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spitfireVb.xml
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spitfireVb.xml
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<?xml version="1.0"?>
<!--
************************************************************************
YASim aerodynamic model for a Spitfire Vb
Author: Vivian Meazza
Version 1.1
Use latest YASim engine config
The reference datum for measurements is the nose.
************************************************************************
-->
<!-- Weight of everything but fuel (4873 empty) -->
<airplane mass="5732">
<!-- Approach configuration -->
<approach speed="85"
aoa="7"
fuel="0.2">
<control-setting axis="/controls/engines/engine[0]/throttle"
value="0.25"/>
<control-setting axis="/controls/engines/engine[0]/mixture"
value="1.0"/>
<control-setting axis="/controls/engines/engine[0]/propeller-pitch"
value="1"/>
<control-setting axis="/controls/engines/engine[0]/boost"
value="1"/>
<control-setting axis="/controls/flight/flaps"
value="1.0"/>
<control-setting axis="/controls/gear/gear-down"
value="1"/>
<solve-weight idx="0"
weight="200"/>
</approach>
<!-- Cruise configuration -->
<cruise speed="322"
alt="2000"
fuel="0.5">
<control-setting axis="/controls/engines/engine[0]/throttle"
value="1"/>
<control-setting axis="/controls/engines/engine[0]/mixture"
value="1.00"/>
<control-setting axis="/controls/engines/engine[0]/propeller-pitch"
value="1"/>
<control-setting axis="/controls/engines/engine[0]/boost"
value="1"/>
<control-setting axis="/controls/flight/flaps"
value="0.0"/>
<control-setting axis="/controls/gear/gear-down"
value="0"/>
<solve-weight idx="0"
weight="200"/>
</cruise>
<!-- pilot's eyepoint -->
<cockpit x="-3.86"
y="0"
z="0.55"/>
<fuselage
ax="0.0"
ay="0.0"
az="0.0"
bx="-9.13"
by="0.0"
bz="0.0"
width="1.0"
taper="0.38"
midpoint="0.35"
/>
<!--
NACA airfoil section 2213
stall aoa not available
flap drag not available
-->
<wing
x="-2.99"
y="0.77"
z="-0.81"
taper="0.3"
incidence="2.0"
twist="-2.0"
length="4.580"
chord="2.845"
sweep="0"
camber="0.0569"
dihedral="6"
effectiveness="1.3">
<stall aoa="24"
width="4"
peak="1.5"/>
<flap0 start="0.00"
end="0.437"
lift="1.4"
drag="1.5"/>
<flap1 start="0.437"
end="0.90"
lift="1.25"
drag="1.45"/>
<spoiler start="0.00"
end="1"
lift="0.01"
drag="20"/>
<control-input axis="/systems/pneumatic/outputs/flaps"
control="FLAP0"/>
<control-output control="FLAP0"
prop="/surface-positions/flap-pos-norm"/>
<control-speed control="FLAP0"
transition-time="10"/>
<control-input axis="/controls/flight/aileron"
control="FLAP1"
split="true"/>
<control-output control="FLAP1"
side="left"
prop="surface-positions/left-aileron-pos-norm"/>
<control-output control="FLAP1"
side="right"
prop="surface-positions/right-aileron-pos-norm"/>
<control-speed control="FLAP1"
transition-time="1"/>
<control-input axis="controls/flight/wing-fold"
control="SPOILER"/>
<control-output control="SPOILER"
prop="/surface-positions/wing-fold-pos-norm"/>
<control-speed control="SPOILER"
transition-time="5"/>
</wing>
<!-- tailplane -->
<hstab
x="-8.22"
y="0.25"
z="0.0"
taper="0.639"
effectiveness="1.25"
length="1.215"
chord="1.246"
sweep="5" >
<stall aoa="22"
width="4"
peak="1.5"/>
<flap0 start="0.0"
end="1"
lift="1.5"
drag="1.5"/>
<control-input axis="/controls/flight/elevator"
control="FLAP0"
square="true"/>
<control-input axis="/controls/flight/elevator-trim"
control="FLAP0"/>
<control-output control="FLAP0"
prop="/surface-positions/elevator-pos-norm"/>
<control-speed control="FLAP0"
transition-time="0.75"/>
</hstab>
<!-- tail -->
<vstab x="-8.52"
y="0"
z="-0.29"
taper="0.386"
effectiveness="1.25"
incidence="-0.25"
length="1.65"
chord="0.994"
