/
L-39C-yasim.xml
executable file
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/
L-39C-yasim.xml
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<?xml version="1.0"?>
<!--
************************************************************************
Aero Vodochody L-39ZA Albatros - YASIM FDM version 16
Compatible FGFS 2020.3.17
==========================
= YASim solution results =
==========================
Iterations : 1369
Drag Coefficient : 32.357
Lift Ratio : 92.022
Cruise AoA : 0.64 deg
Tail Incidence : -1.68 deg
Approach Elevator : -0.681
CG : x:0.077, y:-0.000, z:-0.496
Wing MAC : (x:0.57, y:1.96), length:1.8
hard limit CG-x : 3.883 m
soft limit CG-x : 0.116 m
CG-x : 0.077 m
CG-x rel. MAC : 27%
soft limit CG-x : 0.024 m
hard limit CG-x : -0.450 m
wing lever : 0.039 m
tail lever : -4.233 m
max thrust : 8.01 kN
thrust/empty : 0.24
thrust/mtow : inf
wing span : 8.05 m
sweep lead. edge : 8.7 .. 8.7 deg
wing area : 12.49 m^2
wing load empty : 276.65 kg/m^2 (Empty 3455 kg)
wing load MTOW : 0.00 kg/m^2 (MTOW 0 kg)
tail span : 3.950 m
tail area : 3.485 m^2
#wing sections: 1
Section 0 base point: x="-0.424" y="0.413" z="-0.823" chord="2.470" incidence="2.0" (at section root in deg)
Inertia tensor [kg*m^2], origo at CG:
8155, -0, 4551
-0, 26281, 0
4551, 0, 31504
************************************************************************
-->
<airplane mass="7341">
<!-- Approach configuration -->
<approach speed="108" aoa="4.5" fuel="0.3">
<control-setting axis="/controls/engines/engine[0]/throttle" value="0.7"/>
<control-setting axis="/controls/flight/flaps" value="1.0"/>
<control-setting axis="/controls/flight/speedbrake" value="0.0"/>
<control-setting axis="/controls/gear/gear-down" value="1"/>
<solve-weight idx="0" weight="0"/>
<solve-weight idx="1" weight="0"/>
</approach>
<!-- Cruise configuration -->
<cruise speed="430" alt="39000" fuel="0.8">
<control-setting axis="/controls/engines/engine[0]/throttle" value="1.0"/>
<control-setting axis="/controls/flight/flaps" value="0.0"/>
<control-setting axis="/controls/gear/gear-down" value="0"/>
<solve-weight idx="0" weight="0"/>
<solve-weight idx="1" weight="0"/>
</cruise>
<cockpit x="2.6902" y="0.0" z="-0.085"/>
<!-- nose -->
<fuselage ax="6.0156" ay="0" az="-1.13131" bx="3.44297" by="0" bz="-0.656159" width="0.954" taper="0.01" midpoint="1.0" cx="0.2" cy="0.5" cz="0.2"/>
<!-- main fuselage -->
<fuselage ax="3.49944" ay="0" az="-0.656159" bx="0.756512" by="0" bz="-0.656159" width="1.06" taper="0.9" midpoint="0.23" cx="0.2" cy="0.5" cz="0.2"/>
<!-- cockpit -->
<fuselage ax="3.91231" ay="0" az="-0.388684" bx="-2.14429" by="0" bz="0.282177" width="1.06" taper="0.1" midpoint="0.23" cx="0.2" cy="0.5" cz="0.2"/>
<!-- intakes -->
<fuselage ax="0.756512" ay="0.0" az="-0.388553" bx="-5.06789" by="0" bz="-0.087978" width="1.56" taper="0.5" midpoint="0.0" cx="0.2" cy="0.5" cz="0.2"/>
<mstab x="0.587868" y="0.211216" z="-1.12649"
taper="1"
incidence="0.25"
length="0.22"
