JSBSim change:
[fg:toms-fgdata.git] / Aircraft / c172 / c172.xml
1 <FDM_CONFIG NAME="c172" VERSION="1.57">
2 <!--
3
4   File:        c172.xml
5   Author:      Tony Peden
6   CVS Version: $Id$
7
8   Function: Models a Cessna 172
9   Notes:    Try running FlightGear using this command line,
10             fgfs --fdm=jsb --aircraft=c172
11 -->
12
13   <METRICS>
14     <!--
15     // Wing area (ft^2)
16     // Wing span (ft)
17     // Wing avg. chord (ft)
18     // H. Tail Area (ft^2)
19     // Wing MAC to H.Tail MAC (ft)
20     // V. Tail Area (ft^2)
21     // Wing MAC to V.Tail MAC (ft)
22     // Ixx
23     // Iyy
24     // Izz
25     // Ixz
26     // Empty weight
27     // Center of gravity location, empty weight, in aircraft's own structural coord
28     //   system. X, Y, Z, in inches
29     // Pilot's eyepoint location, in aircraft's own coord system, FROM cg.
30     //  X, Y, Z, in inches
31     AC_AERORP   43.2  0.0    59.4
32     -->
33
34     AC_WINGAREA  174   <!-- square feet -->
35     AC_WINGSPAN  35.8  <!-- ft          -->
36     AC_CHORD     4.9   <!-- ft          -->
37     AC_HTAILAREA 21.9  <!-- square feet -->
38     AC_HTAILARM  15.7  <!-- ft          -->
39     AC_VTAILAREA 16.5  <!-- square feet -->
40     AC_LV        15.7  <!-- ft          -->
41     AC_IXX    948
42     AC_IYY    1346
43     AC_IZZ    1967
44     AC_IXZ    0
45     AC_EMPTYWT   1700
46     AC_AERORP    43.2  0.0 59.4
47     AC_CGLOC     41.0  0.0 36.5
48     AC_POINTMASS 180.0 36.0 -14.0 24.0
49     AC_EYEPTLOC  37.0  0.0 48.0
50     AC_ALPHALIMITS -0.087 0.28
51
52   </METRICS>
53
54   <UNDERCARRIAGE>
55
56     <!--
57     The gear parameters that can be specified are as follows, IN ORDER OF APPEARANCE:
58
59     AC_GEAR
60     <name>                           name of gear entry - no spaces allowed
61     <X> <Y> <Z>                      Gear location in aircraft body coords in inches
62     <spring constant>                spring constant in lbs/ft
63     <damping coefficient>            damping coefficient in lbs/ft/sec
64     <dynamic friction coefficient>   Self-explanatory: sliding friction coefficient
65     <static friction coefficient>    Self-explanatory: "onset" friction coefficient
66     <rolling friction coefficient>   Self-explanatory: rolling friction coefficient
67     <steerability attribute>         One of <STEERABLE | FIXED | CASTERED>
68     <brake group membership>         One of <LEFT | CENTER | RIGHT | NOSE | TAIL | NONE>
69     <max steer angle>                Maximum steerable angle in degrees
70     <retraction attribute>           <RETRACT | FIXED>
71     -->
72
73      AC_GEAR  NOSE        -6.8   0.0 -20.0  1800  600  0.5  0.8 0.02 STEERABLE NONE 20 FIXED
74      AC_GEAR  LEFT_MAIN   58.2 -43.0 -17.9  5400 1600  0.5  0.8 0.02 CASTERED  LEFT  0 FIXED
75      AC_GEAR  RIGHT_MAIN  58.2  43.0 -17.9  5400 1600  0.5  0.8 0.02 CASTERED  RIGHT 0 FIXED
76      AC_GEAR  TAIL_SKID  188.0  0.0    8.0 20000 1000  0.2   0.2 0.2  FIXED NONE 0 FIXED
77      AC_GEAR  LEFT_TIP    43.2 -214.8 59.4 10000 2000  0.2   0.2 0.2  FIXED NONE 0 FIXED
78      AC_GEAR  RIGHT_TIP   43.2  214.8 59.4 10000 2000  0.2   0.2 0.2  FIXED NONE 0 FIXED
79
80 </UNDERCARRIAGE>
81
82   <PROPULSION>
83
84     <!--
85       TANKS SECTION
86
87       Tank locations and characteristics, empty weight, in aircraft's own coord system:
88       X, Y, Z, in inches
89       effective radius of tank, in inches (for fuel slosh, if/when modeled)
90       capacity in pounds
91       Current contents, in pounds
92
93       ENGINE[S] SECTION
94
95       Engine[s] is|are specified by giving engine name (which corresponds to an engine
96       definition file in the "engines" directory) followed by x, y, z placement and
97       pitch and yaw orientation. Coordinates are given in inches in the structural
98       coordinate frame. Angles for pitch and yaw are specified in radians.
