Indicate these models want to use their own terrein handling code, until they switch...
[fg:toms-fgdata.git] / Aircraft / F-8E-Crusader / f8e_v4-jsbsim.xml
1 <?xml version="1.0"?>
2 <?xml-stylesheet href="http://jsbsim.sourceforge.net/JSBSim.xsl" type="text/xsl"?>
3 <fdm_config name="F-8E-Crusader" version="2.0" release="BETA"
4  xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
5  xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">
6
7
8     <fileheader>
9         <author>from template (Aeromatic), Gérard Robin, and Alva </author>
10         <filecreationdate>17-October-2010</filecreationdate>
11         <version> Version 1.4 better data from Naca Doc</version>
12         <description> Models a F-8E-Crusader </description>
13         <note>
14             This model was created using publicly available data, publicly available
15             technical reports, textbooks, and guesses. It contains no proprietary or
16             restricted data. It has been validated only to the extent that it seems
17             to "fly right", and possibly to comply to published, publicly known,
18             performance data (maximum speed, endurance, etc.). Thus, this model
19             is meant for educational and entertainment purposes only.
20
21             This simulation model is not endorsed by the manufacturer.
22         </note>
23         <documentation>
24
25                 http://aeronavale.free.fr/avion_crusader.htm
26                 *********************************************************************
27                 Vought F-8E (FN) Crusader : Caractéristiques principales
28                 Constructeur     Ling-Temco-Vought
29                 Mission     Interception tout temps
30                 Envergure     10.72 m
31                 Longueur     16.61 m
32                 Hauteur     4.80 m
33                 Surface alaire     34.84 m2
34                 Poids max           13 000 kg
35                 Moteur     1 réacteur J 57 P 20 A Pratt et Whitney
36                 Vitesse max    Mach 1.8
37                 Vitesse de croisière     860 km/h
38                 Vitesse d'appontage     180 km/h (97kt)
39                 Plafond     50.000 pieds
40                 Distance franchissable     1 500 nautiques
41                 Autonomie     2 h 30
42                 ********************************************************************************
43                 http://www.vought.com/heritage/products/html/f8u-2spec.html
44
45                 Data below for F-8C
46                 Dimensions
47                 Wingspan    35.17 ft
48                 Overall Langth    55.25 ft
49                 Height    15.75 ft
50                 Weights and Capacities
51                 Empty Weight    18950 lb
52                 Fuel Capacity    1348 gal
53
54                 Powerplant Characteristics
55                 Type:  Pratt  Whitney J57-P16
56                 Rating Thrust    10700 lb
57                 Rating Thrust with afterburner
58                 16900 lb
59
60                 Performance
61                 Maximum Speed, Sea Level
62                 1105 mph
63
64                 **********************************************************************
65                 http://www.aerospaceweb.org/aircraft/fighter/f8/
66
67                 Data below for F-8P
68                 Last modified 14 November 2004
69                 HISTORY:
70                 First Flight    (XF-8U-1) 25 March 1955
71                 (F-8A) 20 September 1955
72                 Service Entry   March 1957
73                 Retirement      4 December 1999
74                 AIRFOIL SECTIONS:
75                 Wing Root       NACA 65A006 mod
76                 Wing Tip        NACA 65A005 mod
77                 DIMENSIONS:
78                 Length  54.50 ft (16.61 m)
79                 Wingspan        35.17 ft (10.72 m)
80                 Height  15.75 ft (4.80 m)
81                 Wing Area       374 ft2 (34.84 m2)
82                 WEIGHTS:
83                 Empty   19,700 lb (8,935 kg)
84                 Typical Load    27,560 lb (12,500 kg)
85                 Max Takeoff     34,000 lb (15,420 kg)
86                 Fuel Capacity   internal: 5,300 L
87                 PROPULSION:
88                 Powerplant      one Pratt  Whitney J57-P-20A afterburning turbojet
89                 Thrust  18,000 lb (80.07 kN)
90                 PERFORMANCE:
91                 Max Level Speed         at altitude: 1,225 mph (1,975 km/h) at 40,000 ft (12,190 m), Mach 1.86
92                 at sea level: unknown
93                 Initial Climb Rate      21,000 ft (6,410 m) / min
94                 Service Ceiling         unknown
95                 Range   typical: 380 nm (710 km)
96                 ferry: 1,040 nm (1,930 km)
97                 g-Limits        unknown
98                 ARMAMENT:
99                 Gun     four 20-mm Colt cannons (84 to 144 rds ea)
100                 Stations        four external hardpoints
101                 Air-to-Air Missile      R.530, Matra 550 Magic, AIM-9 Sidewinder
102                 *************************************************************************************************************************
103                 The F-8A entered service in March of 1957.
104                 Length:                                 55' 3"
105                 Height:                         15' 9"
106                 Wingspan (spread)               35' 8"
107                 Wing area:                              375 sq. ft.
108                 NACA 65A006 mod
109
110                         F-8E
111                 Empty Wt:                                                       19,200
112                 Max Launch Wt:                                  34,100
113                 Max Trap Wt:                                            22,000
114                 Approach speed @max:                            140 kts
115                 Stall, pwr. on/off                                      123/145 kts
116                 JP-5, internal-gal/lb:                                  1,348/9,100
117                 Engine: PW J-57-P....                           16
118                 Thrust, MRT/CRT, #:                             10,700/18,000
119                 Guns:                                                           4-20mm, 500 rds
120                 Missiles:                                                       4 Sidewinder
121                 Max Speed, IMN/mph**:                           1.9/1,255
122                 Combat Radius, nm:                              355
123                 Service Ceiling, MRT                            40,000'
124
125                 *************************************************************************
126
127                 from http://en.wikipedia.org/wiki/F-8_Crusader
128                 # Dry thrust: 10,700 lbf (47.6 kN)
129                 # Thrust with afterburner: 18,000 lbf (80.1 kN)
130                 Airfoil: NACA 65A006 mod root, NACA 65A005 mod tip
131                 Zero-lift drag coefficient: 0.0133
132                 # Drag area: 5.0 ft² (0.46 m²)
133                 # Aspect ratio: 3.42
134
135                 quelques documents qui donnent des courbes19930087197_1993087197-naca65A006.pdf
136                 et 19930087933_1993087933-naca65A006.pdf
137
138                 **************************************************************************
139                 >>>>>>>The very first version ( right now, outdated) was :File:     f8e.xml
140                         Author:   template Aero-Matic v 8
141                         Adons from Gerard Robin     07-10-2005   (jj mm aa)
142                         with an original carrier landing patch (from Mathias Froëhlich)
143                 Inputs:
144                 name:          Vought F-8E Crusader
145                 type:          single-engine transonic/supersonic fighter
146                 max weight:    34100 lb
147                 wing span:     35.17232 ft
148                 length:        54.49741 ft
149                 wing area:     375.0526 sq-ft
150                 gear type:     tricycle
151                 retractable?:  yes
152                 # engines:     1
153                 engine type:   turbine
154                 engine layout: aft fuselage
155                 yaw damper?    yes
156                 Outputs:
157                 wing loading:  90.92 lb/sq-ft
158                 CL-alpha:      3.5 per radian
159                 CL-0:          0.08
160                 CL-max:        1
161                 CD-0:          0.021
162                 K:             0.09
163                 >>>>>>>>>>>>>>>>
164                 ******************************************************************************
165         </documentation>
166     </fileheader>
167
168     <metrics>
169         <wingarea unit="FT2"> 375.05 </wingarea>
170         <wingspan unit="FT"> 35.17 </wingspan>
171         <wing_incidence unit="DEG">0.0</wing_incidence>
172         <chord unit="FT"> 14.76 </chord>
173         <htailarea unit="FT2"> 57 </htailarea>
174         <htailarm unit="FT"> 20.8 </htailarm>
175         <vtailarea unit="FT2"> 113 </vtailarea>  <!--7.5 m2 + 3m2 (fanon)-->
176         <vtailarm unit="FT"> 20.4 </vtailarm>
177         <location name="AERORP" unit="IN">
178             <x> 63</x>
179             <y> 0 </y>
180             <z> 23 </z>
181         </location>
182         <location name="EYEPOINT" unit="IN">
183             <x> 130.8 </x>
184             <y> 0 </y>
185             <z> 36 </z>
186         </location>
187         <location name="VRP" unit="IN">
188             <x> 0 </x>
189             <y> 0 </y>
190             <z> 0 </z>
191         </location>
192     </metrics>
193
194     <mass_balance>
195         <ixx unit="SLUG*FT2">     14326 </ixx>
196         <iyy unit="SLUG*FT2">     61143 </iyy>
197         <izz unit="SLUG*FT2">     56327 </izz>
198
199        <!-- <ixx unit="SLUG*FT2"> 23803 </ixx>
200         <iyy unit="SLUG*FT2"> 96049 </iyy>
201         <izz unit="SLUG*FT2"> 84902 </izz>-->
202
203         <emptywt unit="LBS"> 19700 </emptywt>
204         <location name="CG" unit="IN">
205             <x> 72</x>
206             <y> 0 </y>
207             <z> 0</z>
208         </location>
209         <pointmass name="Transfer-tank"> <!-- Tank Transfert  Max 5678 lbs -->
210             <weight unit="LBS">4000</weight>
211             <location name="Transfer Tank" unit="IN">
212                 <x> 72 </x>
213                 <y> 0 </y>
214                 <z> 17 </z>
215             </location>
216         </pointmass>
217         <pointmass name="Main-tank">    <!-- Tank Main  Max 3488 lbs -->
218             <weight unit="LBS">3000</weight>
219             <location unit="IN">
220                 <x> 63 </x>
221                 <y> 0 </y>
222                 <z> 0 </z>
223             </location>
224         </pointmass>
225         <pointmass name="Nose_Gear_Testing">
226             <weight unit="LBS">0</weight>
227             <location unit="IN">
228                 <x> -139.76 </x>
229                 <y> 0 </y>
230                 <z> -81.6 </z>
231             </location>
232         </pointmass>
233         <pointmass name="Left_Gear_Testing">
