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beech-v35.xml
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207 lines (182 loc) · 11.4 KB
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<!-- Beech v35 Bonanza Yasim FDM Configuration -->
<!--
This file is part of FlightGear, the free flight simulator
http://www.flightgear.org/
This program is free software; you can redistribute it and/or
modify it under the terms of the GNU General Public License as
published by the Free Software Foundation; either version 2 of the
License, or (at your option) any later version.
This program is distributed in the hope that it will be useful, but
WITHOUT ANY WARRANTY; without even the implied warranty of
MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE. See the GNU
General Public License for more details.
-->
<!-- Base Data Dwngs: http://forum.flightgear.org/viewtopic.php?f=4&t=22808&hilit=bonanza -->
<!-- Base Data: http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgMakeModel.nsf/ -->
<!-- -->
<!-- V35pp12/53: Max Weight: 3400lb Eng IO520B 484lb 10qt oil 285hp@2700rpm 275hp@2550rpm -->
<!-- Flap 15deg App 30deg Down Ailr Up20 Dn20 Elev Up22.5 Dn19 deg -->
<!-- LH Rudd Up23 Dn26 RH Rudd Up26 Dn23 deg -->
<!-- LH Tail Up44 Dn27 RH Tail Up35 Dn40 deg -->
<!-- Wing Root NACA 23016.5 Tip: 23012 Root Incid 4.0 Tip Incid 1.0 -->
<!-- from NACA 23012 Curve Stall Crit 14.0 Deg C/L Crit: 1.475 CL @ 0 deg: 0.100 -->
<!-- -->
<!-- Opr Weight: 1915lb IO-540: Dry Weight 484lb Guess 45lb Oil + 16lb Acces -->
<!-- MOTW 3400 - ( 545lb Eng, 300lb Fuel, 655lb Psgrs -->
<airplane mass="2295.5" version="YASIM_VERSION_32">
<!-- Approach configuration BaseLine Vs: 55kn Vapp: 1.3 x Vs AOA = AOAcrit/2 Flap 15 -->
<approach speed="55" aoa="8" fuel="0.6">
<control-setting axis="/controls/engines/engine[0]/throttle" value="0.4"/>
<control-setting axis="/controls/engines/engine[0]/mixture" value="1.0"/>
<control-setting axis="/controls/engines/engine[0]/propeller-pitch" value="1.0"/>
<control-setting axis="/controls/flight/flaps" value="0.3"/>
<solve-weight idx="0" weight="170"/>
<solve-weight idx="1" weight="170"/>
<solve-weight idx="2" weight="100"/>
<solve-weight idx="3" weight="100"/>
<solve-weight idx="4" weight="115"/>
</approach>
<!-- Cruise configuration -->
<cruise speed="165" alt="8000" fuel="0.9">
<control-setting axis="/controls/engines/engine[0]/throttle" value="0.7"/>
<control-setting axis="/controls/engines/engine[0]/mixture" value="0.75"/>
<control-setting axis="/controls/engines/engine[0]/propeller-pitch" value="0.75"/>
<control-setting axis="/controls/flight/flaps" value="0.0"/>
<solve-weight idx="0" weight="170"/>
<solve-weight idx="1" weight="170"/>
<solve-weight idx="2" weight="100"/>
<solve-weight idx="3" weight="100"/>
<solve-weight idx="4" weight="115"/>
</cruise>
<!-- Main Wing xyz Half Chord at Root Incid Root: 4 Tip:1 -->
<!-- BaseLine Cmbr (0.100 / 1.475) Wstall Try 8 AOA: (AOAcrit - Wstall/4) -->
<wing x="-2.755" y="0.5" z="-0.53" taper="0.48" incidence="4.00" twist="-3"
length="4.3" chord="2.25" sweep="-2" dihedral="6" camber="0.068" idrag="0.95">
