<?xml version="1.0"?>
<!--General characteristics
Engine
Continental R975-46
Fuel
115/145 or 100/130 minimum grade aviation gasoline
Engine limits
Normal Maximum (30 minute limit) 2350 RPM and 39 in. Hg. (475 HP)
Maximum allowable continuous 2350 RPM & 37.5 in.Hg. (450 HP)
Rotor limits and engine
Power Off (Rotor Tach.)
Power On (Engine Tach.)
operating speeds
Maximum 360 r.p.m.
Maximum 2350 r.p.m.
Minimum 230 r.p.m.
Minimum 2100 r.p.m.
Airspeed limits
Vne (never exceed) 75 KIAS
C.G. range
14 in. forward to 5.5 in. aft of datum
Datum
Point midway between rotors
Maximum weight
5500 lb.
Minimum crew
1 (Pilot)
Fuel capacity
150 gal. (900 lb.)
Oil capacity
Engine oil 9.5 gal.
Forward transmission 3.0 quarts
Aft transmission 4.0 quarts

HUP Retriever
SAR & Tranporthubschrauber
Rotorblätter  3/3
  Erstflug  03/1948
  Antriebsart  1 Sternmotor
  Triebwerkstyp  Continental R-975-46A
  Leistung je TW  410 kW  550 hp
  Geschwindigkeit  169 km/h  91 kts
  Leermasse  1.782 kg  3.929 lbs
  max. Startmasse  2.767 kg  6.100 lbs
  Hauptrotordurchmesser  10,67 m  35,0 ft
  Heckrotordurchmesser  10,67 m  35,0 ft
  NACA 0012
  Länge  17,35 m  56,9 ft
  Höhe  3,81 m  12,5 ft
  Daten für  Piasecki HUP-3 (UH-25C)
  Bemerkungen  Gesamtproduktion: 339
-->

<!--Missing most of the right data, however learned and made  from FDM  ch47.xml  and s51.xml both by Maik Justus -->

<airplane mass="5500">

	<!-- Approach configuration -->
	<approach speed="47" aoa="16">
		<control-setting axis="/controls/engines/engine[0]/throttle" value="0.3"/>
		<control-setting axis="/controls/engines/engine[0]/mixture" value="1.0"/>
		<control-setting axis="/controls/flight/flaps" value="1.0"/>
	</approach>

	<!-- Cruise configuration -->
	<cruise speed="80" alt="0">
		<control-setting axis="/controls/engines/engine[0]/throttle" value="1.0"/>
		<control-setting axis="/controls/engines/engine[0]/mixture" value="1.0"/>
		<control-setting axis="/controls/flight/flaps" value="0.0"/>
	</cruise>

        <!-- should be rellenflaphinge="0.025"-->
	<rotor name="main" x="3.748" y="0.0" z="1.1" nx="-0.00" ny="0" nz="1." fx="1" fy="0" fz="0" ccw="0"
		  maxcollective="100" mincollective="-100"
		  mincyclicele="-100" maxcyclicele="100"
		  mincyclicail="-100" maxcyclicail="100"
		  diameter="10.67" numblades="3" weightperblade="90" relbladecenter="0.6"
		  dynamic="1" rpm="329" rellenflaphinge="0.11" delta3="0.5"
		  delta=".25"
		  pitch-a="10"
		  pitch-b="15"
		  flapmin="-15"
		  flapmax="15"
		  flap0="-5"
		  flap0factor="0"
		  notorque="0"
		  dragfactor="0.30"
		  translift-ve="20"
		  translift-maxfactor="1.3"
		  ground-effect-constant="0.1"
		  twist="-8.5"
		  taper="1"
		  chord="0.36"
		  number-of-segments="8"
		  number-of-parts="8"
		  rel-len-where-incidence-is-measured="0.7"
		  rel-len-blade-start="0.17"
		  rotor-correction-factor="0.8"
                airfoil-lift-coefficient="6.3"
                airfoil-drag-coefficient0="0.0075"
                airfoil-drag-coefficient1="0.1"
                incidence-stall-zero-speed="18"
                incidence-stall-half-sonic-speed="9"
                lift-factor-stall="0.18" stall-change-over="5.5"
                drag-factor-stall="8.0"
                cyclic-factor="0.8"
>
		<control-input axis="/controls/flight/rudder" control="CYCLICAIL"
					   src0="-1.0" src1="1.0"
					   dst0="-0.02" dst1="0.02"/>
		<control-input axis="/controls/flight/aileron" control="CYCLICAIL"
					   src0="-1.0" src1="1.0"
					   dst0="-0.02" dst1="0.02"/>
		<control-input axis="/controls/flight/elevator" control="COLLECTIVE"
					   src0="-1.0" src1="1.0"
					   dst0="0.02" dst1="-0.03"/>
		<control-input axis="/controls/engines/engine[1]/throttle" control="COLLECTIVE"
					   src0="-0.0" src1="1.0"
					   dst0="0.12" dst1="0.01"/>
	</rotor>
       <!-- should be rellenflaphinge="0.025"-->
	<rotor name="main2" x="-2.89" y="0.0" z="1.93" nx="-0.00" ny="0" nz="1." fx="1" fy="0" fz="0" ccw="1"
		  maxcollective="100" mincollective="-100"
		  mincyclicele="-100" maxcyclicele="100"
		  mincyclicail="-100" maxcyclicail="100"
		  diameter="10.67" numblades="3" weightperblade="90" relbladecenter="0.6"
		  dynamic="1" rpm="329" rellenflaphinge="0.11" delta3="0.5"
		  delta=".25"
		  pitch-a="10"
		  pitch-b="15"
		  flapmin="-15"
		  flapmax="15"
		  flap0="-5"
		  flap0factor="0"
		  notorque="0"
		  dragfactor="0.30"
		  translift-ve="20"
		  translift-maxfactor="1.3"
		  ground-effect-constant="0.1"
		  twist="-8.5"
		  taper="1"
		  chord="0.36"
		  number-of-segments="8"
		  number-of-parts="8"
		  rel-len-where-incidence-is-measured="0.7"
		  rel-len-blade-start="0.17"
                  rotor-correction-factor="0.8"
                airfoil-lift-coefficient="6.3"
                airfoil-drag-coefficient0="0.0075"
                airfoil-drag-coefficient1="0.1"
                incidence-stall-zero-speed="18"
                incidence-stall-half-sonic-speed="9"
                lift-factor-stall="0.18"
                stall-change-over="5.5"
                drag-factor-stall="8.0"
                cyclic-factor="0.8"

