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Mil-Mi-8.xml
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Mil-Mi-8.xml
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<?xml version="1.0" encoding="ISO-8859-1"?>
<!--
2011 BARANGER Emmanuel First for test
2011 JM-26 First really R44 FDM
2019 Re-used as Mi8 FDM
2020 improved Mi-8 FDM by Anirudh Prabhu (Raptor)
-->
<!-- #### Specs.
Speed 130 kn , Empty Wt. 15653 Lb (7100Kg) , Gross Wt. 24471 Lb(11100Kg) , Max TO Wt. 28660 Lb (13000Kg)
Max Internal Cargo 8820Lbs (4000Kg) Max external slung cargo 11,023Lbs (5000Kg)
Max Fuel 3700 L (810 imp gl) = 6548 lbs , Range 267 nmi , ferry range 520 nmi
Service Ceiling 16000ft
Engine = Klimov TV3-117, power = 1640kW each , weight =(648Lbs, 294Kg each) , Specific fuel consumption = 0.308 kg/kW/hr (0.507 lb/shp/hr) each.
APU = AI-9V , weight: 65 kg (143 lb)
#### -->
<airplane mass="15653">
<approach speed="47" aoa="16">
<control-setting axis="/controls/engines/engine[0]/throttle" value="0.3"/>
</approach>
<cruise speed="130" alt="0">
<control-setting axis="/controls/engines/engine[0]/throttle" value="1.0"/>
</cruise>
<!-- #### old values nx="0.05" ny="0" nz="1"
fx="0.99" fy="0" fz="-0.043"
rpm="495" my rpm="280"
mincollective="-0.3" maxcollective="14" then 10
airfoil-lift-coefficient="5.67" incidence-stall-zero-speed="31" incidence-stall-half-sonic-speed="19" drag-factor-stall="6.0" stall-change-over="3.5"
airfoil-drag-coefficient0="0.01" airfoil-drag-coefficient1="0.05"
#### -->
<!-- #### aviahelpgroup.ae/supply/main-rotor-blades-8at-2710-00/
Main rotor blades 8AT-2710-00 conforms to the MIL8565J standards
Weight of each blade, not more than: 140 kg
Weight of balancing loads, not more than: 0,6 kg
Static moment relative to rotation axis, kgf/m: 681
#### -->
<!-- #### RPM= 270 old, as per researech document = 193 #### -->
<rotor name="main"
x="1.988" y="0.0" z="2.725"
nx="0" ny="0" nz="1"
fx="1" fy="0" fz="0"
ccw="0"
phi0="45"
maxcollective="9.2"
mincollective="0.0"
mincyclicele="-8.0"
maxcyclicele="8.0"
mincyclicail="-5.5"
maxcyclicail="5.5"
diameter="21.29"
numblades="5"
weightperblade="308"
relbladecenter="0.5"
dynamic="1"
rpm="240"
rellenflaphinge="0.15"
delta3="0.0"
delta=".25"
pitch-a="10"
pitch-b="15"
flapmin="-13.0"
flapmax="13.0"
flap0="-5.0"
flap0factor="0"
notorque="0"
dragfactor="0.30"
translift-ve="20"
translift-maxfactor="1.2"
ground-effect-constant="0.1"
twist="-8.5"
taper="1"
chord="0.678"
number-of-segments="8"
number-of-parts="8"
rel-len-where-incidence-is-measured="0.7"
rel-len-blade-start="0.178"
airfoil-lift-coefficient="3.85"
airfoil-drag-coefficient0="0.0075"
airfoil-drag-coefficient1="0.2500"
incidence-stall-zero-speed="15"
incidence-stall-half-sonic-speed="14.5"
lift-factor-stall="0.18"
stall-change-over="5.5"
drag-factor-stall="2.0"
cyclic-factor="1.0"
rotor-correction-factor="0.9">
<control-input axis="/controls/flight/aileron-trim" control="CYCLICAIL" split="true"/>
<control-input axis="/controls/flight/fcs/roll" control="CYCLICAIL" src0="-1.0" src1="1.0" dst0="-1.0" dst1="1.0"/>
<control-input axis="/controls/flight/elevator-trim" control="CYCLICELE" split="true"/>
<control-input axis="/controls/flight/fcs/pitch" 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>
<!-- #### Old Values rpm="3356" my rpm="850" pitch-a="10" pitch-b="15" #### -->
<!-- #### Weight of each blade = 13 kg (28.66 lbs) length = 1.74m width = 0.273m
Max blade thickness = 2 cm Thickness of handle = 6 cm Source = upstreamfactory.com