<stall aoa="14" width="4" peak="1.5"/>
<flap0 start="0.00" end="0.54" lift="1.8" drag="1.7"/>
<flap1 start="0.54" end="1.00" lift="1.3" drag="1.2"/>
<control-input axis="/controls/flight/flaps" control="FLAP0"/>
<control-speed control="FLAP0" transition-time="5"/>
<control-input axis="/controls/flight/aileron_in" control="FLAP1" split="true"/>
<control-input axis="/controls/flight/aileron-trim" control="FLAP1" split="true"/>
<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"/>
</wing>
<!-- V-Tail: Conventional stab, vstab replaced with single 30deg dihedral hstab -->
<!-- Elevator is applied similar to conventional -->
<!-- Rudder is applied as "split" to invert action on either side -->
<!-- Rudder is applied as "inverted" to get polrity right, trial and error -->
<!-- /surface-positions/rvator-xxx-pos-norm are output for animations -->
<!-- /surface-positions/rudder-pos-norm is requd for pa-24 action-sim.nas -->
<!-- -->
<!-- From FAA 3A1_Rev_95.pdf -->
<!-- Ailr Limits Up:20 deg Dn: 20deg -->
<!-- Elev Tab Limit Up: 5.5deg Dn: 23deg -->
<!-- Elev Limits Up:22.5deg Dn: 19deg -->
<!-- Rddr Limits LH Up:23 deg Dn: 26deg RH Up:26deg Dn:23deg -->
<!-- Combined Limits LH up:44 deg Dn: 37deg RH Up:35deg Dn:40deg -->
<!-- -->
<!-- Max deflection of 44deg is scaled to 1.0 ctrl input: elevator, rudder summed -->
<!-- Elv-, Up 22.5/44 = 0.511 Elv+, Dn 0.432 Rdr-, Lf 26/44 = 0.591 Rdr+ Rt 0.523 -->
<!-- -->
<!-- Elv Max Up and Rddr Max Right demands 22.5 + 26 = 48.5 RH Down -->
<!-- Rudder demand is limited in AP xml so max demand, above, is scaled to <=35 deg -->
<!-- -->
<!-- Zero for elev axis is offset = -0.0395 Zero offset for rudder axis = -0.034 -->
<!-- -->
<!-- V-Tail HStab -->
<hstab x="-7.0" y="0.0" z="0.31" taper="0.72"
length="1.72" chord="1.06" sweep="0" dihedral="30" camber="0" idrag="1" >
<stall aoa="14" width="4" peak="1.5"/>
<flap0 start="0.05" end="1" lift="2.5" drag="1.7" />
<control-input axis="/controls/flight/elevator-trim"
control="FLAP0"/>
<control-input axis="/controls/flight/elevator_fdm"
control="FLAP0" />
<control-input axis="/controls/flight/rudder_fdm"
control="FLAP0" split="true" invert="true" />
<control-output prop="/surface-positions/elevator-trim"
control="FLAP0" min="-1" max="1"/>
<control-output control="FLAP0" prop="/surface-positions/rvator-left-pos-norm"
min="-1" max="1" invert="true" side="left"/>
<control-output control="FLAP0" prop="/surface-positions/rvator-right-pos-norm"
min="-1" max="1" invert="true" side="right"/>
<control-output control="FLAP0" prop="/surface-positions/rudder-pos-norm"
min="-1" max="1"/>
</hstab>
<!-- IO-520 -->
<propeller radius="1.055"
cruise-speed="180" cruise-rpm="2550"
cruise-alt="11500" cruise-power="275"
takeoff-power="250" takeoff-rpm="2700"
x="-1.00" y="0.0" z="-0.27" mass="540" moment="12"
min-rpm="800" max-rpm="2700"
fine-stop="0.8" coarse-stop="1.77" >
<piston-engine eng-rpm="2700" alt="0" eng-power="285"
displacement="520.0" compression="8.5"/>
<actionpt x="-0.2" y="0.0" z="0.0" />
<control-input control="THROTTLE" axis="/controls/engines/engine[0]/throttle" />
