<!--
Mosquito XE / XEL

Length: Frame 16 ft., Overall 20 ft. Width: 72 in., Height: 84 in.

Rotor Diameter: Main 19.5 ft., Tail 40 in.

Empty Weight XE: 298 lb

Empty Weight XEL: 312 lb

Gross Weight: 610 lbs

Useful (Pilot) Load: 240 lbs.

Fuel Capacity XE: 12 US gallons

Fuel Capacity XEL: 5 US gallons (as required by FAA Part 103, Ultralight Regulations)

Engine: Compact Radial Engines MZ202, 2 cylinder, 2 stroke, rated 64 HP (45kW)

Electrical System: 12 volt DC battery, starter, 180 watt alternator

Rotor Speeds: Main 540 rpm, Tail 2500 rpm

Fuel burn: 4.5 gph

Range: XE: 150 miles/ XEL: 60 miles

Hover in ground effect: 8,000 ft. (estimated)

Hover out of ground effect: 6,500 ft. (estimated)

Max Speed: 80 MPH

 

The FAA has ruled that the maximum speed of 63 mph normally applied to fixed wing ultralights does not apply to helicopters due to their unique power curve.

The FAA increases the weight limit of ultralights to 314 lb for float equipped aircraft. The 312 lb empty weight of the float equipped XEL fits into the ultralight class

 

Mosquito XE3

Length: Frame 16 ft., Overall 20 ft. Width: 72 in., Height: 84 in.

Rotor Diameter: Main 19.5 ft., Tail 40 in.

Empty wt: 360 lb

Gross wt: 720 lb

Useful load: 290 lb

Fuel Capacity: 12 gal

Range: 150 miles

Cruise spd: 80 mph

Max spd: 100+ mph

Fuel burn at cruise: 5 gph
5 gph with 80% power

4500
0,00111 per sec
1/10 sec = 0,0000111
1/40 sec -25 hertz =0,0000111*4

Engine: CRE MZ301 3 cyl 2 cycle

Power 85 hp (64 kw)

Rotor RPM: 590 (main), 2500 (tail)

Hover in ground effect 9500 ft (est)

Hover out of ground effect 7500 ft (est)

 


Mosquito XET

Length: Frame 16 ft., Overall 20 ft. Width: 72 in., Height: 84 in.

Rotor Diameter: Main 19.5 ft., Tail 40 in.

Empty wt: 433 lb

Gross wt: 820 lb

Useful load (with optional aux tank): 240 lb

Useful load (without optional aux tank): 290 lb

Fuel capacity: 12 gal

Aux tank capacity: 8 gal

Range (with aux tank): 160 miles

Cruise spd: 80 mph

Max spd: 100+ mph

Fuel burn at cruise: 8.5 gph

Engine: Solar T62-2A1 turbine

Power: 90 hp

Rotor RPM: 590 (main), 2500 (tail)

Hover in ground effect 9000 ft (est)

Hover out of ground effect 7000 ft (est)

6m rotor
312+180=

rotor1
rotor2
rotor3
rotor4
rotor5
rotor6
rotor7
rotor8
rotor9
rotor10

tail1
tail2
tail3

blades - standard NACA0012 

twist="-7"
-->

  


<airplane mass="500">

    <approach speed="40" aoa="16" fuel="0">
      <control-setting axis="/controls/engines/engine[0]/throttle" value="0.4"/>
    </approach>

    <cruise speed="60" alt="0" fuel="0">
        <control-setting axis="/controls/engines/engine[0]/throttle" value="0.8"/>
    </cruise>
  

    <rotor name="main" x="-0.4" y="0.0" z="1.1" 
    nx="0" ny="0" nz="1.0" fx="1" fy="0" fz="0" ccw="1"
    maxcollective="13" mincollective="0"
    mincyclicele="-9" maxcyclicele="9"
    mincyclicail="-5" maxcyclicail="5"
	 