99
100       AC_ENGINE name x y z pitch yaw
101
102       THRUSTER[S] SECTION
103
104       AC_THRUSTER name x y z pitch yaw
105     -->
106
107     <AC_ENGINE FILE="engIO360C">
108       XLOC  -19.7
109       YLOC    0.0
110       ZLOC   26.6
111       PITCH   0.0
112       YAW     0.0
113       FEED      0
114       FEED      1
115     </AC_ENGINE>
116
117     <AC_THRUSTER FILE="prop_75in2f">
118       XLOC  -37.7
119       YLOC    0.0
120       ZLOC   26.6
121       PITCH   0.0
122       YAW     0
123       P_FACTOR 10.0
124       SENSE   1.0
125     </AC_THRUSTER>
126
127     <AC_TANK TYPE="FUEL" NUMBER="0">
128       XLOC   56.0
129       YLOC -112.0
130       ZLOC   59.4
131       RADIUS 29.4
132       CAPACITY 185.0
133       CONTENTS 100.0
134     </AC_TANK>
135
136     <AC_TANK TYPE="FUEL" NUMBER="1">
137       XLOC   56.0
138       YLOC  112.0
139       ZLOC   59.4
140       RADIUS 29.4
141       CAPACITY 185.0
142       CONTENTS 100.0
143     </AC_TANK>
144
145   </PROPULSION>
146
147   <FLIGHT_CONTROL NAME="c172">
148     <COMPONENT NAME="Pitch Trim Sum" TYPE="SUMMER">
149        ID            0
150        INPUT        FG_ELEVATOR_CMD
151        INPUT        FG_PITCH_TRIM_CMD
152        CLIPTO       -1 1
153     </COMPONENT>
154     <COMPONENT NAME="Elevator Control" TYPE="AEROSURFACE_SCALE">
155        ID            1
156        INPUT         0
157        MIN          -28
158        MAX           23
159        OUTPUT        FG_ELEVATOR_POS
160        GAIN          0.01745
161      </COMPONENT>
162      <COMPONENT NAME="Roll Trim Sum" TYPE="SUMMER">
163        ID            2
164        INPUT        FG_AILERON_CMD
165        INPUT        FG_ROLL_TRIM_CMD
166        CLIPTO       -1 1
167      </COMPONENT>
168      <COMPONENT NAME="Left Aileron Control" TYPE="AEROSURFACE_SCALE">
169        ID            3
170        INPUT         2
171        MIN          -20
172        MAX           15
173        GAIN          0.01745
174        OUTPUT        FG_LEFT_AILERON_POS
175      </COMPONENT>
176       <COMPONENT NAME="Right Aileron Control" TYPE="AEROSURFACE_SCALE">
177        ID            4
178        INPUT         FG_AILERON_CMD
179        MIN          -20
180        MAX           15
181        INVERT
182        GAIN          0.01745
183        OUTPUT        FG_RIGHT_AILERON_POS
184      </COMPONENT>
185      <COMPONENT NAME="Yaw Trim Sum" TYPE="SUMMER">
186        ID            5
187        INPUT        FG_RUDDER_CMD
188        INPUT        FG_YAW_TRIM_CMD
189        CLIPTO       -1 1
190      </COMPONENT>
191      <COMPONENT NAME="Rudder Control" TYPE="AEROSURFACE_SCALE">
192        ID            6
193        INPUT        5
194        MIN         -16
195        MAX          16
196        GAIN         0.01745
197        OUTPUT       FG_RUDDER_POS
198      </COMPONENT>
199      <COMPONENT NAME="Flaps Control" TYPE="KINEMAT">
200        ID           7
201        INPUT        FG_FLAPS_CMD
202        DETENTS      4
203                     0    0
204                     10   2
205                     20   1
206                     30   1
