<!--
Robinson R22 Beta II specs:
Weights
Gross Weight 1,370 lb
Empty Weight Equipped (w/full oil) 855 lb
Fuel (19.2 gal) 115 lb
Optional Auxiliary Fuel (10.5 gal) 	63 lb
MAXIMUM PER SEAT WEIGHT: 240 lbs
MINIMUM SOLO WEIGHT: 140 lb 

Powerplant
Lycoming O-360 Four-Cylinder, Air-Cooled
Derated to 131 horsepower at 2652 rpm

Performance
Maximum Airspeed (Vne) 118 mph (102 kts)
Cruise Airspeed @ 70% Power 110 mph (96 kts)
Maximum Range (no reserve) Over 200 miles
Maximum Range (w/aux fuel) Over 300 miles
Average Fuel Consumption 8 to 10 gph
Rate-of-Climb at Sea Level Over 1,000 fpm
Rate-of-Climb at 10,000 Feet Over 600 fpm
Maximum Operating Altitude 14,000 feet
Hover Ceiling IGE @ 1370 GW 9,400 feet

Rotor
18 degree delta3
530 rpm
Airfoil NACA 63-015
teetering hinge ...
-->
<airplane mass="855">

<approach speed="50" aoa="16">
  <control-setting axis="/controls/engines/engine[0]/throttle" value="0.3"/>
</approach>

<cruise speed="102" alt="0">
  <control-setting axis="/controls/engines/engine[0]/throttle" value="1.0"/>
</cruise>


<rotor name="main" x="0.0" y="0.0" z="0.0" nx="0" ny="0" nz="1.0" fx="1" fy="0" fz="0" ccw="1"
  maxcollective="18" mincollective="0.0"
  mincyclicele="-2" maxcyclicele="2"
  mincyclicail="-10" maxcyclicail="10"
  diameter="7.67" numblades="2" weightperblade="15" relbladecenter="0.5"
  dynamic="0.8" rpm="530" rellenflaphinge="0.002" delta3="0.3"
  delta=".15"
  pitch-a="10"
  pitch-b="15"
  flapmin="-7.6"
  flapmax="14.7"
  flap0="-5"
  phi0="0"
  flap0factor="0"
  notorque="0"
  dragfactor="0.30"
  translift-ve="20"
  translift-maxfactor="1.2"
  ground-effect-constant="0.1"
  twist="-8"
  taper="1"
  chord="0.18288"
  number-of-segments="8"
  number-of-parts="8"
  rel-len-where-incidence-is-measured="0.7"
  rel-len-blade-start="0.02"

  airfoil-lift-coefficient="5.5"
  airfoil-drag-coefficient0="0.005"
  airfoil-drag-coefficient1="0.025"
  incidence-stall-zero-speed="19.25"
  incidence-stall-half-sonic-speed="10.5"
  lift-factor-stall="0.26"
  stall-change-over="7"
  drag-factor-stall="9.0"
  cyclic-factor="0.9"
  rotor-correction-factor="0.9"
  downwashfactor="0.25"
>
  <control-input axis="/controls/flight/aileron-trim" control="CYCLICAIL" split="true"/>
  <control-input axis="/controls/flight/aileron" control="CYCLICAIL"
                 src0="-1.0" src1="1.0"
                 dst0="-0.30" dst1="0.20"/>
  <control-input axis="/controls/flight/elevator-trim" control="CYCLICELE"/>
  <control-input axis="/controls/flight/elevator" control="CYCLICELE"
                 src0="-1.0" src1="1.0"
                 dst0="-1.0" dst1="1.0"/>
  <control-input axis="/controls/engines/engine[0]/throttle" control="COLLECTIVE"
                 src0="0.0" src1="1.0"
                 dst0="1.0" dst1="-1.0"/>
</rotor>


<rotor name="tail" x="-4.41" y="-0.2" z="-0.94" nx="0.0" ny="-1" nz="0.0" fx="1" fy="0" fz="0" ccw="1"
  maxcollective="30" mincollective="0"
  diameter="1.0668" numblades="2" weightperblade="2" relbladecenter="0.55"
  dynamic="0.80" rpm="3356" rellenflaphinge="0.01" delta3="1" translift="0" delta="0.5"
  pitch-a="10"
  pitch-b="15"
  airfoil-lift-coefficient="4.0"
  airfoil-drag-coefficient0="0.01"
  airfoil-drag-coefficient1="0.05"
  incidence-stall-zero-speed="19.25"
  incidence-stall-half-sonic-speed="10.5"
  lift-factor-stall="0.26"
  stall-change-over="7"
  drag-factor-stall="9.0"
  notorque="0"
  taper="1"
  chord="0.116"
  number-of-segments="5"
  number-of-parts="4"
  rel-len-blade-start="0.2"
  rotor-correction-factor="0.8"
  downwashfactor="0.3"

>
<control-input axis="/controls/flight/rudder" control="COLLECTIVE" invert="true" 
    src0="-1.0" src1="1.0"
    dst0="-0.7" dst1="0.7"/>
</rotor>