234             <weight unit="LBS">0</weight>
235             <location unit="IN">
236                 <x> 82.44 </x>
237                 <y> -58.03 </y>
238                 <z> -65.75 </z>
239             </location>
240         </pointmass>
241         <pointmass name="Right_Gear_Testing">
242             <weight unit="LBS">0</weight>
243             <location unit="IN">
244                 <x> 82.44 </x>
245                 <y> 58.03 </y>
246                 <z> -65.75 </z>
247             </location>
248         </pointmass>
249     </mass_balance>
250
251
252     <ground_reactions>
253         <contact type="BOGEY" name="NOSE_LG">  <!--0-->
254             <location unit="IN">
255                 <x> -139.76 </x>
256                 <y> 0 </y>
257                 <z> -81.2 </z>
258             </location>
259             <static_friction> 0.8 </static_friction>
260             <dynamic_friction> 0.5 </dynamic_friction>
261             <rolling_friction> 0.02 </rolling_friction>
262             <spring_coeff unit="LBS/FT"> 14000</spring_coeff>
263             <damping_coeff unit="LBS/FT/SEC">3500</damping_coeff>
264             <max_steer unit="DEG"> 60</max_steer>
265             <brake_group> NONE </brake_group>
266             <retractable>1</retractable>
267         </contact>
268         <contact type="BOGEY" name="LEFT_MLG"> <!--1-->
269             <location unit="IN">
270                 <x> 82.44 </x>
271                 <y> -58.03 </y>
272                 <z> -65.75 </z>
273             </location>
274             <static_friction> 0.8 </static_friction>
275             <dynamic_friction> 0.5 </dynamic_friction>
276             <rolling_friction> 0.02 </rolling_friction>
277             <spring_coeff unit="LBS/FT"> 55000 </spring_coeff>
278             <damping_coeff unit="LBS/FT/SEC"> 11000</damping_coeff>
279             <max_steer unit="DEG"> 0.0 </max_steer>
280             <brake_group> LEFT </brake_group>
281             <retractable>1</retractable>
282         </contact>
283         <contact type="BOGEY" name="RIGHT_MLG"> <!--2-->
284             <location unit="IN">
285                 <x> 82.44 </x>
286                 <y> 58.03 </y>
287                 <z> -65.75 </z>
288             </location>
289             <static_friction> 0.8 </static_friction>
290             <dynamic_friction> 0.5 </dynamic_friction>
291             <rolling_friction> 0.02 </rolling_friction>
292             <spring_coeff unit="LBS/FT"> 55000 </spring_coeff>
293             <damping_coeff unit="LBS/FT/SEC"> 11000 </damping_coeff>
294             <max_steer unit="DEG"> 0.0 </max_steer>
295             <brake_group> RIGHT </brake_group>
296             <retractable>1</retractable>
297         </contact>
298
299        <!-- ========================================================================-->
300
301
302         <contact type="STRUCTURE" name="W_LEFT_FOLD"> <!--3-->
303             <location unit="IN">
304                 <x> 171 </x>
305                 <y> -213 </y>
306                 <z> 7.5 </z>
307             </location>
308             <static_friction> 0.2 </static_friction>
309             <dynamic_friction> 0.2 </dynamic_friction>
310             <rolling_friction> 10 </rolling_friction>
311             <spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
312             <damping_coeff unit="LBS/FT/SEC"> 200 </damping_coeff>
313             <max_steer unit="DEG"> 0.0 </max_steer>
314             <brake_group> NONE </brake_group>
315             <retractable>1</retractable>
316         </contact>
317         <contact type="STRUCTURE" name="W_RIGHT_FOLD"><!-- 4-->
318             <location unit="IN">
319                 <x> 171 </x>
320                 <y> 213 </y>
321                 <z> 7.5 </z>
322             </location>
323             <static_friction> 0.2 </static_friction>
324             <dynamic_friction> 0.2 </dynamic_friction>
325             <rolling_friction> 10 </rolling_friction>
326             <spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
327             <damping_coeff unit="LBS/FT/SEC"> 200 </damping_coeff>
328             <max_steer unit="DEG"> 0.0 </max_steer>
329             <brake_group> NONE </brake_group>
330             <retractable>1</retractable>
331         </contact>
332         <contact type="STRUCTURE" name="W_LEFT"> <!--5-->
333             <location unit="IN">
334                 <x> 113</x>
335                 <y> -135.3 </y>
336                 <z> 15.76 </z>
337             </location>
338             <static_friction> 0.2 </static_friction>
339             <dynamic_friction> 0.2 </dynamic_friction>
340             <rolling_friction> 0.2 </rolling_friction>
341             <spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
342             <damping_coeff unit="LBS/FT/SEC"> 200 </damping_coeff>
343             <max_steer unit="DEG"> 0.0 </max_steer>
344             <brake_group> NONE </brake_group>
345             <retractable>0</retractable>
346         </contact>
347         <contact type="STRUCTURE" name="W_RIGHT"> <!--6-->
348             <location unit="IN">
349                 <x> 113 </x>
350                 <y> 135.3 </y>
351                 <z> 15.76</z>
352             </location>
353             <static_friction> 0.2 </static_friction>
354             <dynamic_friction> 0.2 </dynamic_friction>
355             <rolling_friction> 0.2 </rolling_friction>
356             <spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
357             <damping_coeff unit="LBS/FT/SEC"> 200 </damping_coeff>
358             <max_steer unit="DEG"> 0.0 </max_steer>
359             <brake_group> NONE </brake_group>
360             <retractable>0</retractable>
361         </contact>
362         <contact type="STRUCTURE" name="VT"> <!--7-->
363             <location unit="IN">
364                 <x> 312 </x>
365                 <y> 0 </y>
366                 <z> 14.5 </z>
367             </location>
368             <static_friction> 0.2 </static_friction>
369             <dynamic_friction> 0.2 </dynamic_friction>
370             <rolling_friction> 0.2 </rolling_friction>
371             <spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
372             <damping_coeff unit="LBS/FT/SEC"> 200 </damping_coeff>
373             <max_steer unit="DEG"> 0.0 </max_steer>
374             <brake_group> NONE </brake_group>
375             <retractable>0</retractable>
376         </contact>
377         <contact type="STRUCTURE" name="RADOME"> <!--8-->
378             <location unit="IN">
379                 <x> -172 </x>
380                 <y> 0 </y>
381                 <z> 39.5 </z>
382             </location>
383             <static_friction> 0.2 </static_friction>
384             <dynamic_friction> 0.2 </dynamic_friction>
385             <rolling_friction> 0.2 </rolling_friction>
386             <spring_coeff unit="LBS/FT"> 100 </spring_coeff>
387             <damping_coeff unit="LBS/FT/SEC"> 20000 </damping_coeff>
388             <max_steer unit="DEG"> 0.0 </max_steer>
389             <brake_group> NONE </brake_group>
390             <retractable>1</retractable>
391         </contact>
392         <contact type="BOGEY" name="BELLY"> <!--9-->
393             <location unit="IN">
394                 <x> -173 </x>
395                 <y> 0 </y>
396                 <z> -39.3 </z>
397             </location>
398             <static_friction> 0.2 </static_friction>
399             <dynamic_friction> 0.2 </dynamic_friction>
400             <rolling_friction> 0.2 </rolling_friction>
401             <spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
402             <damping_coeff unit="LBS/FT/SEC"> 3000 </damping_coeff>
403             <max_steer unit="DEG"> 0.0 </max_steer>
404             <brake_group> NONE </brake_group>
405             <retractable>1</retractable>
406         </contact>
407         <contact type="STRUCTURE" name="NOSE"> <!--10-->
408             <location unit="IN">
409                 <x> -317 </x>
410                 <y> 0 </y>
411                 <z> -10 </z>
412             </location>
413             <static_friction> 0.2 </static_friction>
414             <dynamic_friction> 0.2 </dynamic_friction>
415             <rolling_friction> 0.2 </rolling_friction>
416             <spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
417             <damping_coeff unit="LBS/FT/SEC"> 2000</damping_coeff>
418             <max_steer unit="DEG"> 0.0 </max_steer>
419             <brake_group> NONE </brake_group>
420             <retractable>1</retractable>
421         </contact>
422         <contact type="STRUCTURE" name="NOZZLE"> <!--11-->
423             <location unit="IN">
424                 <x> 315 </x>
425                 <y> 0 </y>
426                 <z> -26 </z>
427             </location>
428             <static_friction> 0.2 </static_friction>
429             <dynamic_friction> 0.2 </dynamic_friction>
430             <rolling_friction> 0.2 </rolling_friction>
431             <spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
432             <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
433             <max_steer unit="DEG"> 0.0 </max_steer>
434             <brake_group> NONE </brake_group>
435             <retractable>1</retractable>
436         </contact>
437         <contact type="STRUCTURE" name="TOP"> <!--12-->
438             <location unit="IN">
439                 <x> 0 </x>
440                 <y> 0 </y>
441                 <z> 60</z>
442             </location>
443             <static_friction> 0.2 </static_friction>
444             <dynamic_friction> 0.2 </dynamic_friction>
445             <rolling_friction> 0.2 </rolling_friction>
446             <spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
447             <damping_coeff unit="LBS/FT/SEC"> 20000 </damping_coeff>
448             <max_steer unit="DEG"> 0.0 </max_steer>
449             <brake_group> NONE </brake_group>
450             <retractable>1</retractable>
451         </contact>
452         <contact type="STRUCTURE" name="FICTIVE_REAR"> <!--13-->
453             <location unit="IN">
454                 <x>120 </x>
455                 <y>0</y>
456                 <z> -20 </z>
457             </location>
458             <static_friction> 0.2 </static_friction>
459             <dynamic_friction> 0.2 </dynamic_friction>
460             <rolling_friction> 0.2 </rolling_friction>
461             <spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
462             <damping_coeff unit="LBS/FT/SEC"> 20000 </damping_coeff>
463             <max_steer unit="DEG"> 0.0 </max_steer>
464             <brake_group> NONE </brake_group>
465             <retractable>1</retractable>
466         </contact>
467         <contact type="BOGEY" name="FICTIVE_FRONT"> <!--14-->
468             <location unit="IN">
469                 <x>-334.6</x>
470                 <y>0</y>
471                 <z> -100 </z>
472             </location>
473             <static_friction> 0.2 </static_friction>
474             <dynamic_friction> 0.2 </dynamic_friction>
475             <rolling_friction> 0.2 </rolling_friction>
476             <spring_coeff unit="LBS/FT"> 10 </spring_coeff>
477             <damping_coeff unit="LBS/FT/SEC"> 2 </damping_coeff>
478             <max_steer unit="DEG"> 0.0 </max_steer>
479             <brake_group> NONE </brake_group>