    diameter="6" numblades="2" weightperblade="25" relbladecenter="0.5"
    dynamic="1" rpm="540" rellenflaphinge="0.1" delta3="0"
    delta=".25"
    pitch-a="10"
    pitch-b="15"
    flapmin="-15"
    flapmax="15"
    flap0="-5"
    phi0="0"
    flap0factor="0"
    notorque="0"
    dragfactor="0.30"
    translift-ve="18"
    translift-maxfactor="1.3"
    ground-effect-constant="0.2"
    twist="0"
    taper="1"
    chord="0.175"
    number-of-segments="8"
    number-of-parts="8"
    rel-len-where-incidence-is-measured="0.7"
    rel-len-blade-start="0.076"
    airfoil-lift-coefficient="6.3"
    airfoil-drag-coefficient0="0.0075"
    airfoil-drag-coefficient1="0.1"
    
    incidence-stall-zero-speed="12.0"
    incidence-stall-half-sonic-speed="6.0"
    lift-factor-stall="0.28"
    stall-change-over="5.5"
    drag-factor-stall="8.0"
    cyclic-factor="0.80"
    rotor-correction-factor="0.95"
    downwashfactor="0.9"
    balance="0.999985"
    >
    <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="-1" dst1="1"/>
    <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>
<!--
 
	 maxcollective="24" mincollective="-26.0"
	 
	 added
		dragfactor="0.30" 
		
		
		 maxcollective="24"
         mincollective="-5"
	 maxcollective="24" mincollective="-10.0"
	 
	  yasimdragfactor="20"
	  
	   maxcollective="17" mincollective="-15.0"
	   o.3 to left (5 points)
	  maxcollective="22" mincollective="-10.0"
	  
	  
	  dragfactor="0.30" 
-->

<rotor name="tail" x="-3.7979" y="0.1611" z="0.5568" 
   nx="0.0" ny="-1" nz="0.0" fx="1" fy="0" fz="0" ccw="1"
   maxcollective="22" mincollective="-10.0"
  diameter="1.0668" numblades="2" weightperblade="2" relbladecenter="0.55"
  dynamic="0.90" rpm="2500" rellenflaphinge="0.0" delta3="1" translift="0" delta="0.7"
  sharedflaphinge="1"
  pitch-a="10"
  pitch-b="15"
  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"
  notorque="0"
  taper="1"
  chord="0.116"
  number-of-segments="5"
  number-of-parts="4"
  rel-len-blade-start="0.2"
  rotor-correction-factor="0.98"
  downwashfactor="0.9"

>
<control-input axis="/controls/flight/rudder" control="COLLECTIVE"
    src0="-1.0" src1="1.0"
    dst0="1.0" dst1="-1.0"/>
    <control-input axis="/controls/flight/rudder-trim" control="COLLECTIVE"
    src0="-1.0" src1="1.0"
    dst0="1.0" dst1="-1.0"/>
</rotor>
<!-- 
airfoil-lift-coefficient="6.5"
  airfoil-drag-coefficient0="0.002"
  airfoil-drag-coefficient1="0.05"
  incidence-stall-zero-speed="15"
  incidence-stall-half-sonic-speed="10.5"
  lift-factor-stall="0.26"
  stall-change-over="5"
	dragfactor="0.30" 
  drag-factor-stall="6.0"
  notorque="0"
  taper="1"
  chord="0.116"
  number-of-segments="5"
  number-of-parts="4"
  rel-len-blade-start="0.2"
  rotor-correction-factor="0.9"
  downwashfactor="0.9"



rel-len-where-incidence-is-measured="0.7"
    rel-len-blade-start="0.076"
    airfoil-lift-coefficient="6.3"
    airfoil-drag-coefficient0="0.0075"
    airfoil-drag-coefficient1="0.1"
    incidence-stall-zero-speed="18.0"
    incidence-stall-half-sonic-speed="9.0"
    lift-factor-stall="0.18"
    stall-change-over="5.5"
    drag-factor-stall="8.0"
    cyclic-factor="0.80"
    rotor-correction-factor="0.95"
    downwashfactor="0.9"

-->

<rotorgear
  max-power-engine="64"
  max-power-rotor-brake="50"
  rotorgear-friction="0.2"
  engine-prop-factor="0.02"
  engine-accel-limit="5"

  yasimdragfactor="15"
  yasimliftfactor="150"
>
	
	<control-input axis="/controls/engines/engine[0]/magnetos" control="ROTORGEARENGINEON"/>
	<control-input axis="/controls/rotor/brake" control="ROTORBRAKE"
		   src0="0.0" src1="1.0"
		   dst0="0.0" dst1="1.0"/>
		   