sweep="5" >
<stall aoa="20"
width="4"
peak="1.5"/>
<flap0 start="0"
end="1"
lift="1.5"
drag="1.5"/>
<control-input axis="/controls/flight/rudder"
control="FLAP0"
invert="true"
square="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"/>
<control-speed control="FLAP0"
transition-time="0.75"/>
</vstab>
<!-- stub wing left -->
<vstab x="-2.99"
y="0.32"
z="-0.81"
taper="0"
incidence="-2"
twist="0"
chord="2.845"
sweep="0"
camber="0.0569"
dihedral="90"
length="0.503" >
<stall aoa="15"
width="4"
peak="1.5"/>
<flap0 start="0.00"
end="1"
lift="1.4"
drag="1.6"/>
<control-input axis="/systems/pneumatic/outputs/flaps"
control="FLAP0"/>
<control-output control="FLAP0"
prop="/surface-positions/flap-pos-norm[1]"/>
<control-speed control="FLAP0"
transition-time="10"/>
</vstab>
<!-- stub wing right -->
<vstab x="-2.99"
y="-0.32"
z="-0.81"
taper="0"
incidence="-2"
twist="0"
chord="2.845"
sweep="0"
camber="0.0569"
dihedral="-90"
length="0.503" >
<stall aoa="15"
width="4"
peak="1.5"/>
<flap0 start="0.00"
end="1"
lift="1.4"
drag="1.6"/>
<control-input axis="/systems/pneumatic/outputs/flaps"
control="FLAP0"/>
<control-output control="FLAP0"
prop="/surface-positions/flap-pos-norm[2]"/>
<control-speed control="FLAP0"
transition-time="10"/>
</vstab>
<!-- radiator 'wing' right -->
<vstab x="-3.17377"
y="-0.51"
z="-1.02"
taper="0"
incidence="0"
twist="0"
chord="1.114"
sweep="0"
camber="0.0"
dihedral="-84"
length="0.63" >
<stall aoa="20"
width="4"
peak="1.5"/>
<flap0 start="0.00"
end="1"
lift="1.4"
drag="1.6"/>
<control-input axis="/controls/engines/engine/cowl-flaps-norm"
control="FLAP0"
src0="0"
src1="1"
dst0="0.0"
dst1="0.25"/>
<control-output control="FLAP0"
prop="/engines/engine/cowl-flaps-norm"/>
<control-speed control="FLAP0"
transition-time="3" />
</vstab>
<!-- propeller and engine -->
<!-- moment = radius(m)* propeller mass(kg)/2 - equation provided by Andy Ross -->
<!-- cruise-rpm documented gear ratio of 0.477 min-rpm="1500" max-rpm="3000"
gear-ratio = "0.477" moment = 37.15-->
<propeller x="-1.42"
y="0"
z="-0.25"
mass="2055"
moment="80"
radius="1.638"
cruise-speed="322"
cruise-rpm="1431"
cruise-power="1440"
cruise-alt="20000"
min-rpm="715"
max-rpm="1431"
gear-ratio="0.477"
>
<actionpt x="-0.38"
y="0"
z="0"/>
<control-input axis="/controls/engines/engine[0]/propeller-pitch"
control="ADVANCE"/>
<piston-engine
eng-power="1210"
eng-rpm="3000"
displacement="1649"
compression="6"
turbo-mul="3.15"
wastegate-mp="62.5"
supercharger="1"
>
<control-input axis="/controls/engines/engine[0]/throttle"
control="THROTTLE"/>
<control-input axis="/controls/engines/engine[0]/boost-control"
src0="-1"
src1="1"
dst0="-1"
dst1="1"
control="THROTTLE"/>
<control-input axis="/controls/engines/engine[0]/starter"
control="STARTER"/>
<control-input axis="/controls/engines/engine[0]/magnetos"
control="MAGNETOS"/>
<control-input axis="/controls/engines/engine[0]/mixture"
control="MIXTURE"/>
<control-input axis="/controls/engines/engine[0]/boost"
control="BOOST"/>
</piston-engine>
</propeller>
<!-- simulate cannon recoil -->
<thruster x="-3.5"
y="0"
z="0.4"
vx="-1"
vy="0"
vz="0.15"
thrust="2000">
<control-input axis="/sim/ai/recoil"
control="THROTTLE"
src0="0"
src1="1"
dst0="0"
dst1="1"/>
</thruster>
<thruster x="-3.5"
y="0"
z="0.4"
vx="1"
vy="0"
vz="-0.15"
thrust="1000">
<control-input axis="/sim/ai/runout"
control="THROTTLE"
src0="0"
src1="1"
dst0="0"
dst1="1"/>
</thruster>
<!-- left main spring="0.7" damp="3.0" transition-time="1"-->
<gear
x="-2.20"
y="0.87"
z="-2.00"
compression="0.25"
upx="-0.31"
upy="-0.07"
upz="0.95"
>
<control-input axis="/systems/pneumatic/outputs/brake"
control="BRAKE"
src0="0"
src1="1"
dst0="0"
dst1="0.9"/>
<control-speed control="BRAKE"