207        OUTPUT      FG_FLAPS_POS
208      </COMPONENT>
209    </FLIGHT_CONTROL>
210    <AERODYNAMICS>
211      <AXIS NAME="LIFT">
212        <GROUP NAME="CLb">
213          Basic_lift
214          <FACTOR NAME="kCLge" TYPE="VECTOR">
215             Change_in_lift_due_to_ground_effect
216             13
217             FG_HOVERB
218             FG_NONE
219             0.0   1.203
220             0.1   1.127
221             0.15  1.090
222             0.2   1.073
223             0.3   1.046
224             0.4   1.055
225             0.5   1.019
226             0.6   1.013
227             0.7   1.008
228             0.8   1.006
229             0.9   1.003
230             1.0   1.002
231             1.1   1.0
232          </FACTOR>
233          <COEFFICIENT NAME="CLwbh" TYPE="VECTOR">
234             Lift_due_to_alpha
235             11
236             FG_ALPHA
237             FG_QBAR|FG_WINGAREA
238             -0.087  -0.22
239              0       0.25
240              0.14    1.02
241              0.21    1.252
242              0.24    1.354
243              0.26    1.44
244              0.28    1.466
245              0.30    1.432
246              0.32    1.381
247              0.34    1.298
248              0.36    0.97
249           </COEFFICIENT>
250           <COEFFICIENT NAME="CLDf" TYPE="VECTOR">
251             Delta_lift_due_to_flap_deflection
252             4
253             FG_FLAPS_POS
254             FG_QBAR|FG_WINGAREA
255             0   0
256             10  0.20
257             20  0.30
258             30  0.35
259           </COEFFICIENT>
260        </GROUP>
261        <COEFFICIENT NAME="CLDe" TYPE="VALUE">
262          Lift_due_to_Elevator_Deflection
263          FG_QBAR|FG_WINGAREA|FG_ELEVATOR_POS
264          0.347
265        </COEFFICIENT>
266        <COEFFICIENT NAME="CLadot" TYPE="VALUE">
267          Lift_due_to_alpha_rate
268          FG_QBAR|FG_WINGAREA|FG_ALPHADOT|FG_CI2VEL
269          1.7
270        </COEFFICIENT>
271        <COEFFICIENT NAME="CLq" TYPE="VALUE">
272          Lift_due_to_pitch_rate
273          FG_QBAR|FG_WINGAREA|FG_AEROQ|FG_CI2VEL
274          3.9
275        </COEFFICIENT>
276     </AXIS>
277     <AXIS NAME="DRAG">
278       <COEFFICIENT NAME="CDo" TYPE="VALUE">
279          Drag_at_zero_lift
280          FG_QBAR|FG_WINGAREA
281          0.026
282       </COEFFICIENT>
283        <COEFFICIENT NAME="CDDf" TYPE="VECTOR">
284          Delta_drag_due_to_flap_deflection
285          4
286          FG_FLAPS_POS
287          FG_QBAR|FG_WINGAREA
288          0   0
289          10  0.007
290          20  0.012
291          30  0.018
292        </COEFFICIENT>
293       <COEFFICIENT NAME="CDwbh" TYPE="TABLE">
294          Drag_due_to_alpha
295          26
296          4
297          FG_ALPHA
298          FG_FLAPS_POS
299          FG_QBAR|FG_WINGAREA
300                     0             10             20             30
301         -0.0872664  0.00407143    3.8165e-05     0.000512444    0.00137231
302         -0.0698132  0.0013424     0.000440634    0.00248067     0.00412341
