max Cruise: 140 kmh
Economy Cruise: 120 kmh
Minimum Speed: 40 kmh
Max ROC: 3 m/s
Service Ceiling (estimated): 4000 m (13000 ft)
Takeoff Run 10 m
Landing Run: 5 m
Range: 250 km

-->

<airplane version="YASIM_VERSION_CURRENT" mass-kg="1.2" mtow-kg="1.6">

  <approach speed="20" aoa="0">
    <control-setting axis="/controls/engines/engine[0]/throttle" value="0.60"/>
  </approach>

  <cruise speed="26" alt="0">
    <control-setting axis="/controls/engines/engine[0]/throttle" value="0.75"/>
  </cruise>

  <rotor name="main"
       x="-0.17" y="0.0" z="0.229"
       nx="0" ny="0" nz="1"
       fx="1" fy="0" fz="0"  ccw="1"
       maxcollective="3.5" mincollective="3.5"
       maxcyclicele="0" mincyclicele="0"
       maxcyclicail="0" mincyclicail="0"
       diameter="0.98"
       numblades="2"
       weightperblade="0.083"
       twist="0"
       chord="0.045"
       rpm="700"
       tiltcenterx="-0.15" tiltcentery="0" tiltcenterz="0.229"
       mintiltpitch=" 2"
       maxtiltpitch="22"
       mintiltroll="-3"
       maxtiltroll="1"
       relbladecenter="0.55"
       dynamic="1"
       sharedflaphinge="0"
       rellenflaphinge="0.0"
       delta3="1"
       delta="0.8"
       pitch-a="6.3"
       pitch-b="6.3"
       flapmin="-8"
       flapmax="8"
       flap0="-3"
       flap0factor="0"
       notorque="0"
       translift-ve="15"
       translift-maxfactor="1"
       ground-effect-constant="0.2"
       taper="1"
       number-of-segments="8"
       number-of-parts="8"
       rel-len-where-incidence-is-measured="0.5"
       rel-len-blade-start="0.125"
  		 airfoil-lift-coefficient="6.8"
  		 airfoil-drag-coefficient0="0.0075"
  		 airfoil-drag-coefficient1="0.325"
  		 airfoil-incidence-no-lift="0"
  		 incidence-stall-zero-speed="15"
  		 incidence-stall-half-sonic-speed="14.5"
  		 lift-factor-stall="0.6"
  		 stall-change-over="10"
  		 drag-factor-stall="1.5"
       cyclic-factor="0.8"
       rotor-correction-factor="0.95"
       downwashfactor="0.0"
       balance="0.999995"
	 >
         <control-input axis="/controls/flight/aileron-trim" control="TILTROLL" split="true" src0="-1.0" src1="1.0" dst0="1.0" dst1="-1.0"/>
         <control-input axis="/controls/flight/aileron" control="TILTROLL" src0="-1.0" src1="1.0" dst0="1.0" dst1="-1.0"/>
         <control-input axis="/controls/flight/elevator-trim" control="TILTPITCH" split="true" src0="-1.0" src1="1.0" dst0="1.0" dst1="-1.0"/>
         <control-input axis="/controls/flight/elevator" control="TILTPITCH" src0="-1.0" src1="1.0" dst0="1.0" dst1="-1.0"/>

 </rotor>
  <rotorgear max-power-engine="0.750"
             max-power-rotor-brake="0.050"
             rotorgear-friction="0.0005"
             engine-prop-factor="0.02"
	           engine-accel-limit="5"
             yasimdragfactor="30"
             yasimliftfactor="140"
	>
  <!-- ROTORGEARENGINEON is unable to handle proportional input (https://sourceforge.net/p/flightgear/flightgear/ci/next/tree/src/FDM/YASim/Rotor.cpp#l1533)-->
 	<control-input axis="/controls/engines/engine[0]/starter" control="ROTORGEARENGINEON"/>
	<control-input axis="/controls/rotor/brake" control="ROTORBRAKE" src0="0.0" src1="1.0" dst0="0.0" dst1="1.0"/>
  </rotorgear>

  <!-- a fixed pitch propeller ommiting the  max-rpm, min-rpm, fine-stop and coarse-stop, the pitch is set by cruise speed and power parameters. -->
  <propeller x="0.02" y="0" z="0.026"
      mass="0.05"
      moment="0.0006"
      radius="0.113"
      cruise-speed="26"
      cruise-rpm="7000"
      cruise-power="0.1"
      cruise-alt="2000"
      takeoff-power="0.2"
      takeoff-rpm="9200"
      contra="1">
	    <actionpt x="0.02" y="0" z="0.026"/>
    	<electric-engine Kv="750" voltage="12" Rm="0.02" >
    		<control-input axis="/controls/engines/engine[0]/throttle" control="THROTTLE"/>
    	</electric-engine>
  </propeller>