pitch-a = -6 (full left pedal) pitch-b = +23 (full right pedal) #### -->
<!-- #### RPM= 980 old, as per researech document = 1124 #### -->
<rotor name="tail"
x="-10.742" y="0.63" z="2.743"
nx="0.0" ny="-1" nz="0.0"
fx="1" fy="0" fz="0"
ccw="1"
maxcollective="24"
mincollective="-11"
diameter="3.91"
numblades="3"
weightperblade="28.66"
relbladecenter="0.55"
dynamic="0.70"
rpm="980"
rellenflaphinge="0.0"
delta3="1"
translift="0" delta="0.8"
pitch-a="10"
pitch-b="15"
airfoil-lift-coefficient="6.4"
airfoil-drag-coefficient0="0.0035"
airfoil-drag-coefficient1="0.10"
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="8"
notorque="0"
taper="1"
chord="0.273"
number-of-segments="5"
number-of-parts="4"
rel-len-blade-start="0.2"
rotor-correction-factor="0.9"
downwashfactor="0.3">
<control-input axis="/controls/flight/fcs/yaw" control="COLLECTIVE" invert="true" src0="-1.0" src1="1.0" dst0="-1.0" dst1="1.0"/>
<control-input axis="/controls/flight/fcs/tail-rotor/throttle" control="COLLECTIVE" src0="-1.0" src1="1.0" dst0="-1.0" dst1="1.0"/>
</rotor>
<!-- Engine: Klimov TV3-117, power: 1,640kW each-->
<rotorgear max-power-engine="3280"
max-power-rotor-brake="300"
rotorgear-friction="0.5"
engine-prop-factor="0.005"
engine-accel-limit="3"
yasimdragfactor="60"
yasimliftfactor="100">
<!--<control-input axis="/controls/engines/engine[0]/magnetos" control="ROTORGEARENGINEON"/>-->
<control-input axis="/engines/engine/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="6.40" y="0.51" z="-0.10"/>
<!-- Fuselage -->
<fuselage ax="7.327" ay="0" az="-0.157" bx="6.755" by="0" bz="-0.157" width="1.52" taper="0.328" midpoint="1"/> <!-- Nose cone area -->
<fuselage ax="6.755" ay="0" az="-0.157" bx="5.647" by="0" bz="-0.157" width="2.07" taper="0.734" midpoint="1"/> <!-- Cockpit area -->
<fuselage ax="5.647" ay="0" az="-0.157" bx="-0.757" by="0" bz="0" width="2.31" taper="0.895" midpoint="1.0"/> <!-- Cargo Compartment area -->
<fuselage ax="-0.312" ay="0" az="-0.075" bx="-2.979" by="0" bz="1.066" width="2.31" taper="0.432" midpoint="0"/> <!-- Rear Cargo area -->
<fuselage ax="-2.772" ay="0" az="1.020" bx="-9.520" by="0" bz="1.171" width="1.0" taper="0.513" midpoint="0"/> <!-- Tail shaft area-->
<fuselage ax="-9.385" ay="0" az="1.254" bx="-10.758" by="0" bz="2.683" width="0.36" taper="1" midpoint="0.5"/> <!-- Tail shaft vertical area-->
<fuselage ax="4.259" ay="0.281" az="1.284" bx="-1.0" by="0.281" bz="1.284" width="0.7" taper="1" midpoint="0.5"/> <!-- Left Engine -->
<fuselage ax="5.038" ay="0.281" az="1.241" bx="4.259" by="0.281" bz="1.284" width="0.7" taper="0.317" midpoint="1"/> <!-- Left Engine Dust Filter -->
<fuselage ax="4.259" ay="-0.281" az="1.284" bx="-1.0" by="-0.281" bz="1.284" width="0.7" taper="1" midpoint="0.5"/> <!-- Right Engine -->
<fuselage ax="5.038" ay="-0.281" az="1.241" bx="4.259" by="-0.281" bz="1.284" width="0.7" taper="0.317" midpoint="1"/> <!-- Right Engine Dust Filter -->
<fuselage ax="3.204" ay="0" az="1.801" bx="0" by="0.158" bz="1.801" width="0.60" taper="1" midpoint="0.5"/> <!-- Oil Cooler Area -->
<fuselage ax="3.065" ay="1.26" az="-0.8" bx="0.899" by="1.26" bz="-0.8" width="0.52" taper="1" midpoint="0.5"/> <!-- Left Saddle Tank area -->
<fuselage ax="3.514" ay="1.26" az="-0.8" bx="3.065" by="1.26" bz="-0.8" width="0.52" taper="0.225" midpoint="1"/> <!-- Left Saddle Tank front cone -->
<fuselage ax="0.899" ay="1.26" az="-0.8" bx="0.425" by="1.26" bz="-0.8" width="0.52" taper="0.225" midpoint="0"/> <!-- Left Saddle Tank rear cone -->