303         -0.0523599  8.96747e-05   0.00231942     0.0059252      0.00835082
304         -0.0349066  0.000313268   0.00567451     0.0108461      0.0140545
305         -0.0174533  0.00201318    0.0105059      0.0172432      0.0212346
306         0           0.0051894     0.0168137      0.0251167      0.0298909
307         0.0174533   0.00993967    0.0247521      0.0346492      0.0402205
308         0.0349066   0.0162201     0.0342207      0.0457119      0.0520802
309         0.0523599   0.0240308     0.0452195      0.0583047      0.0654701
310         0.0698132   0.0333717     0.0577485      0.0724278      0.0803902
311         0.0872664   0.0442427     0.0718077      0.088081       0.0968405
312         0.10472     0.056644      0.0873971      0.105265       0.114821
313         0.122173    0.0705754     0.104517       0.123978       0.134332
314         0.139626    0.086037      0.123166       0.144222       0.155373
315         0.15708     0.096239      0.135317       0.157346       0.168984
316         0.174533    0.106859      0.147857       0.170848       0.182966
317         0.191986    0.118034      0.160954       0.184905       0.197503
318         0.209439    0.129765      0.174606       0.199517       0.212596
319         0.226893    0.142366      0.189176       0.215072       0.228643
320         0.244346    0.156452      0.205363       0.23231        0.246406
321         0.261799    0.172732      0.223956       0.252059       0.266733
322         0.279253    0.178209      0.230187       0.258667       0.273529
323         0.296706    0.171598      0.222665       0.25069        0.265325
324         0.314159    0.161786      0.211468       0.2388         0.253089
325         0.331613    0.147493      0.19508        0.221364       0.235129
326         0.349066    0.109678      0.151171       0.174408       0.186649
327        </COEFFICIENT>
328        <COEFFICIENT NAME="CDDe" TYPE="VALUE">
329          Drag_due_to_Elevator_Deflection
330          FG_QBAR|FG_WINGAREA|FG_AELEVATOR_POS
331          0.06
332        </COEFFICIENT>
333        <COEFFICIENT NAME="CDbeta" TYPE="VALUE">
334          Drag_due_to_sideslip
335          FG_QBAR|FG_WINGAREA|FG_ABETA
336          0.17
337        </COEFFICIENT>
338
339     </AXIS>
340
341     <AXIS NAME="SIDE">
342        <COEFFICIENT NAME="CYb" TYPE="VECTOR">
343          Side_force_due_to_beta
344          3
345          FG_BETA
346          FG_QBAR|FG_WINGAREA
347          -0.349   0.108 
348           0       0
349           0.349  -0.108
350        </COEFFICIENT>
351
352        <COEFFICIENT NAME="CYda" TYPE="VALUE">
353          Side_force_due_to_aileron
354          FG_QBAR|FG_WINGAREA|FG_AILERON_POS
355         -0.05
356       </COEFFICIENT>
357
358       <COEFFICIENT NAME="CYdr" TYPE="VALUE">
359          Side_force_due_to_rudder
360          FG_QBAR|FG_WINGAREA|FG_RUDDER_POS
361          0.098
362       </COEFFICIENT>
363       <COEFFICIENT NAME="CYp" TYPE="VALUE">
364          Side_force_due_to_roll_rate
365          FG_QBAR|FG_WINGAREA|FG_BI2VEL|FG_AEROP
366          -0.037