transition-time="0.5"/>
<!--<control-input axis="/controls/gear/brake-parking"
control="BRAKE"/>-->
<control-input axis="/controls/gear/chock-left"
control="BRAKE" />
<control-input axis="/systems/hydraulic/outputs/gear"
control="EXTEND"/>
<control-speed control="EXTEND"
transition-time="9"/>
<control-output control="EXTEND"
prop="/gear/gear/position-norm"/>
</gear>
<!-- right main spring="0.7" damp="3.0" transition-time="1"-->
<gear
x="-2.20"
y="-0.87"
z="-2.00"
compression="0.25"
upx="-0.31"
upy="0.07"
upz="0.95"
>
<control-input axis="/systems/pneumatic/outputs/brake[1]"
control="BRAKE"
src0="0"
src1="1"
dst0="0"
dst1="0.9"/>
<control-speed control="BRAKE"
transition-time="0.5"/>
<!--<control-input axis="/controls/gear/brake-parking"
control="BRAKE"/>-->
<control-input axis="/controls/gear/chock-right"
control="BRAKE"/>
<control-input axis="/systems/hydraulic/outputs/gear[1]"
control="EXTEND"/>
<control-speed control="EXTEND"
transition-time="7"/>
<control-output control="EXTEND"
prop="/gear/gear[1]/position-norm"/>
</gear>
<!-- Tail wheel -->
<!-- tail wheel casters freely in Spitfire -->
<gear x="-8.48"
y="0"
z="-0.66"
compression="0.15"
castering="1">
<control-input axis="/controls/gear/tailwheel-lock"
src0="0"
src1="1"
dst0="1"
dst1="0"
control="CASTERING"/>
</gear>
<!-- Canopy -->
<gear x="-3.90"
y="0.0"
z="0.7"
compression="1">
<control-input axis="/controls/flight/canopy-slide"
control="EXTEND"/>
<control-speed control="EXTEND"
transition-time="2"/>
<control-output control="EXTEND"
prop="/gear/canopy/position-norm"/>
</gear>
<!-- Hook - the hook extends only - it has no retracting mechanism
<hook x="-5.91"
y="0.0"
z="-0.60"
length="1.416"
down-angle="55"
up-angle="-5">
<control-input axis="/controls/gear/tailhook"
control="HEXTEND"/>
<control-speed control="HEXTEND"
transition-time="5"/>
</hook>-->
<!-- Launch-bar
Note: the Seafire was not fitted with a catpult launch-bar - it used a catapult strop,
if at all. It usually did a free take-off.
the launch-bar is included here as a workable substitute.
<launchbar x="-2.30"
y="0.0"
z="-1.25"
length="1.0">
<control-input axis="/controls/gear/launchbar"
control="LEXTEND"/>
<control-speed control="LEXTEND"
transition-time="1"/>
</launchbar>-->
<!-- Fuselage tanks.
Weight of contents calculated using 100 octane AVGAS density of 695 kg/m3 @ 15degC
-->
<tank x="-2.80"
y="0"
z="0.17"
capacity="335"/>
<!-- upper 48 imp gals -->
<tank x="-2.56"
y="0"
z="-0.45"
capacity="258"/>
<!-- lower 37 imp gals -->
<!-- ballast and weights -->
<!-- cockpit, radio, oxygen tanks etc. -->
<ballast x="-4.3"
y="0"
z="-0.3"
mass="500"/>
<!-- 5 x 17.5 lbs lead ballast weights fitted in tail -->
<ballast x="-8.50"
y="0"
z="-0.15"
mass="87.5"/>
<!-- armament -->
<ballast x="-2.39"
y="2.17"
z="-0.60"
mass="184"/>
<ballast x="-2.39"
y="-2.17"
z="-0.60"
mass="184"/>
<ballast x="-2.70"
y="3.10"
z="-0.48"
mass="60"/>
<ballast x="-2.70"
y="-3.10"
z="-0.48"
mass="60"/>
<ballast x="-2.75"
y="3.80"
z="-0.57"
mass="60"/>
<ballast x="-2.75"
y="-3.80"
z="-0.57"
mass="60"/>
<!--Oil Cooler-->
<ballast x="-3.0"
y="2.07"
z="-0.88"
mass="4.0"/>
<!-- pilot -->
<weight x="-3.95"
y="0"
z="-0.2"
mass-prop="/yasim/spitfire/pilot-lb"/>
<!-- armament -->
<weight x="-2.39"
y="2.17"
z="-0.60"
mass-prop="/yasim/weights/ammo-lb[0]"/>
<weight x="-2.39"
y="-2.17"
z="-0.60"
mass-prop="/yasim/weights/ammo-lb[1]"/>
<weight x="-2.70"
y="3.10"
z="-0.48"
mass-prop="/yasim/weights/ammo-lb[2]"/>
<weight x="-2.70"
y="-3.10"
z="-0.48"
mass-prop="/yasim/weights/ammo-lb[3]"/>
<weight x="-2.75"
y="3.80"
z="-0.57"
mass-prop="/yasim/weights/ammo-lb[4]"/>
<weight x="-2.75"
y="-3.80"
z="-0.57"
mass-prop="/yasim/weights/ammo-lb[5]"/>
</airplane>