480             <retractable>1</retractable>
481         </contact>
482
483
484 <!--=========================================================-->
485         <!--DON'T  MODIFY:  Used to animate LG  at rest    with  extended  position-->
486         <!--we are missing an extension dimension definition within LG-->
487
488         <contact type="STRUCTURE" name="NOSE_LG_under">  <!--CP 15-->
489             <location unit="IN">
490                 <x> -139.76 </x>
491                 <y> 0 </y>
492                 <z> -92 </z>
493             </location>
494             <static_friction> 0.001 </static_friction>
495             <dynamic_friction> 0.001 </dynamic_friction>
496             <rolling_friction> 0.0001 </rolling_friction>
497             <spring_coeff unit="LBS/FT"> 10</spring_coeff>
498             <damping_coeff unit="LBS/FT/SEC">2</damping_coeff>
499             <max_steer unit="DEG"> 0.0</max_steer>
500             <brake_group> NONE </brake_group>
501             <retractable>1</retractable>
502         </contact>
503         <contact type="STRUCTURE" name="LEFT_MLG_under"> <!--CP 16-->
504             <location unit="IN">
505                 <x> 82.44 </x>
506                 <y> -58.03 </y>
507                 <z> -78 </z>
508             </location>
509             <static_friction> 0.001 </static_friction>
510             <dynamic_friction> 0.001 </dynamic_friction>
511             <rolling_friction> 0.0001 </rolling_friction>
512             <spring_coeff unit="LBS/FT"> 10</spring_coeff>
513             <damping_coeff unit="LBS/FT/SEC"> 2</damping_coeff>
514             <max_steer unit="DEG"> 0.0 </max_steer>
515             <brake_group> NONE</brake_group>
516             <retractable>1</retractable>
517         </contact>
518         <contact type="STRUCTURE" name="RIGHT_MLG_under"> <!--CP 17-->
519             <location unit="IN">
520                 <x> 82.44 </x>
521                 <y> 58.03 </y>
522                 <z> -78 </z>
523             </location>
524             <static_friction> 0.001 </static_friction>
525             <dynamic_friction> 0.001 </dynamic_friction>
526             <rolling_friction> 0.0001 </rolling_friction>
527             <spring_coeff unit="LBS/FT"> 10 </spring_coeff>
528             <damping_coeff unit="LBS/FT/SEC"> 2 </damping_coeff>
529             <max_steer unit="DEG"> 0.0 </max_steer>
530             <brake_group> RIGHT </brake_group>
531             <retractable>1</retractable>
532         </contact>
533
534
535     </ground_reactions>
536     <propulsion>
537         <engine file="PW-J57P-new">
538             <location unit="IN">
539                 <x> 317 </x>
540                 <y> 0 </y>
541                 <z> 0 </z>
542             </location>
543             <orient unit="DEG">
544                 <roll> 0.0 </roll>
545                 <pitch> 0 </pitch>
546                 <yaw> 0 </yaw>
547             </orient>
548             <feed>0</feed>
549             <thruster file="direct-new">
550                 <location unit="IN">
551                     <x> 317 </x>
552                     <y> 0 </y>
553                     <z> 0 </z>
554                 </location>
555                 <orient unit="DEG">
556                     <roll> 0.0 </roll>
557                     <pitch> 0.0 </pitch>
558                     <yaw> 0.0 </yaw>
559                 </orient>
560             </thruster>
561         </engine>
562
563         <tank type="FUEL">
564             <location unit="IN">
565                 <x> 0 </x>
566                 <y> 0 </y>
567                 <z> -16.3492 </z>
568             </location>
569             <priority>1</priority>
570             <capacity unit="LBS"> 5 </capacity>
571             <contents unit="LBS"> 0 </contents>
572         </tank>
573
574     </propulsion>
575     <!--<system file="aero"/>-->
576     <system file="fcs"/>
577     <system file="steady-behaviour"/>
578     
579     <!-- _________________-->
580     <system file="electrical-fdm-custom"/>
581     <system file="electrical-fdm"/>
582     <system file="electrical-lights"/>
583    <!-- _____Carrier____________-->
584
585    <system file="catapult_free"/>
586    <system file="holdback_free"/>
587     <!-- _________________-->
588
589     <system file="init-carrier"/>
590     
591      <system file="cat-hold"/>
592     
593     <system file="hook"/>
594     
595     <!-- _____FCS______________-->
596     <system file="speedbrake"/>
597     <system file="wings"/>
598     <!--<system file="FCS-Stall_Spin"/>-->
599     <system file="BLC"/>
600     <system file="propulsion"/>
601     <!-- _________________-->
602     <system file="crash-detect"/>
603     <system file="crash-sink-anim"/>
604     <!-- _________________-->
605     
606     <system file="fuel"/>
607     <system file="probe-refuel"/>
608     <system file="refuel"/>
609     <!-- _________________-->
610
611     <!-- _________________-->
612     <system file="brake"/>
613     <system file="landing-gear"/>
614     <!-- _________________-->
615     <system file="instruments"/>
616     <system file="annunciator"/>
617     <system file="aoa-new"/>
618     <!-- _________________-->
619     <system file="canopy"/>
620     <!-- _________________-->
621     
622     <system file="mule-crus"/>
623     <!-- _________________-->
624     <system file="blackout"/>
625     <system file="cpdrag"/>
626     
627     
628
629
630
631     <flight_control name="FCS: F-8E">
632
633
634     </flight_control>
635
636     <aerodynamics>
637         <!--Variable incidence wings,   the max incidence 7 deg  0.12217305 rad    -->
638         <!--french version Variable incidence wings,   the max incidence 8 deg  0.13962634 rad     defined within  systems/wings ( line 124)-->
639         <!--<function name="aero/alpha-rad-w-incidence">
640             <description>Addition of incidence due to UP</description>
641                 <sum>
642                     <property>aero/alpha-rad</property>
643                     <property>fcs/wings-pos-rad</property>
644                 </sum>
645         </function>-->
646         <!--Voir wings.xml-->
647
648
649
650        <!-- Here from A-7E by Dave-->
651         <function name="aero/function/kCDge">
652             <description>Change_in_drag_due_to_ground_effect</description>
653             <product>
654                 <table>
655                     <independentVar>aero/h_b-mac-ft</independentVar>
656                     <tableData>
657                         0.0000  0.0480
658                         0.1000  0.5150
659                         0.1500  0.6290
660                         0.2000  0.7090
661                         0.3000  0.8150
662                         0.4000  0.8820
663                         0.5000  0.9280
664                         0.6000  0.9620
665                         0.7000  0.9880
666                         0.8000  1.0000
667                     </tableData>
668                 </table>
669             </product>
670         </function>
671
672         <function name="aero/function/kCLge">
673             <description>Change_in_lift_due_to_ground_effect</description>
674             <product>
675                 <table>
676                     <independentVar>aero/h_b-mac-ft</independentVar>
677                     <tableData>
678                         0.0000  1.2030
679                         0.1000  1.1270
680                         0.1500  1.0900
681                         0.2000  1.0730
682                         0.3000  1.0460
683                         0.4000  1.0550
684                         0.5000  1.0190
685                         0.6000  1.0130
686                         0.7000  1.0080
687                         0.8000  1.0060
688                         0.9000  1.0030
689                         1.0000  1.0020
690                         1.1000  1.0000
691                     </tableData>
692                 </table>
693             </product>
694         </function>
695
696         <!--CL-alpha:      3.5 per radian
697                            CL-0:          0.08
698                            CL-max:        1
699                            CD-0:          0.021    must be checked with data tunnel
700                         K:             0.09-->
701
702         <!--document 19930085859_1993085859.pdf with SviTEPT RACK 35O, ASPECT RATIO 4, TAPER RATIO 0.8,
703         AND NACA 65A006 AIRFOIL SECTION.-->
704         <!--Zero-lift drag coefficient: 0.0133-->
705         <!--CL-alpha:      3.5 per radian
706             CL-0:          0.08
707             CL-max:        1
708             CD-0:          0.021  must be checked with data tunnel
709             K:             0.09
710             NACA 65A006  -->
711         <!--lift curve calculated with wing pos-norm  0  ==> 0 degree TEFlap 0 LEFlap 0-->
712         <!--lift curve calculated with wing pos-norm  1  ==> 8 degree TEFlap 32 LEFlap 12-->
713
714
715             <function name="aero/function/krootCLalpha">
716                 <description>kLift_due_to_alpha</description>
717                 <product>
718                     <sum>
719                         <property>systems/wing-lift_coeff_add</property>
720                         <value>1</value>
721                     </sum>
722                     <table>
723                         <independentVar lookup="row">aero/alpha-deg</independentVar>
724                         <independentVar lookup="column">fcs/wings-pos-norm</independentVar>
725                           <tableData name="lw">
726
727                                                         00.000000               01.000000
728                             -15.00000           -00.72130               -00.22030
729                             -14.50000           -00.70880               -00.21470
730                             -14.00000           -00.69700               -00.20910
731                             -13.50000           -00.68590               -00.20350
732                             -13.00000           -00.67550               -00.19820
733                             -12.50000           -00.66670               -00.19320
734                             -12.00000           -00.65890               -00.18860
735                             -11.50000           -00.65140               -00.18490
736                             -11.00000           -00.64570               -00.18270
737                             -10.50000           -00.63930               -00.18410
738                             -10.00000           -00.63390               -00.19700
739                             -09.50000           -00.63030               -00.19610
740                             -09.00000           -00.62800               -00.18170
741                             -08.50000           -00.62770               -00.15770
742                             -08.00000           -00.63370               -00.12070
743                             -07.50000           -00.63870               -00.06510
744                             -07.00000           -00.63000               00.02080
745                             -06.50000           -00.61290               00.54750
746                             -06.00000           -00.58950               00.60180
747                             -05.50000           -00.56140               00.64070