367       </COEFFICIENT>
368       <COEFFICIENT NAME="CYr" TYPE="VALUE">
369          Side_force_due_to_yaw_rate
370          FG_QBAR|FG_WINGAREA|FG_BI2VEL|FG_AEROR
371          0.21
372       </COEFFICIENT>
373     </AXIS>
374
375     <AXIS NAME="ROLL">
376        <COEFFICIENT NAME="Clb" TYPE="VECTOR">
377          Roll_moment_due_to_beta
378          3
379          FG_BETA
380          FG_QBAR|FG_WINGAREA|FG_WINGSPAN
381          -0.349  0.0311
382           0      0
383           0.349 -0.0311
384        </COEFFICIENT>
385
386        <COEFFICIENT NAME="Clp" TYPE="VALUE">
387          Roll_moment_due_to_roll_rate_(roll_damping)
388          FG_QBAR|FG_WINGAREA|FG_WINGSPAN|FG_BI2VEL|FG_AEROP
389          -0.47
390        </COEFFICIENT>
391
392        <COEFFICIENT NAME="Clr" TYPE="VALUE">
393          Roll_moment_due_to_yaw_rate
394          FG_QBAR|FG_WINGAREA|FG_WINGSPAN|FG_BI2VEL|FG_AEROR
395          0.18
396        </COEFFICIENT>
397
398        <COEFFICIENT NAME="Clda" TYPE="VALUE">
399          Roll_moment_due_to_aileron
400          FG_QBAR|FG_WINGAREA|FG_WINGSPAN|FG_AILERON_POS
401          0.09
402        </COEFFICIENT>
403
404        <COEFFICIENT NAME="Cldr" TYPE="VALUE">
405          Roll_moment_due_to_rudder
406          FG_QBAR|FG_WINGAREA|FG_WINGSPAN|FG_RUDDER_POS
407          0.0147
408         </COEFFICIENT>
409
410       </AXIS>
411
412     <AXIS NAME="PITCH">
413
414       <COEFFICIENT NAME="Cmalpha" TYPE="VALUE">
415         Pitch_moment_due_to_alpha
416         FG_QBAR|FG_WINGAREA|FG_CBAR|FG_ALPHA
417         -1.8
418       </COEFFICIENT>
419       <COEFFICIENT NAME="CmDf" TYPE="VECTOR">
420          Delta_pitching_moment_due_to_flap_deflection
421          4
422          FG_FLAPS_POS
423          FG_QBAR|FG_WINGAREA|FG_CBAR
424          0    0
425          10  -0.0654
426          20  -0.0981
427          30  -0.1140
428        </COEFFICIENT>
429       <COEFFICIENT NAME="Cmq" TYPE="VALUE">
430          Pitch_moment_due_to_pitch_rate
431          FG_QBAR|FG_WINGAREA|FG_CBAR|FG_CI2VEL|FG_AEROQ
432          -12.4
433       </COEFFICIENT>
434       <COEFFICIENT NAME="Cmadot" TYPE="VALUE">
435         Pitch_moment_due_to_alpha_rate
436         FG_QBAR|FG_WINGAREA|FG_CBAR|FG_CI2VEL|FG_ALPHADOT
437         -5.2
438       </COEFFICIENT>
439       <COEFFICIENT NAME="Cmo" TYPE="VALUE">
440         Pitching_moment_at_zero_alpha
441         FG_QBAR|FG_WINGAREA|FG_CBAR
442         0.1
443       </COEFFICIENT>
444
445       <COEFFICIENT NAME="Cmde" TYPE="VALUE">
446         Pitch_moment_due_to_elevator_deflection
447         FG_QBAR|FG_WINGAREA|FG_CBAR|FG_ELEVATOR_POS
448         -1.28
449       </COEFFICIENT>
450
451     </AXIS>
452
453     <AXIS NAME="YAW">
454
455        <COEFFICIENT NAME="Cnb" TYPE="VECTOR">
456          Yaw_moment_due_to_beta
457          3
458          FG_BETA
459          FG_QBAR|FG_WINGAREA|FG_WINGSPAN
460          -0.349  -0.0227
461           0      0
462           0.349  0.0227
463        </COEFFICIENT>
464        <COEFFICIENT NAME="Cnp" TYPE="VALUE">
465          Yaw_moment_due_to_roll_rate