 <!-- main fuselage -->
 <fuselage ax="0" ay="0" az="0" bx="-0.62" by="0" bz="0" width="0.2" taper="0" midpoint="0.25"/>
  <!-- main tube -->
 <fuselage ax="0" ay="0" az="0" bx="-0.92" by="0" bz="0" width="0.03" taper="1" midpoint="0.6"/>


  <hstab x="-0.7" y="0.0" z="-0.035"
         incidence="-3"
         taper="1"
         length="0.15"
         chord="0.08"
         sweep="10"
	      dihedral = "0">
	<stall aoa="14" width="4" peak="1.5"/>
  </hstab>

  <vstab x="-0.82" y="0" z="-0.02"
         chord="0.08"
         length="0.17"
         taper="1"
         sweep="13">
         <stall aoa="16" width="4" peak="1.5"/>
         <flap0 start="0.1" end="0.9" lift="1.2" drag="0.8"/>
         <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" min="1" max="-1"/>
  </vstab>

  <!-- two front gears -->

  <gear x="-0.05" y="0.15" z="-0.13"
    spring="0.9"
    damp="0.8"
    dfric="0.9"
    sfric="1.1"
    compression="0.051">
        <control-input axis="/controls/gear/brake-right" control="BRAKE" split="true"/>
        <control-input axis="/controls/gear/brake-parking" control="BRAKE" split="true"/>
  </gear>

  <gear x="-0.05" y="-0.15" z="-0.13"
    spring="0.9"
    damp="0.8"
    dfric="0.9"
    sfric="1.1"
    compression="0.051">
        <control-input axis="/controls/gear/brake-left" control="BRAKE" split="true"/>
        <control-input axis="/controls/gear/brake-parking" control="BRAKE" split="true"/>
  </gear>


  <!-- rear gear -->

  <gear x="-0.83" y="0.0" z="-0.065"
    spring="0.9"
    damp="0.8"
    dfric="0.9"
    sfric="1.1"
    compression="0.051">
        <control-input axis="/controls/flight/rudder" control="STEER" square="true" src0="-1.0" src1="1.0" dst0="-0.3" dst1="0.3"/>
        <control-input axis="/controls/gear/brake-right" control="BRAKE" split="true"/>
        <control-input axis="/controls/gear/brake-parking" control="BRAKE" split="true"/>
  </gear>



<!-- fuel tank for moddeled engine-->
 <!-- <tank x="-0.1" y="0.0" z="-0.05" capacity="0.2"/> -->

<!-- rotor ballast -->
<ballast  x="-0.15" y="0.0" z="0.23" mass-kg="0.1"/>

<!-- body balast -->
<ballast  x="-0.17" y="0.0" z="0.02" mass-kg="0.7"/>



<!-- motor balast -->
<ballast  x="0.01" y="0.01" z="0.03" mass-kg="0.18"/>

<!-- accumulator balast -->
<ballast  x="-0.09" y="0.01" z="0.03" mass-kg="0.15"/>

<!-- tail balast -->
<!-- Toto nastaveni predpoklada ocas v nejblizsi poloze -->
<ballast  x="-0.66" y="0.0" z="-0.003" mass-kg="0.13"/>



<!-- hitch -->
<hitch name="winch" x="0.0" y="0.0" z="0.0">
    <tow length="50" weight-per-meter="0.0035" elastic-constant="40000" break-force="10000"/>
    <!-- 3mm paracord-->
    <winch max-tow-length="1000" min-tow-length="1" initial-tow-length="1000" max-winch-speed="20" power="2" max-force="80"/>
    <control-input axis="/controls/winch/place" control="PLACEWINCH"/>
</hitch>
<hitch name="aerotow" x="0.0" y="0.0" z="0.0" force-is-calculated-by-other="0">
    <tow length="60" weight-per-meter="0.0035" elastic-constant="9000" break-force="100" mp-auto-connect-period="0.0"/>
    <winch max-tow-length="1000" min-tow-length="60" initial-tow-length="60"/>
    <control-input axis="/controls/aerotow/find-aircraft" control="FINDAITOW"/>
</hitch>

</airplane>