chord="1"
sweep="0"
dihedral="0">
<stall aoa="21" width="8" peak="1.3"/>
<flap0 start="0.0" end="0.15" lift="-2" drag="2.8"/>
<control-input axis="/controls/flight/speedbrake" control="FLAP0"/>
<control-output control="FLAP0" prop="/surface-positions/speedbrake-pos-norm"/>
<control-speed control="FLAP0" transition-time="3.0"/>
</mstab>
<!-- NACA 64A012 -->
<wing x="-0.423783" y="0.413" z="-0.8227"
chord="2.47"
incidence="2.0"
length="3.62"
taper="0.4"
sweep="-3"
dihedral="2.5"
camber="0.02"
effectiveness="1.0"
idrag="1.4">
<stall aoa="13" width="12" peak="1.1"/>
<flap0 start="0.08" end="0.628" lift="1.38" drag="2.4"/>
<flap1 start="0.629" end="0.99" lift="1.24" drag="1.34"/>
<control-input axis="/controls/flight/flaps" control="FLAP0"/>
<control-input axis="/controls/flight/aileron" control="FLAP1" split="true"/>
<control-input axis="/controls/flight/aileron-trim" control="FLAP1" split="true"/>
<control-output control="FLAP0" side="left" prop="/surface-positions/left-flap-pos-norm"/>
<control-output control="FLAP0" side="right" prop="/surface-positions/right-flap-pos-norm"/>
<control-output control="FLAP0" prop="/surface-positions/flap-pos-norm"/>
<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-output control="FLAP1" prop="/surface-positions/aileron-pos-norm"/>
<control-speed control="FLAP0" transition-time="6"/>
<control-speed control="FLAP1" transition-time="0.25"/>
</wing>
<hstab x="-4.37881" y="0.329" z="0.219316"
chord="1.402"
length="1.65"
taper="0.51"
sweep="4"
dihedral="0.0"
effectiveness="1.0"
idrag="1.2">
<stall aoa="20.0" width="10.0" peak="1.05"/>
<flap0 start="0.1" end="1" lift="1.51" drag="1.41"/>
<flap1 start="0.0" end="0.1" lift="1.1" drag="1.1"/>
<control-input axis="/controls/flight/elevator" control="FLAP0" square="false" src0="-0.9" src1="0.9" dst0="-1.0" dst1="1.0"/>
<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="1"/>
<control-input control="FLAP1" axis="/controls/flight/elevator-trim"/>
<control-output control="FLAP1" prop="/surface-positions/elevator-trim-pos-norm"/>
</hstab>
<vstab x="-3.25429" y="0" z="0.282177"
chord="2.220"
length="2.565"
taper="0.35"
sweep="34"
effectiveness="1.0"
idrag="1.4">
<stall aoa="19.0" width="8.0" peak="1.05"/>
<flap0 start="0.2" end="0.86" lift="1.4" drag="1.43"/>
<control-input axis="/controls/flight/rudder" control="FLAP0" invert="true"/>
<control-input axis="/controls/flight/rudder-trim" control="FLAP0" invert="true"/>
<control-output control="FLAP0" prop="/surface-positions/rudder-pos-norm"/>
<control-speed control="FLAP0" transition-time="1"/>
</vstab>
<!-- Engine Ivchenko AI-25TL turbofan -->
<jet x="-1.15" y="0.0" z="-0.150"
mass="770"
thrust="3800"
exhaust-speed="1520"
tsfc="0.575"
egt="933"
spool-time="4">
<actionpt x="-1.93" y="0.0" z="-0.150"/>
<!-- <control-input axis="/controls/engines/engine[0]/throttle" control="THROTTLE"/> -->
<control-input axis="/controls/engines/engine[0]/throttle" control="THROTTLE" src0="0" src1="1" dst0="0.07" dst1="1"/>