<fuselage ax="4.644" ay="-1.26" az="-0.8" bx="0.899" by="-1.26" bz="-0.8" width="0.52" taper="1" midpoint="0.5"/> <!-- Right Saddle Tank area -->
<fuselage ax="5.198" ay="-1.26" az="-0.8" bx="4.644" by="-1.26" bz="-0.8" width="0.52" taper="0.476" midpoint="1"/> <!-- Right Saddle Tank front cone -->
<fuselage ax="0.899" ay="-1.26" az="-0.8" bx="0.425" by="-1.26" bz="-0.8" width="0.52" taper="0.225" midpoint="0"/> <!-- Right Saddle Tank rear cone -->
<vstab x="-9.636" y="0" z="1.5"
chord="0.6"
length="1.16"
taper="0.54"
sweep="40">
<stall aoa="16" width="4" peak="1.5"/>
</vstab>
<hstab x="-8.0" y="-0.38" z="1.214"
chord="0.816"
length="1.48"
taper="0.612"
dihedral="180">
<stall aoa="0" width="0" peak="1.5"/>
</hstab>
<!-- Nose -->
<!-- #### damp="1.0 spring="1.2" #### -->
<gear x="4.96" y="0" z="-2.09166"
skid="0"
compression="0.1"
spring="1.1"
damp="1.0"
sfric="1.5"
dfric="0.8">
<control-input axis="/controls/flight/rudder" control="STEER" square="true" src0="-1" dst0="-1.0" src1="1" dst1="1.0"/>
<control-output control="STEER" prop="controls/gear/steering"/>
</gear>
<!-- Left -->
<gear x="0.70" y="2.186" z="-1.80386"
skid="0"
compression="0.2"
spring="1.2"
damp="1.0"
sfric="1.5"
dfric="0.8">
<control-input axis="/controls/gear/brake-left" control="BRAKE"/>
<control-input axis="/controls/gear/brake-parking" control="BRAKE"/>
</gear>
<!-- Right -->
<gear x="0.70" y="-2.186" z="-1.80386"
skid="0"
compression="0.2"
spring="1.2"
damp="1.0"
sfric="1.5"
dfric="0.8">
<control-input axis="/controls/gear/brake-right" control="BRAKE"/>
<control-input axis="/controls/gear/brake-parking" control="BRAKE"/>
</gear>
<!-- Tail -->
<gear x="-8.899" y="0" z="-0.05856"
skid="1"
compression="0.01"
spring="0.1"
sfric="1"
dfric="1">
</gear>
<!-- Fuel Tanks -->
<!-- Auxiliary internal tank of 1530Lbs i.e. inside Cargo Cabin is not used -->
<tank x="0.50" y="0" z="1.15" jet="1" capacity="710.0"/> <!-- Service Tank -->
<tank x="1.91" y="1.4" z="-0.87" jet="1" capacity="1993.0"/> <!-- Left Saddle Tank -->
<tank x="1.91" y="-1.4" z="-0.87" jet="1" capacity="1834.0"/> <!-- Right Saddle Tank -->
<weight x="6.48141" y="0.506127" z="-0.175444" mass-prop="/sim/weight[0]/weight-lb"/> <!-- left seat -->
<weight x="6.48141" y="-0.506127" z="-0.175444" mass-prop="/sim/weight[1]/weight-lb"/> <!-- right seat -->
<weight x="2.4" y="0" z="-0.60" mass-prop="/sim/weight[2]/weight-lb"/> <!-- Internal Cargo load -->
<!-- #### <weight x="-1.47" y="0" z="-0.65" mass-prop="/sim/weight[2]/weight-lb"/> #### --> <!-- To be implemented combined Weight of rear cargo doors -->
<!-- Weight of each engine (Klimov TV3-117) 648Lbs, 294Kg -->
<ballast x="3.6" y="0.4" z="1.31" mass="648"/> <!-- Left Engine -->
<ballast x="3.6" y="-0.4" z="1.31" mass="648"/> <!-- Right Engine -->
<ballast x="0.4" y="0.0" z="1.74" mass="143"/> <!-- APU: AI-9V -->
<ballast x="2.0" y="0.0" z="1.38" mass="1856"/> <!-- Main Rotor Gearbox: VR-14 842Kg, 1,856Lbs -->
<ballast x="1.95" y="0.0" z="2.33" mass="269"/> <!-- Swash/Wollbe plate: 8-1950-000 122Kg, 269Lbs -->
<ballast x="-9.45" y="0.0" z="1.2" mass="53.8"/> <!-- Intermediate gearbox: 8?-1515-000 24.4Kg, 53.8Lbs -->
<ballast x="-10.74" y="0.04" z="2.74" mass="129.4"/> <!-- Tail Rotor gearbox: 246-1517-000 58.7Kg, 129.4Lbs -->
<ballast x="6.36" y="0.0" z="-0.15" mass="1800"/> <!-- GUSSED WEIGHT 816Kg 1800Lbs of Panel, Instruments, seats, & other equipment weight in Cockpit. This is done to bring CG below main rotor mast during empty helicopter weight. -->
</airplane>