Pilatus PC 12/47 : Adding a livery "Orange", improved dashboard.
[fg:toms-fgdata.git] / Aircraft / PC-12 / pc12-yasim.xml
1 <?xml version="1.0" encoding="ISO-8859-1"?>
2
3 <!-- Pilatus PC12/47 - 2010 Emmanuel BARANGER
4              updated - 2014 Emmanuel BARANGER
5
6      sources          : http://en.wikipedia.org/wiki/Pilatus_PC-12
7
8      wingspan         :  16.23 m ( 53 ft 3 in )
9      length           :  14.40 m ( 47 ft 3 in )
10      height           :   4.26 m ( 14 ft 0 in )
11      empty weight     :  2761 kg ( 5867 lb    )
12      engine           : Pratt & Whitney Canada PT6A-67B or -67P turboprop ( 1217 hp )
13      Maximum speed    :   280 km/h ( 152 kts )
14      Cruise speed     :   500 km/h ( 270 Kts )
15 -->
16
17 <airplane mass="5867">
18
19   <!-- Approach configuration -->
20   <approach speed="120" aoa="2" fuel="0.2">
21     <control-setting axis="/controls/engines/engine[0]/throttle" value="0.2"/>
22     <control-setting axis="/controls/engines/engine[0]/condition" value="1"/>
23     <control-setting axis="/controls/engines/engine[0]/propeller-pitch" value="0.3"/>
24     <control-setting axis="/controls/flight/flaps" value="1"/>
25     <control-setting axis="/controls/gear/gear-down" value="1"/>
26   </approach>
27
28   <!-- Cruise configuration -->
29   <cruise speed="270" alt="0" fuel="0.5">
30     <control-setting axis="/controls/flight/elevator-trim" value="0"/>
31     <control-setting axis="/controls/engines/engine[0]/throttle" value="0.8"/>
32     <control-setting axis="/controls/engines/engine[0]/condition" value="1"/>
33     <control-setting axis="/controls/engines/engine[0]/propeller-pitch" value="0.9"/>
34     <control-setting axis="/controls/flight/flaps" value="0"/>
35     <control-setting axis="/controls/gear/gear-down" value="0"/>
36   </cruise>
37
38   <cockpit x="3.37507" y="0.37523" z="0.28085"/>
39
40   <fuselage ax="6.58961" ay="0" az="-0.463" bx="-5.14686" by="0" bz="-0.0321" width="1.662" taper="0.4" midpoint="0.3"/>
41
42   <wing x="1.18751" y="0.339" z="-1.07958" 
43         chord="2.158" 
44         length="7.138" 
45         taper="0.6"
46         dihedral="6"
47         sweep="-2"
48         camber="0.001">
49         <stall aoa="20" width="1" peak="1.5"/>
50         <flap0 start="0.08" end="0.75" lift="1.1" drag="1.1"/>
51         <flap1 start="0.76" end="1.00" lift="1.2" drag="1.1"/>
52
53         <control-input axis="/controls/flight/flaps" control="FLAP0"/>
54         <control-input axis="/controls/flight/aileron" control="FLAP1" split="true"/>
55         <control-input axis="/controls/flight/aileron-trim" control="FLAP1" split="true"/>
56
57         <control-output control="FLAP0" prop="/surface-positions/flap-pos-norm"/>
58         <control-output control="FLAP1" side="left" prop="/surface-positions/left-aileron-pos-norm"/>
59         <control-output control="FLAP1" side="right" prop="/surface-positions/right-aileron-pos-norm"/>
60
61         <control-speed control="FLAP0" transition-time="2"/>
62   </wing>
63
64   <hstab x="-6.16016" y="0" z="1.95551" 
65          chord="1.266" 
66          length="2.638" 
67          taper="0.7">
68          <stall aoa="18" width="1" peak="1.5"/>
69          <flap0 start="0" end="1" lift="1.2" drag="1.1"/>
70
71          <control-input axis="/controls/flight/elevator" control="FLAP0"/>
72          <control-input axis="/controls/flight/elevator-trim" control="FLAP0"/>
73
74          <control-output control="FLAP0" prop="/surface-positions/elevator-pos-norm"/>
75   </hstab>
76
77   <vstab x="-4.40078" y="0" z="-0.17619" 
78          chord="2.979"
79          length="2.8"
80          taper="0.4"
81          sweep="40">
82          <stall aoa="16" width="1" peak="1.5"/>
83          <flap0 start="0.02" end="0.9" lift="1.2" drag="1.1"/>
84
85          <control-input axis="/controls/flight/rudder" control="FLAP0" invert="true"/>
86          <control-input axis="/controls/flight/rudder-trim" control="FLAP0" invert="true"/>
87