</rotorgear>



<!--fake engine for sound and consumption

  <engines>
    <engine>
      <rpm type="double">500</rpm>
    </engine>
  </engines>
  
  <control-input axis="/engines/engine[0]/running" control="ROTORGEARENGINEON"/>
	
  
<control-input axis="/controls/rotor/reltarget" control="ROTORRELTARGET"
                 src0="0.0" src1="2.0"
                 dst0="0.0" dst1="2.0"/>
  <control-input axis="/controls/rotor/maxreltorque" control="ROTORENGINEMAXRELTORQUE"
                 src0="0.0" src1="2.0"
                 dst0="0.0" dst1="2.0"/>
	
	
<control-input axis="/controls/engines/engine[0]/magnetos" control="ROTORGEARENGINEON"/>
	
	    <propeller x="-0.6936" y="0" z="-0.009823"
  
             mass="1"
             moment="0.1"
             radius="0.0001"
             cruise-speed="80"
             cruise-rpm="2400"
             cruise-alt="2000"
             cruise-power="1"
             takeoff-power="1"
             takeoff-rpm="3000"
	     contra="1"
	    
	      >
	</propeller>


  
	<piston-engine eng-power="1"
                            eng-rpm="3200"
                            displacement="1" >
		<control-input axis="/controls/engines/engine[0]/throttle" control="THROTTLE"
			src0="0.0" src1="1.0"
			dst0="0.0" dst1="1.0"/>
		<control-input axis="/controls/engines/engine[0]/starter" control="STARTER"/>
		<control-input axis="/controls/engines/engine[0]/magnetos" control="MAGNETOS"/>
	</piston-engine>
  
-->
<!--fake engine
  <jet x="-0.6936" y="0" z="-0.009823"
  mass="1" thrust="1"
   tsfc="53" rotate="0.0" egt="840" spool-time="2"
   n1-idle="0.0" n1-max="100" n2-idle="0.0" n2-max="100">
    <control-input axis="/controls/engines/engine[0]/throttle" control="THROTTLE"
     src0="0.0" src1="1.0"
     dst0="1.0" dst1="0.0"/>
   />
    
    </jet>
-->



<cockpit x="0" y="0" z="0"/>



<fuselage ax="1.0229" ay="0" az="-0.1040"
  bx="-0.7752" by="0" bz="0.5294" idrag="0"
  width="0.6" taper="0.7" midpoint="0.5"
  cy="1.2" cx="1.2"/><!--cabin-->

<fuselage ax="1.0229" ay="0" az="0.4684"
  bx="-0.6512" by="0" bz="0.1448" idrag="0"
  width="0.6" taper="0.7" midpoint="0.5"
  cy="1.2" cx="1.2"/><!--cabin-->

<fuselage ax="-0.55" ay="0" az="0.4730"
  bx="-3.85" by="0" bz="0.5568" idrag="0"
  width="0.22" taper="0.2" midpoint="0.0"/><!--tail boom-->


<vstab x="-3.4" y="0" z="0.5568" taper="0.7" length="0.45" chord="0.2">
  <stall aoa="16" width="4" peak="1.5"/>
</vstab>

<vstab x="-3.4" y="0" z="0.5568" taper="0.7" length="0.45" chord="0.2"
	dihedral="-90">
  <stall aoa="16" width="4" peak="1.5"/>
</vstab>



<!--  


Slows down

<hstab x="-2.9"  y="0" z="0.5568" taper="1.0" effectiveness="2.0" length="0.5" 
	chord="0.2" sweep="0">
  <stall aoa="0" width="0" peak="1.5"/>
</hstab>

<gear x="0.7900" y="0.7510" z="-0.7518" skid="1" compression="0.10"
spring="1.0" damp="0" sfric="0.2" dfric="0.5"
>
  </gear>
 initial-load="0.75"
 
 spring="1.0" damp="0" sfric="0.2" dfric="0.5"
 

 skid="1" 
        compression="0.05"
        spring="1.0" 
        damp="0.2" 
        sfric="0.5" 
        dfric="0.4"
	

