Of course, no problem. If you're on linux it's easy. You copy'n'paste that to a file named turboprop.patch in the PC-6 directory. In that directory you simply put
- Code: Select all
patch -i turboprop.patch
in the command line and the patch is applied.
If you're on windows you have to rely on 3rd-party tools, maybe tortoise-svn and the svn patch command. I don't know how this stuff works, though.
But as a last hope it's not so difficult to read the patch file yourself and apply the changes by hand, it's only a few lines. In the patch file there are hints like @@ -13,8 which means that in this file at line 13, something starts to change. You look at the following block and every line that has a "-" in front has to be deleted, each line with a "+" has to be added and each line with " " is unchanged and just for reference. You'll see that most line changes just add or move a few comments or add some additional lines. So with few changes you could produce the new version yourself.
If you don't get this done, here's the entire new yasim file for reference:
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<?xml version="1.0"?>
<!--
************************************************************************
YASim aerodynamic model for Pilatus PC-6 Turbo Porter
allowed CG Range 4.015-4.186
-->
<airplane mass="2940">
<!-- Approach configuration -->
<approach speed="52" aoa="12">
<!--<control-setting axis="/controls/engines/pt6a/power" value="0.3"/>
<control-setting axis="/controls/engines/pt6a/condition" value="1.0"/>-->
<control-setting axis="/controls/engines/engine[0]/throttle" value="0.3" />
<control-setting axis="/controls/engines/engine[0]/condition" value="1" />
<control-setting axis="/controls/flight/flaps" value="1.0"/>
<control-setting axis="/controls/gear/gear-down" value="1"/>
</approach>
<!-- Cruise configuration -->
<cruise speed="140" alt="10000">
<!--<control-setting axis="/controls/engines/pt6a/power" value="1.0"/>
<control-setting axis="/controls/engines/pt6a/condition" value="1.0"/>-->
<control-setting axis="/controls/engines/engine[0]/throttle" value="1" />
<control-setting axis="/controls/engines/engine[0]/condition" value="1" />
<control-setting axis="/controls/flight/flaps" value="0.0"/>
<control-setting axis="/controls/gear/gear-down" value="1"/>
</cruise>
<!-- pilot's eyepoint -->
<cockpit x="-4.495" y="0" z="0.689"/>
<fuselage ax="0.0" ay="0.0" az="-0.0" bx="-11.0" by="0.0" bz="0.3" width="1.4" taper="0.3" midpoint="0.5" />
<!--Main Wing -->
<wing x="-4.475" y="0.618" z="0.821" taper="1.0" incidence="2.0" idrag="1.3" length="7.75" chord="1.9" dihedral="1.0" camber="0.2">
<stall aoa="11" width="8" peak="1.3"/>
<flap0 start="0.0" end="0.43" lift="1.7" drag="1.9"/>
<flap1 start="0.43" end="0.9" lift="1.5" drag="1.1"/>
<control-input axis="/controls/flight/flaps" control="FLAP0"/>
<control-output control="FLAP0" prop="/surface-positions/flap-pos-norm"/>
<control-speed control="FLAP0" transition-time="7"/>
<control-input axis="/controls/flight/aileron" control="FLAP1" split="true"/>
<control-input axis="/controls/flight/aileron-trim" control="FLAP1" split="true"/>
<!--to simulate wing destruction-->
<spoiler start="0" end="1.0" lift="10" drag="0"/>
<control-input axis="/controls/flight/wing_destroyed" control="SPOILER" split="true"/>
</wing>
<hstab x="-10.133" y="0.112" z="0.508" taper="1.0" camber="0.0" length="2.2" chord="1.32" sweep="0" incidence="-2.0">
<stall aoa="16" width="16" peak="1.2"/>
<flap0 start="0.0" end="1.0" lift="1.7" drag="1.7"/>
<control-input axis="/controls/flight/elevator" control="FLAP0"/>
<control-input axis="/controls/flight/elevator-trim" control="FLAP0"/>
<control-output control="FLAP0" prop="/surface-positions/elevator-pos-norm"/>
</hstab>
<!-- rudder has to be able to counteract aileron drag -->
<vstab x="-9.66" y="0" z="0.606" taper="1.0" length="2.0" chord="1.3" sweep="0" >
<stall aoa="15" width="10" peak="1.5"/>
<flap0 start="0" end="1" lift="1.6" drag="1.4"/>
<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" min="1" max="-1"/>