748                             -05.00000           -00.52190               00.69190
749                             -04.50000           -00.47850               00.73390
750                             -04.00000           -00.42600               00.78200
751                             -03.50000           -00.37310               00.82850
752                             -03.00000           -00.32020               00.87710
753                             -02.50000           -00.26730               00.92320
754                             -02.00000           -00.21400               00.96910
755                             -01.50000           -00.16050               01.00840
756                             -01.00000           -00.10700               01.08538
757                             -00.50000           -00.05350               01.16236
758                             00.00000            00.00000                01.23933
759                             00.50000            00.05350                01.31631
760                             01.00000            00.10700                01.39329
761                             01.50000            00.16050                01.47027
762                             02.00000            00.21400                01.47027
763                             02.50000            00.26730                01.47934
764                             03.00000            00.32020                01.47854
765                             03.50000            00.37310                01.47682
766                             04.00000            00.42600                01.47528
767                             04.50000            00.47850                01.47595
768                             05.00000            00.51800                01.47630
769                             05.50000            00.56380                01.47660
770                             06.00000            00.58950                01.47610
771                             06.50000            00.61300                01.43530
772                             07.00000            00.63020                01.39330
773                             07.50000            00.63910                01.35630
774                             08.00000            00.63440                01.32860
775                             08.50000            00.62890                01.31990
776                             09.00000            00.62960                01.31810
777                             09.50000            00.63220                01.31790
778                             10.00000            00.63600                01.31940
779                             10.50000            00.64160                01.32230
780                             11.00000            00.64820                01.32590
781                             11.50000            00.65420                01.33010
782                             12.00000            00.66180                01.33440
783                             12.50000            00.66960                01.33850
784                             13.00000            00.67860                01.34180
785                             13.50000            00.68910                01.34320
786                             14.00000            00.70030                01.33720
787                             18.00000           00.65000               01.30000
788                             20.00000           00.62000               01.12200
789                             25.00000           00.61000               01.00000
790                             40.00000           00.60000               00.90000
791                             </tableData>
792                         </table>
793                     </product>
794             </function>
795
796             
797 <!--RE 3000000-->
798             <function name="aero/function/ktipCLalpha">
799                 <description>kwing tip_Lift_due_to_alpha</description>
800                 <product>
801                     <sum>
802                         <property>systems/wing-lift_coeff_add</property>
803                         <value>1</value>
804                     </sum>
805                     <table>
806                         <independentVar>aero/alpha-wing-deg</independentVar>
807                         <tableData>
808                             -14         -1.036299
809                             -13         -1.076908
810                             -12         -1.206191
811                             -11         -1.154813
812                             -10         -1.089431
813                             -9         -1.020265
814                             -8        -0.9251668
815                             -7        -0.7986193
816                             -6        -0.6783747
817                             -5        -0.5491416
818                             -4        -0.4273973
819                             -3        -0.2967012
820                             -2        -0.1948231
821                             -1       -0.09816584
822                             0      1.728283e-10
823                             1        0.09816586
824                             2         0.1948231
825                             3         0.2967018
826                             4         0.4274075
827                             5         0.5491644
828                             6         0.6784037
829                             7         0.7986763
830                             8         0.9252383
831                             9          1.020225
832                             10          1.089411
833                             11          1.154854
834                             12          1.206384
835                             13          1.075839
836                             14          1.037182
837                             15          1.002985
838                             16         0.8640548
839                             17         0.7118886
840                             18         0.7352895
841                             19         0.7630147
842                             20         0.7861199
843                             21         0.8082324
844                             22         0.8289926
845                             40          0.600000
846                         </tableData>
847                     </table>
848                 </product>
849             </function>
850
851 <!--RE 3000000-->
852             <function name="aero/function/ktipLeCLalpha">
853                 <description>kwing tip_Lift_with_LE_due_to_alpha</description>
854                 <product>
855                     <sum>
856                         <property>systems/wing-lift_coeff_add</property>
857                         <value>1</value>
858                     </sum>
859                     <table>
860                         <independentVar>aero/alpha-wing-deg</independentVar>
861
862                         <tableData>
863
864                             -10.00              -00.3824
865                             -09.50              -00.3652
866                             -09.00              -00.3510
867                             -08.50              -00.3383
868                             -08.00              -00.3270
869                             -07.50              -00.3168
870                             -07.00              -00.3077
871                             -06.50              -00.3006
872                             -06.00              -00.2959
873                             -05.00              -00.5617
874                             -04.50              -00.5227
875                             -04.00              -00.4756
876                             -03.50              -00.4263
877                             -03.00              -00.3749
878                             -02.50              -00.3222
879                             -02.00              -00.2688
880                             -01.50              -00.2161
881                             -01.00              -00.1632
882                             -00.50              -00.1098
883                             00.00               -00.0561
884                             00.50               -00.0020
885                             01.00               00.0514
886                             01.50               00.1055
887                             02.00               00.1589
888                             02.50               00.2125
889                             03.00               00.2662
890                             03.50               00.3197
891                             04.00               00.3731
892                             04.50               00.4266
893                             05.00               00.4802
894                             05.50               00.5336
895                             06.00               00.5866
896                             06.50               00.6397
897                             07.00               00.6969
898                             07.50               00.7557
899                             08.00               00.8120
900                             08.50               00.8674
901                             09.00               00.9248
902                             09.50               00.9786
903                             10.00               01.0125
904                             10.50               01.0622
905                             11.00               01.1118
906                             11.50               01.1604
907                             12.00               01.2085
908                             12.50               01.2551
909                             13.00               01.2977
910                             13.50               01.3406
911                             14.50               01.4541
912                             15.00               01.4801
913                             15.50               01.4923
914                             16.00               01.4907
915                             16.50               01.4843
916                             17.00               01.4685
917                             17.50               01.4449
918                             18.00               01.4084
919                             18.50               01.3750
920                             19.00               01.3418
921                             19.50               01.3171
922                             20.00               01.3046
923                             20.500      1.2871
924                             21.000      1.2780
925                             21.500      1.2577
926                             22.000      1.2528
927                             22.500      1.2474
928                             23.000      1.2305
929                             23.500      1.2253
930                             24.000      1.2132
931                             25.000      1.1513
932                             26.000      1.0598
933                             40              0.700000
934                         </tableData>
935                     </table>
936                 </product>
937             </function>
938
939
940
941
942
943             <axis name="LIFT">