88          <control-output control="FLAP0" prop="/surface-positions/rudder-pos-norm"/>
89   </vstab>
90
91   <!-- Engines   source            : http://en.wikipedia.org/wiki/Pratt_%26_Whitney_Canada_PT6A
92                                    : http://www.pwc.ca/en/engines/pt6a-67b
93
94                  Name              : Pratt & Whitney Canada PT6
95                  Type              : Turboprop
96                  Weight            : 270 lb ( 122.47 kg )
97                  Maximum power     : 1200 hp equivalent power at 2000 output rpm for take-off
98                  Pressure ratio    : 6.3:1
99  
100  
101  gear-ratio="0.66"
102   -->
103   <propeller x="5.61035" y="0.0" z="-0.40130"
104              mass="270" 
105              moment="73.211" 
106              radius="1.35"
107              cruise-speed="270" 
108              cruise-rpm="1500"
109              cruise-power="1000" 
110              cruise-alt="19000"
111              min-rpm="150" 
112              max-rpm="2200"
113              fine-stop="0.25" 
114              coarse-stop="3.0">
115              <actionpt x="6.72862" y="0.0" z="-0.40130"/>
116              <control-input axis="/controls/engines/engine[0]/propeller-pitch" control="ADVANCE"/>
117              <turbine-engine eng-power="1200" 
118                              eng-rpm="2000" 
119                              alt="19000"
120                              flat-rating="1200"
121                              n2-low-idle="32"
122                              n2-high-idle="65"
123                              n2-max="100"
124                              bsfc="0.35">
125                              <control-input axis="/controls/engines/engine[0]/condition" control="CONDLEVER"/>
126                              <control-input axis="/controls/engines/engine[0]/throttle" control="THROTTLE"/>
127              </turbine-engine>
128   </propeller>
129   
130   <!-- Noze wheel -->
131   <gear x="4.68439" y="0" z="-2.02835" 
132         compression="0.15" 
133         spring="0.8"
134         on-solid="1"
135         sfric="1"
136         dfric="1">
137         <control-input axis="/controls/flight/rudder" control="STEER" square="false"/>
138         <control-input axis="/controls/gear/gear-down" control="EXTEND"/>
139         
140         <control-output control="EXTEND" prop="/gear/gear[0]/position-norm"/>
141         
142         <control-speed control="EXTEND" transition-time="7"/>
143   </gear>
144
145   <!-- Left wheel -->
146   <gear x="1.22521" y="-2.24719" z="-2.11304"
147         compression="0.2" 
148         spring="1.8" 
149         damp="0.03" 
150         on-solid="1" >
151         <control-input axis="/controls/gear/brake-left" control="BRAKE"/>
152         <control-input axis="/controls/gear/brake-parking" control="BRAKE"/>
153         <control-input axis="/controls/gear/gear-down" control="EXTEND"/>
154         
155         <control-output control="EXTEND" prop="gear/gear[1]/position-norm"/>
156         
157         <control-speed control="EXTEND" transition-time="7"/>
158   </gear>
159
160   <!-- Right wheel -->
161   <gear x="1.22521" y="2.24719" z="-2.11304"
162         compression="0.2" 
163         spring="1.8"
164         damp="0.03" 
165         on-solid="1" >
166         <control-input axis="/controls/gear/brake-right" control="BRAKE"/>
167         <control-input axis="/controls/gear/brake-parking" control="BRAKE"/>
168         <control-input axis="/controls/gear/gear-down" control="EXTEND"/>
169         
170         <control-output control="EXTEND" prop="gear/gear[2]/position-norm"/>
171         
172         <control-speed control="EXTEND" transition-time="7"/>
173   </gear>
174
175   <tank x="1.58" y=" 2.58" z="-0.85" capacity="1500" />
176   <tank x="2.50" y=" 0.00" z="-1.00" capacity="1500" />
177   <tank x="1.58" y="-2.58" z="-0.85" capacity="1500" />
178
179   <!-- Mass distribution -->
180   <ballast x="6" y="0" z="-1.6" mass="550"/>
181  
182 </airplane>