<gear x="-1.04" y="+1.20" z="-1.22" skid="1" compression="0.10" spring="0.8" sfric="0.5" dfric="0.4"/>
<gear x="-3.32" y="+1.20" z="-1.18" skid="1" compression="0.10" spring="0.8" sfric="0.5" dfric="0.4"/>


<gear x="-1.04" y="-1.20" z="-1.22" skid="1" compression="0.10" spring="0.8" sfric="0.5" dfric="0.4"/>
<gear x="-3.32" y="-1.20" z="-1.18" skid="1" compression="0.10" spring="0.8" sfric="0.5" dfric="0.4"/>

<gear x="-8.45" y="+0.00" z="-0.03" skid="1" compression="0.01" spring="0.1" sfric="1" dfric="1"/>


	skid="1" compression="0.05" spring="0.8" sfric="0.5" dfric="0.4"
	
	skid="1" compression="0.05" spring="0.8" sfric="0.5" dfric="0.4"
	
	skid="1" compression="0.10" spring="1.0" damp="0" sfric="0.2" dfric="0.5"


 skid="1" compression="0.05" spring="0.7"   damp="10"  sfric="0.8" dfric="0.1"
 
 
 
  skid="1" compression="0.10" spring="1.0" damp="0" sfric="0.2" dfric="0.5"
 skid="1" compression="0.05" spring="0.7"   damp="10"  sfric="0.8" dfric="0.1"

skid="1" compression="0.05" spring="0.8" sfric="0.5" dfric="0.4"

-->



<gear x="0.7900" y="0.7510" z="-0.7518" 
 skid="1" compression="0.05" spring="0.8" sfric="0.5" dfric="0.4"
>
  </gear>

<gear x="0.7900" y="-0.7510" z="-0.7518" 
 skid="1" compression="0.05" spring="0.8" sfric="0.5" dfric="0.4"
>
  </gear>

  
<gear x="-0.8625" y="0.7510" z="-0.7518" 
  skid="1" compression="0.05" spring="0.8" sfric="0.5" dfric="0.4"
>
  </gear>

<gear x="-0.8625" y="-0.7510" z="-0.7518" 
  skid="1" compression="0.05" spring="0.8" sfric="0.5" dfric="0.4"
>
  </gear>


<!-- gear thrusters - "magnets"



<thruster x="0.7900" y="0.7510" z="-0.7518" 
	vx="0" vy="0" vz="-1" thrust="10">
  <control-input axis="gear/gear[0]/wow" src0="0" src1="1" dst0="0" dst1="1" control="THROTTLE"/>
  </thruster>
  
<thruster x="0.7900" y="-0.7510" z="-0.7518" 
	vx="0" vy="0" vz="-1" thrust="10">
  <control-input axis="gear/gear[1]/wow" src0="0" src1="1" dst0="0" dst1="1" control="THROTTLE"/>
  </thruster>
  
  <thruster x="-0.8625" y="0.7510" z="-0.7518" 
	vx="0" vy="0" vz="-1" thrust="10">
  <control-input axis="gear/gear[2]/wow" src0="0" src1="1" dst0="0" dst1="1" control="THROTTLE"/>
  </thruster>
  
  <thruster x="-0.8625" y="-0.7510" z="-0.7518" 
	vx="0" vy="0" vz="-1" thrust="10">
  <control-input axis="gear/gear[3]/wow" src0="0" src1="1" dst0="0" dst1="1" control="THROTTLE"/>
  </thruster>
  
-->

  
<!-- tail rotor guard
skid="1" compression="0.01"
spring="0.1" sfric="1" dfric="1"/
-->
<gear x="-3.6805" y="0.00" z="0.1108" 
skid="1" compression="0.01" spring="0.1" sfric="1" dfric="1"
/>
<gear x="-3.8031" y="0.00" z="0.0" 
skid="1" compression="0.01" spring="0.1" sfric="1" dfric="1"
/>
<gear x="-4.0033" y="0.00" z="0.06448" 
skid="1" compression="0.01" spring="0.1" sfric="1" dfric="1"
/>