944
945                 <function name="aero/coefficient/CLralpha">
946                     <description>wing_root_Lift_due_to_alpha</description>
947                     <product>
948                         <property>systems/crash-detect/aero-sw</property>
949                         <property>aero/qbar-psf</property>
950                         <property>metrics/Sw-sqft</property>
951                         <property>aero/function/kCLge</property>
952                         <property>aero/function/krootCLalpha</property>
953                         <value>0.80</value>
954                     </product>
955                 </function>
956
957                 <function name="aero/coefficient/CLtalpha">
958                     <description>wing_tip_Lift_due_to_alpha</description>
959                     <product>
960                         <property>systems/crash-detect/aero-sw</property>
961                         <property>aero/qbar-psf</property>
962                         <property>metrics/Sw-sqft</property>
963                         <property>aero/function/kCLge</property>
964                         <property>aero/function/ktipCLalpha</property>
965                         <property>systems/wings-fold/right-wing</property>
966                         <property>systems/wings-fold/left-wing</property>
967                         <property>fcs/wing-incidence-down</property>
968                         <value>0.20</value>
969                     </product>
970                 </function>
971
972
973                 <function name="aero/coefficient/CLtlealpha">
974                     <description>wing_tip_Lift_due_to_alpha</description>
975                     <product>
976                         <property>systems/crash-detect/aero-sw</property>
977                         <property>aero/qbar-psf</property>
978                         <property>metrics/Sw-sqft</property>
979                         <property>aero/function/kCLge</property>
980                         <property>aero/function/ktipLeCLalpha</property>
981                         <property>systems/wings-fold/right-wing</property>
982                         <property>systems/wings-fold/left-wing</property>
983                         <property>fcs/wing-incidence-up</property>
984                         <value>0.20</value>
985                     </product>
986                 </function>
987
988             <!--only UP or DOWN  of  Flaps  synchro with Wing incidence  Flap => 32 degres + wing => 8 deg  = 40-->
989             <!--===we want lft coef=1   at wing 8 deg ======= we have it ==>> 0.5 wings + 0.5 flap -->
990
991             <function name="aero/coefficient/dCLBLC">
992             <description>Delta_Lift_due_to_BLC</description>
993             <product>
994                 <property>systems/crash-detect/aero-sw</property>
995                 <property>aero/qbar-psf</property>
996                     <property>metrics/Sw-sqft</property>
997                     <property>systems/BLC/active</property>
998                     <!--<property>fcs/wings-pos-norm</property>-->
999                     <value> 0.20 </value>
1000             </product>
1001             </function>
1002
1003             <function name="aero/coefficient/dCLDlef">
1004                 <!--only with wing incidence to Zero-->
1005                 <description>Delta_Lift_due_to_leading_edge_flap_deflection</description>
1006                 <product>
1007                     <property>systems/crash-detect/aero-sw</property>
1008                     <property>aero/qbar-psf</property>
1009                     <property>metrics/Sw-sqft</property>
1010                     <table>
1011                         <independentVar lookup="row">fcs/leflap-pos-rad</independentVar>
1012                         <independentVar lookup="column">fcs/wings-pos-norm</independentVar>
1013                         <tableData>
1014                                                         0               1
1015                             0.0000      0.0000       0000
1016                             0.2100      0.0160       0000
1017
1018                         </tableData>
1019                     </table>
1020                 </product>
1021             </function>
1022             <function name="aero/coefficient/dCLsb">
1023                 <description>Delta_Lift_due_to_speedbrake</description>
1024                 <product>
1025                     <property>systems/crash-detect/aero-sw</property>
1026                     <property>aero/qbar-psf</property>
1027                     <property>metrics/Sw-sqft</property>
1028                     <property>fcs/speedbrake-pos-deg</property>
1029                     <value>0.0008</value>
1030                 </product>
1031             </function>
1032
1033            <!-- with efficiency due to wing incidence a guess must be fixed-->
1034             <function name="aero/coefficient/CLde">
1035                 <description>Lift_due_to_Elevator_Deflection</description>
1036                 <product>
1037                     <property>systems/crash-detect/aero-sw</property>
1038                     <property>aero/qbar-psf</property>
1039                     <property>metrics/Sw-sqft</property>
1040                     <sum>
1041                         <property>fcs/elevator-pos-rad</property>
1042                         <product>
1043                             <property>fcs/wings-pos-norm</property>
1044                             <value>-0.04</value><!---0.04-->
1045                         </product>
1046                     </sum>
1047                     <value>0.18</value>
1048                 </product>
1049             </function>
1050
1051             <!--<function name="aero/coefficient/buffet">
1052                 <description>Buffet at high alpha</description>
1053                 <product>
1054                     <property>systems/alpha_buffet/sine_wave</property>
1055                     <property>systems/alpha_buffet/strength</property>
1056                 </product>
1057             </function>-->
1058
1059         </axis>
1060
1061         <axis name="DRAG">
1062             <!--Doc NACA L51A02 page 25 and doc NACA RM N9A21 page 17
1063                     Mach 1.8 extrapolated-->
1064             <function name="aero/coefficient/CDclrmach">
1065                 <description>wing_root_Drag_due_to_CL_due_to_Mach</description>
1066                 <product>
1067                     <property>systems/crash-detect/aero-sw</property>
1068                     <property>aero/qbar-psf</property>
1069                     <property>metrics/Sw-sqft</property>
1070                     <property>aero/function/kCDge</property>
1071                     <property>systems/wing-drag_coeff</property> <!--value=1-->
1072                     <value>0.80</value>
1073                     <table name="drm">
1074                         <independentVar lookup="row">aero/function/krootCLalpha</independentVar>
1075                         <independentVar lookup="column">velocities/mach</independentVar>
1076                         <tableData>
1077
1078                                                         00.600000               00.875000               00.930000               01.200000           01.800000
1079                            -00.200000           00.010000               00.010000               00.030000               00.033000           00.026800
1080                            00.000000            00.006000               00.007000               00.020000               00.026000           00.023000
1081                            00.100000            00.006500               00.007000               00.021000               00.028000           00.026800
1082                            00.200000            00.010000               00.010000               00.027000               00.038000           00.030660
1083                            00.300000            00.020000               00.020000               00.040000               00.053000           00.042160
1084                            00.400000            00.030000               00.030000               00.050000               00.070000           00.053600
1085                            00.500000            00.050000               00.050000               00.070000               00.090000           00.069000
1086                            00.600000            00.090000               00.070000               00.090000               00.120000           00.092000
1087                            00.700000            00.150000               00.100000               00.120000               00.150000           00.115000
1088                            00.800000            00.220000               00.220000               00.160000               00.180000           00.138000
1089                         </tableData>
1090                     </table>
1091                 </product>
1092             </function>
1093             <function name="aero/coefficient/CDcltmach">
1094                 <description>wing_tip_Drag_due_to_CL_due_to_Mach</description>
1095                 <product>
1096                     <property>systems/crash-detect/aero-sw</property>
1097                     <property>aero/qbar-psf</property>
1098                     <property>metrics/Sw-sqft</property>
1099                     <property>aero/function/kCDge</property>
1100                     <property>systems/wing-drag_coeff</property> <!--value=1-->
1101                     <value>0.20</value>
1102                     <table name="dtm">
1103                         <independentVar lookup="row">aero/function/ktipCLalpha</independentVar>
1104                         <independentVar lookup="column">velocities/mach</independentVar>
1105                         <tableData>
1106
1107                             00.600000           00.875000               00.930000               01.200000           01.800000
1108                             -00.200000          00.010000               00.010000               00.030000               00.033000           00.026800
1109                             00.000000           00.006000               00.007000               00.020000               00.026000           00.023000
1110                             00.100000           00.006500               00.007000               00.021000               00.028000           00.026800
1111                             00.200000           00.010000               00.010000               00.027000               00.038000           00.030660
1112                             00.300000           00.020000               00.020000               00.040000               00.053000           00.042160
1113                             00.400000           00.030000               00.030000               00.050000               00.070000           00.053600
1114                             00.500000           00.050000               00.050000               00.070000               00.090000           00.069000
1115                             00.600000           00.090000               00.070000               00.090000               00.120000           00.092000
1116                             00.700000           00.150000               00.100000               00.120000               00.150000           00.115000