466          FG_QBAR|FG_WINGAREA|FG_WINGSPAN|FG_BI2VEL|FG_AEROP
467          -0.03
468         </COEFFICIENT>
469
470        <COEFFICIENT NAME="Cnr" TYPE="VALUE">
471          Yaw_moment_due_to_yaw_rate
472          FG_QBAR|FG_WINGAREA|FG_WINGSPAN|FG_BI2VEL|FG_AEROR
473          -0.099
474        </COEFFICIENT>
475
476        <COEFFICIENT NAME="Cnda" TYPE="VALUE">
477          Yaw_moment_due_to_aileron
478          FG_QBAR|FG_WINGAREA|FG_WINGSPAN|FG_AILERON_POS
479          0.0053
480        </COEFFICIENT>
481
482        <COEFFICIENT NAME="Cndr" TYPE="VALUE">
483          Yaw_moment_due_to_rudder
484          FG_QBAR|FG_WINGAREA|FG_WINGSPAN|FG_RUDDER_POS
485          -0.043
486        </COEFFICIENT>
487
488     </AXIS>
489   </AERODYNAMICS>
490   <!--
491     OUTPUT section definition
492
493     The following specifies the way that JSBSim writes out data.
494
495     NAME is the filename you want the output to go to
496
497     TYPE can be:
498       CSV       Comma separated data. If a filename is supplied then the data
499                 goes to that file. If COUT or cout is specified, the data goes
500                 to stdout. If the filename is a null filename the data goes to
501                 stdout, as well.
502       SOCKET    Will eventually send data to a socket output, where NAME
503                 would then be the IP address of the machine the data should be
504                 sent to. DON'T USE THIS YET!
505       TABULAR   Columnar data. NOT IMPLEMENTED YET!
506       TERMINAL  Output to terminal. NOT IMPLEMENTED YET!
507       NONE      Specifies to do nothing. THis setting makes it easy to turn on and
508                 off the data output without having to mess with anything else.
509
510     The arguments that can be supplied, currently, are
511
512     RATE_IN_HZ  An integer rate in times-per-second that the data is output. This
513                 value may not be *exactly* what you want, due to the dependence
514                 on dt, the cycle rate for the FDM.
515
516     The following parameters tell which subsystems of data to output:
517
518     SIMULATION       ON|OFF
519     ATMOSPHERE       ON|OFF
520     MASSPROPS        ON|OFF
521     AEROSURFACES     ON|OFF
522     RATES            ON|OFF
523     VELOCITIES       ON|OFF
524     FORCES           ON|OFF
525     MOMENTS          ON|OFF
526     POSITION         ON|OFF
527     COEFFICIENTS     ON|OFF
528     GROUND_REACTIONS ON|OFF
529     FCS              ON|OFF
530     PROPULSION       ON|OFF
531
532     NOTE that Time is always output with the data.
533   -->
534   <OUTPUT NAME="JSBout172.csv" TYPE="NONE">
535     RATE_IN_HZ       20
536     SIMULATION       OFF
537     ATMOSPHERE       ON
538     MASSPROPS        ON
539     AEROSURFACES     ON
540     RATES            ON
541     VELOCITIES       ON
542     FORCES           ON
543     MOMENTS          ON
544     POSITION         ON
545     COEFFICIENTS     ON
546     GROUND_REACTIONS ON
547     FCS              ON
548     PROPULSION       ON
549   </OUTPUT>
550 </FDM_CONFIG>
551