</jet>
<!--guns recoil in 2000 Lbf = 2.5Tf negative angle of the gun : -2'-->
<thruster thrust="1000"
x="3.2" y="0.0" z="-1.23"
vx="-0.999390827" vy="0" vz="0.03489949">
<control-input axis="sim/multiplay/generic/int[11]" control="THROTTLE" />
</thruster>
<!-- nose -->
<gear x="3.88256" y="0.0" z="-2.115"
retract-time="7"
compression="0.3"
spring="0.7"
sfric="0.6"
dfric="0.8"
damp="0.44"
castering="1">
<control-input axis="/controls/gear/brake-parking" control="CASTERING" src0="0" src1="1" dst0="1" dst1="0" />
<!-- <control-input axis="/controls/gear/nosewheel-lock" control="CASTERING" src0="0" src1="1" dst0="1" dst1="0" /> -->
<control-input axis="/controls/gear/gear-down" control="EXTEND"/>
<control-output control="EXTEND" prop="/gear/gear[0]/position-norm"/>
<control-speed control="EXTEND" transition-time="7"/>
</gear>
<!-- left main -->
<gear x="-0.45" y="1.941" z="-2.045"
retract-time="7"
compression="0.25"
spring="0.4"
sfric="1.0"
dfric="0.8"
damp="0.48">
<control-input axis="/controls/gear/brake-left" control="BRAKE" split="true"/>
<control-input axis="/controls/gear/brake-parking" control="BRAKE" split="true"/>
<control-input axis="/controls/gear/gear-down" control="EXTEND"/>
<control-output control="EXTEND" prop="gear/gear[1]/position-norm"/>
<control-speed control="EXTEND" transition-time="7"/>
</gear>
<!-- right main -->
<gear x="-0.45" y="-1.941" z="-2.045"
retract-time="7"
compression="0.25"
spring="0.4"
sfric="1.0"
dfric="0.8"
damp="0.48">
<control-input axis="/controls/gear/brake-right" control="BRAKE" split="true"/>
<control-input axis="/controls/gear/brake-parking" control="BRAKE" split="true"/>
<control-input axis="/controls/gear/gear-down" control="EXTEND"/>
<control-output control="EXTEND" prop="gear/gear[2]/position-norm"/>
<control-speed control="EXTEND" transition-time="7"/>
</gear>
<!-- Main fuel system:
5 fuselage tanks (total capacity of 1100 liters (825 kg, 290 gal x6.73 (A-1) =)).
Wingtip tanks: 2 tanks (capacity of 100 liters each, 26 gal).
Max total fuel load: (1200 liters) 975 kg.
-Right wingtip 100l
-Fuselage tank #1 260l
-Fuselage tank #2 365l
-Fuselage tank #3 135l
-Fuselage tank #4 135l
-Fuselage tank #5 205l -feed tank
-Left wingtip 100l
fuel capacity in pounds; 1520kg=3351lb -->
<tank x="0.6839" y="0.0" z="-0.2471" jet="true" capacity="1954.6"/>
<!-- Wing -->
<tank x="0.0" y="4.12806" z="-0.6650" jet="true" capacity="175.24"/>
<tank x="0.0" y="-4.12806" z="-0.6650" jet="true" capacity="175.24"/>
<!-- Drop tanks -->
<tank x="-0.016398" y=" 2.3614" z="-1.17747" jet="true" capacity="278.025"/>
<tank x="-0.016398" y="-2.3614" z="-1.17747" jet="true" capacity="278.025"/>
<ballast x="3.882" y="0.0" z="-1.2081" mass="1620"/>
<!-- External loads -->
<weight x="-0.016398"
y=" 2.3614"
z="-1.17747"
size="0.3"
mass-prop="sim/weight[0]/weight-lb"/>
<weight x="-0.016398"
y="-2.3614"
z="-1.17747"
size="0.3"
mass-prop="sim/weight[1]/weight-lb"/>
</airplane>