<!--main-->
<tank name="Main" x="-0.6936" y="0" z="-0.009823" capacity="72"/>
<!--aux
   CG: x:-0.352, y:0.000, z:0.083

-->
<tank name="Aux" x="-0.352" y="0" z="-0.50" capacity="48"/>



<!-- 
<ballast x="-0.6936" y="0" z="-0.5" mass="180"/>
cog 
x  -0.2708
z  0.1839

<ballast x="-0.0" y="0.0" z="0" mass="40"/>
-->


<!--
pilot
 CG: x:-0.247, y:-0.000, z:0.177
<weight x="0" y="0"  z="0" mass-prop="/sim/weight[0]/weight-lb"/>
x="-0.4" y="0.0" z="0.1" 
-->

<ballast x="-0.6936" y="0" z="0" mass="200"/>

<ballast x="0" y="0" z="0" mass="100"/>


<!--
 CG: x:-0.247, y:-0.000, z:0.177
 

 <rotor name="main" x="-0.4" y="0.0" z="1.1" 

CG should be close to x-0.4 z-0.1

<ballast x="-0.4" y="0.7510" z="0.1" mass="40"/>
<ballast x="-0.4" y="-0.7510" z="0.1" mass="40"/>


<ballast x="-0.4" y="0.1500" z="0.1" mass="40"/>
<ballast x="-0.4" y="-0.1500" z="0.1" mass="40"/>

-->

<ballast x="-0.4" y="0.300" z="0.1" mass="40"/>
<ballast x="-0.4" y="-0.300" z="0.1" mass="40"/>

<!--
<weight n="0">
            <name>Pilot</name>
            <weight-lb>180</weight-lb>
            <max-lb>240</max-lb>
            <min-lb>100</min-lb>
        </weight>

		<weight n="1">
			<name>LeftFGear</name>
			<weight-lb>0</weight-lb>
			<max-lb>100</max-lb>
		</weight>

		<weight n="2">
			<name>LeftRGear</name>
			<weight-lb>0</weight-lb>
			<max-lb>100</max-lb>
		</weight>

		<weight n="3">
			<name>RightFGear</name>
			<weight-lb>0</weight-lb>
			<max-lb>100</max-lb>
		</weight>

		<weight n="4">
			<name>RightRGear</name>
			<weight-lb>0</weight-lb>
			<max-lb>100</max-lb>
		</weight>
		
<weight x="0" y="0"  z="0" mass-prop="/sim/weight[0]/weight-lb"/>

-->


<weight x="0.7900" y="0.7510" z="-0.7518"    mass-prop="/sim/weight[1]/weight-lb"/>
<weight x="0.7900" y="-0.7510" z="-0.7518"   mass-prop="/sim/weight[2]/weight-lb"/>
<weight x="-0.8625" y="0.7510" z="-0.7518"   mass-prop="/sim/weight[3]/weight-lb"/>
<weight x="-0.8625" y="-0.7510" z="-0.7518"  mass-prop="/sim/weight[4]/weight-lb"/>

<!-- settling with power weight 
               CG: x:-0.352, y:0.000, z:0.083
	       
	       
	       in" x="-0.4" y="0.0" z="1.1" 
	       x="-0.352" y="0.0" z="0.083" 
	       
-->

<weight  x="-0.4" y="0.0" z="0.083"  mass-prop="/sim/weight[5]/weight-lb"/>


<!-- 
retreating blade stall
x="-0.4" y="0.0" z="1.1" 

<weight  x="-0.4" y="2.8" z="0.083"  mass-prop="/sim/weight[6]/weight-lb"/>


-->



<!-- 
<thruster x="-0.3" y="0.0" z="1.1"  vx="1" vy="0" vz="0" thrust="4000">
  <control-input axis="/rotors/main/vibration/longitudinal" src0="-1" src1="1" dst0="-1" dst1="1" control="THROTTLE"/>
</thruster>

<thruster x="-0.3" y="0.0" z="1.1"  vx="0" vy="1" vz="0" thrust="4000">
  <control-input axis="/rotors/main/vibration/lateral" src0="-1" src1="1" dst0="-1" dst1="1" control="THROTTLE"/>
</thruster>

-->



</airplane>


              