</vstab>
<!--false wing used to simulate beta range of the propeller, which is used to brake in air without reverse the propeller-->
<mstab x="-0.3" y="0" z="0" taper="1" length="1.28" chord="0.2" incidence="0">
<spoiler start="0.0" end="1.0" lift="0" drag="100"/>
<control-input axis="/controls/engines/pt6a/power_beta" control="SPOILER"/>
</mstab>
<!--nasal propeller 2 thrusters to generate "helicoidale" torque-->
<!--<thruster vx="1" vy="0" vz="0.25" x="-0.25" y="-1.0" z="0.0" thrust="1250">
<control-input axis="/controls/engines/pt6a/power" control="THROTTLE"/>
</thruster>
<thruster vx="1" vy="0" vz="-0.25" x="-0.25" y="1.0" z="0.0" thrust="1250">
<control-input axis="/controls/engines/pt6a/power" control="THROTTLE"/>
</thruster> -->
<!--nasal reverse propeller-->
<thruster vx="-1" vy="0.0" vz="0" x="-0.3" y="0.0" z="0.0" thrust="2000">
<control-input axis="/controls/engines/pt6a/power_reverse" control="THROTTLE"/>
</thruster>
<!-- nasal turbo prop ... -->
<propeller x="-0.0" y="0.0" z="0.0" mass="550" moment="42" radius="1.28" cruise-speed="90" cruise-rpm="2000" cruise-power="500" cruise-alt="6000" min-rpm="850" max-rpm="2200">
<turbine-engine eng-power="550" eng-rpm="2200" alt="6000" flat-rating="550" max-n2="90" bsfc="0.46" spool-time="4"/>
<actionpt x="-0.22" y="0.0" z="0.0"/>
<control-input axis="/controls/engines/engine[0]/throttle" control="THROTTLE"/>
<control-input axis="/controls/engines/engine[0]/condition" control="CONDLEVER"/>
<control-input axis="/controls/engines/engine[0]/starter" control="STARTER"/>
<control-input axis="/controls/engines/engine[0]/propeller-pitch" control="ADVANCE"/>
<control-input axis="/controls/engines/engine[0]/propeller-feather" control="PROPFEATHER"/>
</propeller>
<!-- left main -->
<gear x="-3.195" y="1.5" z="-1.65" compression="0.15" spring="1.3" dfric="0.8" sfric ="0.8">
<control-input axis="/controls/gear/brake-left" control="BRAKE"/>
<control-input axis="/controls/gear/brake-parking" control="BRAKE" split="true"/>
</gear>
<!-- right main -->
<gear x="-3.195" y="-1.5" z="-1.65" compression="0.15" spring="1.3" dfric="0.8" sfric ="0.8">
<control-input axis="/controls/gear/brake-right" control="BRAKE"/>
<control-input axis="/controls/gear/brake-parking" control="BRAKE" split="true"/>
</gear>
<!-- Tail wheel -->
<gear x="-10.75" y="0" z="-0.47" compression="0.1" castering="1" dfric="0.6" sfric ="0.4">
<control-input axis="/controls/gear/tailwheel-lock" src0="0" src1="1" dst0="1" dst1="0" control="CASTERING" />
</gear>
<!-- source: http://pilatus-aircraft.com/00-def/main/scripts/ckfinder/userfiles/files/Downloads/Brochures/Pilatus%20Aircraft%20Ltd%20-%20PC-6.pdf -->
<tank x="-4.475" y="3.4" z="0.821" capacity="567.7" jet="true"/> <!-- 515kg total, converted to pounds -->
<tank x="-4.475" y="-3.4" z="0.821" capacity="567.7" jet="true"/>
<weight x="-3.54" y="0.28" z="0" mass-prop="/sim/weight[0]/weight-lb"/>
<weight x="-3.36" y="-0.30" z="-0.24" mass-prop="/sim/weight[1]/weight-lb"/>
<weight x="-4.23" y="0.28" z="-0.13" mass-prop="/sim/weight[2]/weight-lb"/>
<weight x="-4.68" y="0.28" z="-0.13" mass-prop="/sim/weight[3]/weight-lb"/>
<weight x="-5" y="0.28" z="-0.13" mass-prop="/sim/weight[4]/weight-lb"/>
<weight x="-5.49" y="0.28" z="-0.13" mass-prop="/sim/weight[5]/weight-lb"/>
<weight x="-5.92" y="0.28" z="-0.13" mass-prop="/sim/weight[6]/weight-lb"/>
<weight x="-3.96" y="-0.30" z="-0.37" mass-prop="/sim/weight[7]/weight-lb"/>
<weight x="-4.69" y="-0.30" z="-0.37" mass-prop="/sim/weight[8]/weight-lb"/>
<weight x="-5.38" y="-0.30" z="-0.37" mass-prop="/sim/weight[9]/weight-lb"/>
<weight x="-5.90" y="-0.30" z="-0.13" mass-prop="/sim/weight[10]/weight-lb"/>
<!-- to adjust gravity center-->
<ballast x="-10" y="0.0" z="0" mass="340"/> --><!--donne un CG a 4.8 -->
</airplane>
I've basically commented out the two thrusters, re-enabled the turboprop element, fixed the CG because of different mass distribution with an actual engine present, and attached the new engine to the cruise and approach configurations.