<control-input control="STARTER" axis="/controls/engines/engine[0]/starter" />
<control-input control="MAGNETOS" axis="/controls/engines/engine[0]/magnetos" />
<control-input control="MIXTURE" axis="/controls/engines/engine[0]/mixture" />
<control-input control="ADVANCE" axis="/controls/engines/engine[0]/propeller-pitch"/>
</propeller>
<!-- Nose Gear -->
<gear x="-0.5" y="0" z="-1.43"
upx="-0.1" upy="0" upz="0.9" sfric="0.99" dfric="0.8" retract-time="5"
compression="0.45" spring="1.35" damp="2.4" initial-load="0.4"> <!-- nose -->
<control-input axis="/controls/flight/nose-steer" control="STEER"
src0="-1.0" src1="1.0"
dst0="-1.0" dst1="1.0"/>
<control-input axis="/controls/gear/gear-down" control="EXTEND"/>
<control-speed control="EXTEND" transition-time="5"/>
<control-output control="EXTEND" prop="/gear/gear[2]/position-norm"/>
</gear>
<!-- LH Main Gear -->
<gear x="-2.76" y="1.47" z="-1.215" sfric="0.9" dfric="0.8" retract-time="5"
compression="0.1" spring="1.5" damp="8.8" initial-load="0.0"> <!-- -1.17 left main -->
<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-speed control="EXTEND" transition-time="4.2"/>
<control-output control="EXTEND" prop="/gear/gear[0]/position-norm"/>
</gear>
<!-- RH Main Gear -->
<gear x="-2.76" y="-1.47" z="-1.215" sfric="0.9" dfric="0.8" retract-time="5"
compression="0.1" spring="1.5" damp="8.8" initial-load="0.0"> <!-- -1.17 right main -->
<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-speed control="EXTEND" transition-time="4"/>
<control-output control="EXTEND" prop="/gear/gear[1]/position-norm"/>
</gear>
<!-- Fuel Capacity LBS -->
<tank x="-2.185" y="1.05" z="-0.45" capacity="240" />
<tank x="-2.185" y="-1.05" z="-0.45" capacity="240" />
<!-- Safe CG range: 2.375 to 2.433 for all weights 2900 to 3400 -->
<ballast x="-7.0" y="0" z=".22" mass="-359"/> <!-- Move CG forward to -2.418 -->
<!--ballast x="-7.0" y="0" z=".22" mass="-403"/--> <!-- Move CG forward to -2.433 -->
<!-- Pilot, copilot, left passenger, right passenger, baggage -->
<weight x="-2.17" y="0.33" z="0" mass-prop="/sim/weight[0]/weight-lb"/>
<weight x="-2.17" y="-.33" z="0" mass-prop="/sim/weight[1]/weight-lb"/>
<weight x="-3.04" y="0.33" z="0" mass-prop="/sim/weight[2]/weight-lb"/>
<weight x="-3.04" y="-.33" z="0" mass-prop="/sim/weight[3]/weight-lb"/>
<weight x="-3.64" y="0.00" z="0" mass-prop="/sim/weight[4]/weight-lb"/>
<!-- Pilot's Eye Point -->
<cockpit x="-2.7" y="0.25" z="0.55"/>
<!-- A-B Cowl to WShield Bottom Edge -->
<fuselage ax="-0.42" ay="0" az="-0.17" bx="-1.75" by="0" bz="-0.17"
width="1.10" taper="0.75" midpoint="1.00"/>
<!-- B-C Cabin -->
<fuselage ax="-1.75" ay="0" az="0.08" bx="-2.40" by="0" bz="0.08"
width="1.12" taper="0.6" midpoint="1.00" cx="1.25" cy="1.25" cz="1.0"/>
<!-- C-D Cabin -->
<fuselage ax="-2.40" ay="0" az="0.08" bx="-4.00" by="0" bz="0.08"
width="1.12" taper="0.86" midpoint="0.00" cx="1.25" cy="1.25" cz="1.0"/>
<!-- D-Tail Cone -->
<fuselage ax="-4.00" ay="0" az="0.08" bx="-7.54" by="0" bz="0.16"
width=".96" taper="0.148" midpoint="0" cx="1.25" cy="1.25" cz="1.0"/>
</airplane>