1117                             00.800000           00.220000               00.220000               00.160000               00.180000           00.138000
1118                         </tableData>
1119                     </table>
1120                 </product>
1121             </function>
1122
1123
1124             <function name="aero/coefficient/CDDlef">
1125                 <!--only with wing incidence to Zero-->
1126                 <description>Drag_due_to_leading_edge_flap_deflection</description>
1127                 <product>
1128                     <property>systems/crash-detect/aero-sw</property>
1129                     <property>aero/qbar-psf</property>
1130                     <property>metrics/Sw-sqft</property>
1131                     <property>fcs/leflap-pos-norm</property>
1132                     <table>
1133                         <independentVar>fcs/wings-pos-norm</independentVar>
1134                         <tableData>
1135                             0   0.0025
1136                             1   0.000
1137                         </tableData>
1138                     </table>
1139                     <value>0.0025</value>
1140                 </product>
1141             </function>
1142
1143             <function name="aero/coefficient/CDwing">
1144                 <description>Drag_due-to_wing_up</description>
1145                 <product>
1146                     <property>systems/crash-detect/aero-sw</property>
1147                     <property>aero/qbar-psf</property>
1148                     <property>metrics/Sw-sqft</property>
1149                     <property>fcs/wings-pos-norm</property>
1150                     <value>0.00500</value>
1151                 </product>
1152             </function>
1153
1154             <function name="aero/coefficient/CDgear">
1155                 <description>Drag_due_to_gear</description>
1156                 <product>
1157                     <property>systems/crash-detect/aero-sw</property>
1158                     <property>aero/qbar-psf</property>
1159                     <property>metrics/Sw-sqft</property>
1160                     <property>gear/unit[0]/pos-norm</property>
1161                     <property>gear/unit[1]/pos-norm</property>
1162                     <property>gear/unit[2]/pos-norm</property>
1163                     <value>0.0200</value>
1164                 </product>
1165             </function>
1166             <function name="aero/coefficient/CDsb">
1167                 <description>Drag_due_to_speedbrakes</description>
1168                 <product>
1169                     <property>systems/crash-detect/aero-sw</property>
1170                     <property>aero/qbar-psf</property>
1171                     <property>metrics/Sw-sqft</property>
1172                     <property>fcs/speedbrake-pos-deg</property>
1173                     <value>0.0010</value>
1174                 </product>
1175             </function>
1176             <function name="aero/coefficient/CDbeta">
1177                 <description>Drag_due_to_sideslip</description>
1178                 <product>
1179                     <property>systems/crash-detect/aero-sw</property>
1180                     <property>aero/qbar-psf</property>
1181                     <property>metrics/Sw-sqft</property>
1182                     <table>
1183                         <independentVar>aero/beta-rad</independentVar>
1184                         <tableData>
1185                             -1.5700     1.2000
1186                             -0.2600     0.0300
1187                             0.0000      0.0000
1188                             0.2600      0.0300
1189                             1.5700      1.2000
1190                         </tableData>
1191                     </table>
1192                 </product>
1193             </function>
1194             <function name="aero/coefficient/CDde">
1195                 <description>Drag_due_to_Elevator_Deflection</description>
1196                 <product>
1197                     <property>systems/crash-detect/aero-sw</property>
1198                     <property>aero/qbar-psf</property>
1199                     <property>metrics/Sw-sqft</property>
1200                     <table>
1201                         <independentVar lookup="row">fcs/elevator-pos-rad</independentVar>
1202                         <independentVar lookup="column">fcs/wings-pos-norm</independentVar>
1203                         <tableData>
1204                                             0           1
1205                             -0.35   0.02    0.0248
1206                                 0       0           0
1207                             0.35    0.02    0.0152
1208                         </tableData>
1209                     </table>
1210                 </product>
1211             </function>
1212
1213             <!--not realistic , only for animation with crash in water -->
1214             <function name="aero/coefficient/CDgear_water">
1215                 <description>Drag_due_to_crashing_with_gear_in_water</description>
1216                 <product>
1217                     <property>fcs/drag-gear-in-water-switch</property>
1218                     <table>
1219                         <independentVar>velocities/vc-kts</independentVar>
1220                         <tableData>
1221                             0     0
1222                             30    900
1223                             50    2700
1224                             90    10000
1225                             110  100000
1226                             220  10000000
1227                         </tableData>
1228                     </table>
1229                 </product>
1230             </function>
1231         </axis>
1232
1233
1234
1235         <axis name="ROLL">
1236             <function name="aero/coefficient/Clb">
1237                 <description>Roll_moment_due_to_beta</description>
1238                 <product>
1239                     <property>systems/crash-detect/aero-sw</property>
1240                     <property>aero/qbar-psf</property>
1241                     <property>metrics/Sw-sqft</property>
1242                     <property>metrics/bw-ft</property>
1243                     <property>aero/beta-rad</property>
1244                     <value>-0.0500</value>
1245                 </product>
1246             </function>
1247
1248             <!--Stall >>Spinning  temporary removed-->
1249             <!--<function name="aero/coefficient/Clalpha">
1250                 <description>Roll_moment_due_to_alpha</description>
1251                 <product>
1252                     <property>aero/qbar-psf</property>
1253                     <property>metrics/Sw-sqft</property>
1254                     <property>metrics/bw-ft</property>
1255                     <property>fcs/w_asym-coefficient</property>
1256                     <value>0.3</value>
1257                 </product>
1258             </function>-->
1259
1260             <!--Roll damping-->
1261             <function name="aero/coefficient/Clp">
1262                 <description>Roll_moment_due_to_roll_rate</description>
1263                 <product>
1264                     <property>systems/crash-detect/aero-sw</property>
1265                     <property>aero/qbar-psf</property>
1266                     <property>metrics/Sw-sqft</property>
1267                     <property>metrics/bw-ft</property>
1268                     <property>aero/bi2vel</property>
1269                     <property>velocities/p-aero-rad_sec</property>
1270                     <table>
1271                         <independentVar>fcs/wings-pos-norm</independentVar>
1272                         <tableData>
1273                             0   -0.6
1274                             1   -0.7
1275                         </tableData>
1276                     </table>
1277                 </product>
1278             </function>
1279             <function name="aero/coefficient/Clr">
1280                 <description>Roll_moment_due_to_yaw_rate</description>
1281                 <product>
1282                     <property>systems/crash-detect/aero-sw</property>
1283                     <property>aero/qbar-psf</property>
1284                     <property>metrics/Sw-sqft</property>
1285                     <property>metrics/bw-ft</property>
1286                     <property>aero/bi2vel</property>
1287                     <property>velocities/r-aero-rad_sec</property>
1288                     <table>
1289                         <independentVar>fcs/wings-pos-norm</independentVar>
1290                         <tableData>
1291                             0   0.07
1292                             1   0.05
1293                         </tableData>
1294                     </table>
1295                 </product>
1296             </function>
1297
1298             <function name="aero/coefficient/Clda">
1299                 <description>Roll_moment_due_to_aileron</description>
1300                 <product>
1301                     <property>systems/crash-detect/aero-sw</property>
1302                     <property>aero/qbar-psf</property>
1303                     <property>metrics/Sw-sqft</property>
1304                     <property>metrics/bw-ft</property>
1305                     <property>fcs/left-aileron-pos-rad</property>
1306                     <table>
1307                         <independentVar lookup="row">velocities/mach</independentVar>
1308                         <independentVar lookup="column">fcs/wings-pos-norm</independentVar>
1309
1310                         <tableData>
1311                                                   0                 1
1312                             0.0000      0.1100   0.1800
1313                             2.0000      0.0370    0.0370
1314                         </tableData>
1315                     </table>
1316                       <!--Stall >>Spinning, Lost of efficiency-->
1317                       <!--base FCS-Stall_Spin revoir le principe, raisonnement "marche d'escalier"-->
1318                     <!--<table>
1319                         <independentVar>fcs/w_asym-coefficient</independentVar>
1320                         <tableData>
1321                             0.0             1.0
1322                             0.002         0.7
1323                             0.010         0.2
1324                         </tableData>
1325                 </table>-->
1326
1327                 </product>
1328             </function>
1329             <function name="aero/coefficient/Cldr">
1330                 <description>Roll_moment_due_to_rudder</description>
1331                 <product>
1332                     <property>systems/crash-detect/aero-sw</property>
1333                     <property>aero/qbar-psf</property>
1334                     <property>metrics/Sw-sqft</property>
1335                     <property>metrics/bw-ft</property>
1336                     <property>fcs/rudder-pos-rad</property>
1337                     <table>
1338                         <independentVar>fcs/wings-pos-norm</independentVar>
1339                         <tableData>
1340                             0   0.01
1341                             1   0.01
1342                         </tableData>