<rotorgear
  max-power-engine="125"
  max-power-rotor-brake="10"
  rotorgear-friction="0.5"
  engine-prop-factor="0.005"
  engine-accel-limit="10"

  yasimdragfactor="10"
  yasimliftfactor="180"
>
  <control-input axis="engines/engine[0]/clutch-engaged" control="ROTORGEARENGINEON"/>
  <control-input axis="/controls/rotor/brake" control="ROTORBRAKE"
                 src0="0.0" src1="1.0"
                 dst0="0.0" dst1="1.0"/>
</rotorgear>


<cockpit x="0.5" y=".33" z="-1.2"/>

<fuselage ax="1.348" ay="0" az="-1.574"
  bx="-0.6" by="0" bz="-1.46" idrag="0"
  width="1.1" taper="0.7" midpoint="0.5"
  cy="1.2" cx="1.2"/><!--cabin-->

<fuselage ax="-0.55" ay="0" az="-1.22"
  bx="-4.308" by="0" bz="-0.928" idrag="0"
  width="0.36" taper="0.2" midpoint="0.0"/><!--tail boom-->

<vstab x="-0.01" y="0" z="-0.540" taper="0.7" length="0.716" chord="0.525">
</vstab>

<fuselage ax="0.065" ay="0" az="-1.57"
  bx="-0.464" by="0" bz="-1.57" idrag="0"
  width="0.7" taper="1.0" midpoint="0.5"/><!--engine-->

<fuselage ax="1.5" ay="-0.918" az="-2.495"
  bx="-0.465" by="-0.918" bz="-2.495" idrag="0"
  width="0.05" taper="1.0" midpoint="0.5"/><!--RH skid-->

<fuselage ax="0.9" ay="-0.427" az="-2.07"
  bx="0.9" by="-0.884" bz="-2.455" idrag="0"
  width="0.05" taper="1.0" midpoint="0.5"/><!--RH skid Frtleg-->

<fuselage ax="-0.365" ay="-0.427" az="-2.07"
  bx="-0.365" by="-0.884" bz="-2.455" idrag="0"
  width="0.05" taper="1.0" midpoint="0.5"/><!--RH skid Rrleg-->

<fuselage ax="1.5" ay="0.918" az="-2.495"
  bx="-0.465" by="0.918" bz="-2.495" idrag="0"
  width="0.05" taper="1.0" midpoint="0.5"/><!--LH skid-->

<fuselage ax="0.9" ay="0.427" az="-2.07"
  bx="0.9" by="0.884" bz="-2.455" idrag="0"
  width="0.05" taper="1.0" midpoint="0.5"/><!--LH skid Frtleg-->

<fuselage ax="-0.365" ay="0.427" az="-2.07"
  bx="-0.365" by="0.884" bz="-2.455" idrag="0"
  width="0.05" taper="1.0" midpoint="0.5"/><!--LH skid Rrleg-->


<vstab x="-4.408" y="0" z="-1.493" taper="1" length="1.06" chord="0.22" effectiveness="0.5">
  <stall aoa="16" width="4" peak="1.5"/>
</vstab>

<gear x="1.5" y="0.92" z="-2.558" skid="1" compression="0.10"
spring="1.0" damp="0.2" sfric="0.5" dfric="0.4">
  </gear>
<gear x="1.5" y="-0.92" z="-2.558" skid="1" compression="0.10"
spring="1.0" damp="0.2" sfric="0.5" dfric="0.4">
  </gear>
<gear x="-0.5" y="0.92" z="-2.558" skid="1" compression="0.10"
spring="1.0" damp="0.2" sfric="0.5" dfric="0.4">
  </gear>
<gear x="-0.5" y="-0.92" z="-2.558" skid="1" compression="0.10"
spring="1.0" damp="0.2" sfric="0.5" dfric="0.4">
  </gear>

<!-- tail rotor guard-->
<gear x="-4.47" y="0.00" z="-1.8" skid="1" compression="0.01"
spring="0.1" sfric="1" dfric="1"/>

<tank x="-0.2185" y="-0.2794" z="-1.8" capacity="115.2"/><!--main-->
<tank x="-0.09652" y="0.2718" z="-1.8" capacity="63"/><!--auxilary-->
<tank x="0" y="0.0" z="-1.7" capacity="0"/>

<weight x="0.5" y="0.27"  z="-1.5" mass-prop="/sim/weight[0]/weight-lb"/><!-- left seat-->
<weight x="0.5" y="-0.236" z="-1.5" mass-prop="/sim/weight[1]/weight-lb"/><!-- right seat-->
<!--
<ballast x="-0.5" y="0.15" z="-1.2" mass="150"/>
<ballast x="-0.5" y="-0.15" z="-1.2" mass="150"/>
<ballast x="0.05" y="0.5" z="-1.5" mass="150"/>
-->
<ballast x="-0.4" y="0" z="-1.3" mass="300"/>
</airplane>