>
		<control-input axis="/controls/flight/rudder" control="CYCLICAIL" invert="true"
					   src0="-1.0" src1="1.0"
					   dst0="-0.02" dst1="0.02"/>
		<control-input axis="/controls/flight/aileron" control="CYCLICAIL"
					   src0="-1.0" src1="1.0"
					   dst0="-0.02" dst1="0.02"/>
		<control-input axis="/controls/flight/elevator" control="COLLECTIVE"
                                           src0="-1.0" src1="1.0"
                                           dst0="-0.03" dst1="0.02"/>
		<control-input axis="/controls/engines/engine[1]/throttle" control="COLLECTIVE"
					   src0="-0.0" src1="1.0"
					   dst0="0.12" dst1="0.01"/>
	</rotor>

        <!--should be max-power-engine="475"-->
	<rotorgear
	  max-power-engine="550"
	  max-power-rotor-brake="100"
	  rotorgear-friction="1.4"
	  engine-prop-factor="0.005"
	  engine-accel-limit="10"

	  yasimdragfactor="16"
	  yasimliftfactor="180"
>

		<control-input axis="/controls/engines/engine[0]/rotorgear" 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="3.79" y="0" z="-0.16"/>

	<fuselage ax="4.83" ay="0" az="-0.33" bx="-4.83" by="0" bz="-0.75"  cx="0.45" cy="1.2" cz="0.5"
          width="1.6" taper="1.6" midpoint="0.5"/>

        <fuselage ax="-2.1" ay="0" az="0.96" bx="-4.83" by="0" bz="0.96"  cx="1.2" cy="1.2" cz="0.5"
          width="1" taper="1" midpoint="0.5"/>


	<vstab x="-2.26" y="0" z="0.90" taper="0.7" length="2." chord="2.5" sweep="40" incidence="0">
		<stall aoa="16" width="4" peak="1.5"/>
	</vstab>




	<!-- left  -->

	<gear x="1.50107" y="-1.4" z="-1.83624"   compression="0.30" spring="8" sfric="1" dfric="0.8" damp="2.5" >
            <control-input axis="/controls/gear/brake-left" control="BRAKE" split="true"/>
            <control-input axis="/controls/gear/brake-parking" control="BRAKE" split="true"/>
        </gear>


	<!-- right  -->

	<gear x="1.50107" y="1.4" z="-1.83624"   compression="0.30" spring="8" sfric="1" dfric="0.8" damp="2.5">
            <control-input axis="/controls/gear/brake-right" control="BRAKE" split="true"/>
            <control-input axis="/controls/gear/brake-parking" control="BRAKE" split="true"/>
        </gear>


        <!--tail-->
	<gear axis="/controls/gear/tailwheel-lock"   src0="0"  src1="1" dst0="0" dst1="0" control="CASTERING"
            x="-3.23" y="+0.00" z="-1.82"   compression="0.20" spring="3" damp="2" sfric="1" dfric="0.8" />




        <!-- Left Door -->
        <gear x="0" y="0" z="0" retract-time="4" compression="0">
        <control-input axis="/controls/engines/engine[0]/rotorgear" control="EXTEND"/>
        <control-speed control="EXTEND" transition-time="4"/>
        <control-output control="EXTEND" prop="/surface-positions/left-door-position"/>
        </gear>

        <!-- Bottom Door -->
        <gear x="0" y="0" z="0" retract-time="4" compression="0">
        <control-input axis="/controls/doors/trapdoor" control="EXTEND"/>
        <control-speed control="EXTEND" transition-time="10"/>
        <control-output control="EXTEND" prop="/surface-positions/trap-position"/>
        </gear>



	<tank x="-0.50" y="0" z="0" capacity="450"/>
	<tank x="-0.50" y="0" z="0" capacity="450"/>


<!-- fuselage     cg from + 0.7646 to   + 0.2893  calculated with midpoint 0.429  and range  +0.3356   -0.1397-->
        <ballast x="2.4" y="0.4" z="-0.4" mass="1000"/>
        <ballast x="-1.2" y="0.4" z="-0.4" mass="1200"/>
         <ballast x="2.4" y="-0.4" z="-0.4" mass="1000"/>
        <ballast x="-1.2" y="-0.4" z="-0.4" mass="1200"/>






<weight x="3.79" y="0"  z="-0.6" mass-prop="/sim/weight[0]/weight-lb"/>	<!-- pilots -->

<weight x="2.46" y="0"  z="-0.6" mass-prop="/sim/weight[1]/weight-lb"/>


</airplane>