1343                     </table>
1344                 </product>
1345             </function>
1346         </axis>
1347
1348         <axis name="PITCH">
1349             <function name="aero/coefficient/Cmralpha">
1350                 <description>wing_root_Pitch_moment_due_to_alpha</description>
1351                 <product>
1352                     <property>systems/crash-detect/aero-sw</property>
1353                     <property>aero/qbar-psf</property>
1354                     <property>metrics/Sw-sqft</property>
1355                     <property>metrics/cbarw-ft</property>
1356                     <value>0.80</value>
1357                     <table name="prm">
1358                        <independentVar lookup="row">aero/alpha-deg</independentVar>
1359                         <independentVar lookup="column">fcs/wings-pos-norm</independentVar>
1360                           <tableData>
1361                                                             0.0000                   1.0000
1362                         -15.00000               00.05190                00.03285
1363                         -14.50000               00.04880                00.02995
1364                         -14.00000               00.04580                00.02718
1365                         -13.50000               00.04280                00.02440
1366                         -13.00000               00.03980                00.02165
1367                         -12.50000               00.03680                00.01890
1368                         -12.00000               00.03370                00.01610
1369                         -11.50000               00.03080                00.01355
1370                         -11.00000               00.02790                00.01108
1371                         -10.50000               00.02460                00.00840
1372                         -10.00000               00.02110                00.00615
1373                         -09.50000               00.01750                00.00298
1374                         -09.00000               00.01330                -00.00160
1375                         -08.50000               00.00820                -00.00765
1376                         -08.00000               -00.00180               -00.01933
1377                         -07.50000               -00.00850               -00.02880
1378                         -07.00000               -00.01140               -00.03623
1379                         -06.50000               -00.01170               -00.06893
1380                         -06.00000               -00.00990               -00.06720
1381                         -05.50000               -00.00640               -00.06324
1382                         -05.00000               -00.00350               -00.06028
1383                         -04.50000               00.00060                -00.05585
1384                         -04.00000               00.00070                -00.05555
1385                         -03.50000               00.00070                -00.05523
1386                         -03.00000               00.00070                -00.05493
1387                         -02.50000               00.00070                -00.05460
1388                         -02.00000               00.00060                -00.05438
1389                         -01.50000               00.00040                -00.05423
1390                         -01.00000               00.00030                -00.05400
1391                         -00.50000               00.00010                -00.05388
1392                         00.00000                00.00000                -00.05369
1393                         00.50000                -00.00010               -00.05343
1394                         01.00000                -00.00030               -00.05338
1395                         01.50000                -00.00040               -00.05308
1396                         02.00000                -00.00060               -00.05196
1397                         02.50000                -00.00070               -00.05075
1398                         03.00000                -00.00070               -00.04944
1399                         03.50000                -00.00070               -00.04813
1400                         04.00000                -00.00070               -00.04682
1401                         04.50000                -00.00060               -00.04541
1402                         05.00000                00.00210                -00.04140
1403                         05.50000                00.00370                -00.03763
1404                         06.00000                00.00990                -00.02988
1405                         06.50000                00.01170                -00.02730
1406                         07.00000                00.01140                -00.02778
1407                         07.50000                00.00840                -00.03255
1408                         08.00000                00.00150                -00.04298
1409                         08.50000                -00.00850               -00.05605
1410                         09.00000                -00.01360               -00.06313
1411                         09.50000                -00.01790               -00.06910
1412                         10.00000                -00.02150               -00.07420
1413                         10.50000                -00.02510               -00.07918
1414                         11.00000                -00.02840               -00.08375
1415                         11.50000                -00.03130               -00.08788
1416                         12.00000                -00.03430               -00.09205
1417                         12.50000                -00.03740               -00.09628
1418                         13.00000                -00.04040               -00.10035
1419                         13.50000                -00.04340               -00.10438
1420                         14.00000                -00.04660               -00.10950
1421                         14.50000                -00.05020               -00.11430
1422                         15.00000                -00.05440               -00.12008
1423                         </tableData>
1424                     </table>
1425                 </product>
1426             </function>
1427
1428             <function name="aero/coefficient/Cmtalpha">
1429                 <description>wing_tip_Pitch_moment_due_to_alpha</description>
1430                 <product>
1431                     <property>systems/crash-detect/aero-sw</property>
1432                     <property>aero/qbar-psf</property>
1433                     <property>metrics/Sw-sqft</property>
1434                     <property>metrics/cbarw-ft</property>
1435                     <value>0.20</value>
1436                     <table name="ptm">
1437                         <independentVar>aero/alpha-wing-deg</independentVar>
1438                           <tableData>
1439                             -14       -0.01885384
1440                             -13       -0.03842179
1441                             -12       -0.02174873
1442                             -11       -0.01266822
1443                             -10      -0.004588366
1444                             -9       0.003576898
1445                             -8       0.006921423
1446                             -7       0.003330527
1447                             -6       0.001301623
1448                             -5      -0.002568254
1449                             -4       -0.00460672
1450                             -3      -0.008935088
1451                             -2      -0.006526491
1452                             -1      -0.003054819
1453                             0      2.357382e-10
1454                             1       0.003054819
1455                             2       0.006526512
1456                             3       0.008934981
1457                             4         0.0046044
1458                             5       0.002562999
1459                             6      -0.001308367
1460                             7      -0.003343697
1461                             8      -0.006937832
1462                             9      -0.003568542
1463                             10       0.004593342
1464                             11        0.01266149
1465                             12        0.02171153
1466                             13        0.03796354
1467                             14        0.01796081
1468                             15       0.005273767
1469                             16       -0.01673217
1470                             17       -0.04267304
1471                             18       -0.04918116
1472                             19       -0.05542727
1473                             20        -0.0618301
1474                             21       -0.06806703
1475                             22       -0.07413074
1476                         </tableData>
1477                     </table>
1478                 </product>
1479             </function>
1480
1481
1482
1483             <function name="aero/coefficient/Cmfalpha">
1484                 <description>fuse_Pitch_moment_due_to_alpha</description>
1485                 <product>
1486                     <property>systems/crash-detect/aero-sw</property>
1487                     <property>aero/qbar-psf</property>
1488                     <property>metrics/Sw-sqft</property>
1489                     <property>metrics/cbarw-ft</property>
1490                     <property>aero/alpha-rad</property>
1491                     <value>-0.008</value>
1492                 </product>
1493              </function>
1494
1495             <function name="aero/coefficient/Cmde">
1496                 <description>Pitch_moment_due_to_elevator</description>
1497                 <product>
1498                     <property>systems/crash-detect/aero-sw</property>
1499                     <property>aero/qbar-psf</property>
1500                     <property>metrics/Sw-sqft</property>
1501                     <property>metrics/cbarw-ft</property>
1502                     <property>fcs/elevator-pos-rad</property>
1503                       <table>
1504                           <independentVar>velocities/mach</independentVar>
1505                           <tableData>
1506                               0.0000    -0.950
1507                               2.0000    -0.250
1508                           </tableData>
1509                       </table>
1510                 </product>
1511             </function>
1512
1513             <function name="aero/coefficient/Cmgear">
1514                 <description>Pitch_due_to_gear</description>
1515                 <product>
1516                     <property>aero/qbar-psf</property>
1517                     <property>metrics/Sw-sqft</property>
1518                     <property>gear/unit[0]/pos-norm</property>
1519                     <property>gear/unit[1]/pos-norm</property>
1520                     <property>gear/unit[2]/pos-norm</property>
1521                     <value>-0.0600</value>
1522                 </product>
1523             </function>
1524             <function name="aero/coefficient/Cmq">
1525                 <description>Pitch_moment_due_to_pitch_rate</description>
1526                 <product>
1527                     <property>systems/crash-detect/aero-sw</property>
1528                     <property>aero/qbar-psf</property>
1529                     <property>metrics/Sw-sqft</property>
1530                     <property>metrics/cbarw-ft</property>
1531                     <property>aero/ci2vel</property>
1532                     <property>velocities/q-aero-rad_sec</property>
1533                     <table>                       
1534                         <independentVar lookup="row">fcs/wings-pos-norm</independentVar>
1535                         <independentVar lookup="column">velocities/mach</independentVar>
1536                         <tableData>
1537                                     0.00        2.00
1538                             0   -45.0      -75.0
1539                             1   -32.0      -32.0
1540                         </tableData>
1541                     </table>
1542                 </product>
1543             </function>
1544
1545             <function name="aero/coefficient/Cmadot">
1546                 <description>Pitch_moment_due_to_alpha_rate</description>
1547                 <product>
1548                     <property>systems/crash-detect/aero-sw</property>
1549                     <property>aero/qbar-psf</property>
1550                     <property>metrics/Sw-sqft</property>
1551                     <property>metrics/cbarw-ft</property>
1552                     <property>aero/ci2vel</property>
1553                     <property>aero/alphadot-rad_sec</property>
1554                     <table>
1555                         <independentVar>fcs/wings-pos-norm</independentVar>
1556                         <tableData>
1557                             0   -10.8
1558                             1   -12.7
1559                         </tableData>
1560                     </table>
1561                 </product>
1562             </function>
1563
1564            <!-- <function name="aero/coefficient/Cmthr">
1565                 <description>Pitch_moment_due_to_thrust</description>
1566                 <product>
1567                     <property>propulsion/engine/thrust-lbs</property>
1568                     <table>
1569                         <independentVar>fcs/wings-pos-norm</independentVar>
1570                         <tableData>
1571                             0   0.000
1572                             1   0.01
1573                         </tableData>
1574                     </table>
1575                 </product>
1576             </function>-->
1577         </axis>
1578
1579         <axis name="YAW">
1580             <function name="aero/coefficient/Cnb">
1581                 <description>Yaw_moment_due_to_beta</description>
1582                 <product>
1583                     <property>systems/crash-detect/aero-sw</property>
1584                     <property>aero/qbar-psf</property>
1585                     <property>metrics/Sw-sqft</property>
1586                     <property>metrics/bw-ft</property>
1587                     <property>aero/beta-rad</property>
1588                     <value>0.12</value>
1589                 </product>
1590             </function>
1591
1592             <!--Stall >>Spinning-->
1593            <!-- <function name="aero/coefficient/Cnalpha">
1594                 <description>Yaw_moment_due_to_alpha</description>
1595                 <product>
1596                     <property>aero/qbar-psf</property>
1597                     <property>metrics/Sw-sqft</property>
1598                     <property>metrics/bw-ft</property>
1599                     <property>fcs/w_asym-coefficient</property>
1600                 </product>
1601             </function>-->
1602
1603             <function name="aero/coefficient/Cnr">
1604                 <description>Yaw_moment_due_to_yaw_rate</description>
1605                 <product>
1606                     <property>systems/crash-detect/aero-sw</property>
1607                     <property>aero/qbar-psf</property>
1608                     <property>metrics/Sw-sqft</property>
1609                     <property>metrics/bw-ft</property>
1610                     <property>aero/bi2vel</property>
1611                     <property>velocities/r-aero-rad_sec</property>
1612                     <table>
1613                         <independentVar>fcs/wings-pos-norm</independentVar>
1614                         <tableData>
1615                             0   -15.000
1616                             1   -20.000
1617                         </tableData>
1618                     </table>
1619                 </product>
1620             </function>
1621
1622             <!--FIXME getting trouble with it-->
1623             <function name="aero/coefficient/Cnp">
1624                 <description>Yaw_moment_due_to_roll_rate</description>
1625                 <product>
1626                     <property>systems/crash-detect/aero-sw</property>
1627                     <property>aero/qbar-psf</property>
1628                     <property>metrics/Sw-sqft</property>
1629                     <property>metrics/bw-ft</property>
1630                     <property>aero/bi2vel</property>
1631                     <property>velocities/p-aero-rad_sec</property>
1632                     <!--<value>-0.030</value>-->
1633                     <value>-0.00</value>
1634                 </product>
1635             </function>
1636             <function name="aero/coefficient/Cndr">
1637                 <description>Yaw_moment_due_to_rudder</description>
1638                 <product>
1639                     <property>systems/crash-detect/aero-sw</property>
1640                     <property>aero/qbar-psf</property>
1641                     <property>metrics/Sw-sqft</property>
1642                     <property>metrics/bw-ft</property>
1643                     <property>fcs/rudder-pos-rad</property>
1644                     <value>-0.1200</value>
1645                 </product>
1646             </function>
1647             <function name="aero/coefficient/Cnda">
1648                 <description>Adverse_yaw</description>
1649                 <product>
1650                     <property>systems/crash-detect/aero-sw</property>
1651                     <property>aero/qbar-psf</property>
1652                     <property>metrics/Sw-sqft</property>
1653                     <property>metrics/bw-ft</property>
1654                     <property>fcs/left-aileron-pos-rad</property>
1655                     <value>0.0000</value>
1656                 </product>
1657             </function>
1658         </axis>
1659
1660     </aerodynamics>
1661
1662
1663      <external_reactions>
1664
1665         <force name="catapult" frame="LOCAL">
1666             <location unit="IN">
1667                 <x>  -30 </x>
1668                 <y>    0.0 </y>
1669                 <z>  -39.0 </z>
1670             </location>
1671             <direction>
1672                 <x>1</x>
1673                 <y>0</y>
1674                 <z>0.08</z>
1675             </direction>
1676         </force>
1677
1678        
1679         
1680         <!--Catapult   vertical force when necessary to keep the right position on the catapult rail-->
1681         <force name="cat-hold" frame="BODY">
1682         <location unit="IN">
1683             <x>  -30 </x>
1684             <y>    0.0 </y>
1685             <z>  -39.0 </z>
1686         </location>
1687         <direction>
1688             <x>0</x>
1689             <y>0</y>
1690             <z>1 </z>
1691         </direction>
1692         </force>
1693
1694         <force name="holdback" frame="BODY">
1695         <location unit="IN">
1696             <x> 211</x>
1697             <y>    0.0 </y>
1698             <z>  -39.0 </z>
1699         </location>
1700         <direction>
1701             <x>   -1.0 </x>
1702             <y>    0.0 </y>
1703             <z>    -0.15 </z>
1704         </direction>
1705         </force>
1706
1707         
1708         <force name="hook" frame="BODY">
1709         <location unit="IN">
1710             <x> 100 </x>
1711             <y> 0.0 </y>
1712             <z>  -15.0 </z>
1713         </location>
1714         <direction>
1715             <x>  -1  </x>
1716             <y>0</y>
1717             <z>   0.1</z>
1718         </direction>
1719         </force>
1720
1721         <force name="mule" frame="BODY">
1722         <location unit="IN">
1723             <x>  -139 </x>
1724             <y>    0.0 </y>
1725             <z>  -71.0 </z>
1726         </location>
1727         <direction>
1728             <x>1</x>
1729             <y>0</y>
1730             <z>0</z>
1731         </direction>
1732         </force>
1733
1734         <force name="taxi" frame="BODY">
1735             <location unit="IN">
1736                 <x>  -139 </x>
1737                 <y>    0.0 </y>
1738                 <z>  -71.0 </z>
1739             </location>
1740             <direction>
1741                 <x>1</x>
1742                 <y>0</y>
1743                 <z>0.3</z>
1744             </direction>
1745         </force>
1746
1747         <force name="cp1-bellydragx" frame="BODY">
1748             <location unit="IN">
1749                 <x>  0 </x>
1750                 <y>  0.0 </y>
1751                 <z>  -5 </z>
1752             </location>
1753             <direction>
1754                 <x>-1</x>
1755                 <y>0</y>
1756                 <z>0.1</z>
1757             </direction>
1758         </force>
1759
1760         <force name="nose-gear" frame="BODY">
1761             <location unit="IN">
1762                 <x> -139.76 </x>
1763                 <y> 0 </y>
1764                 <z> -81.6 </z>
1765             </location>
1766             <direction>
1767                 <x>1</x>
1768                 <y>0</y>
1769                 <z>0</z>
1770             </direction>
1771         </force>
1772         <force name="left-gear" frame="BODY">
1773             <location unit="IN">
1774                 <x> 82.44 </x>
1775                 <y> -58.03 </y>
1776                 <z> -65.75 </z>
1777             </location>
1778             <direction>
1779                 <x>1</x>
1780                 <y>0</y>
1781                 <z>0</z>
1782             </direction>
1783         </force>
1784         <force name="right-gear" frame="BODY">
1785             <location unit="IN">
1786                 <x> 82.44 </x>
1787                 <y> 58.03 </y>
1788                 <z> -65.75 </z>
1789             </location>
1790             <direction>
1791                 <x>1</x>
1792                 <y>0</y>
1793                 <z>0</z>
1794             </direction>
1795         </force>
1796         <force name="nose-gear-bump" frame="BODY">
1797             <location unit="IN">
1798                 <x> -139.76 </x>
1799                 <y> 0 </y>
1800                 <z> -81.6 </z>
1801             </location>
1802             <direction>
1803                 <x>0</x>
1804                 <y>0</y>
1805                 <z>-1</z>
1806             </direction>
1807         </force>
1808         <force name="left-gear-bump" frame="BODY">
1809             <location unit="IN">
1810                 <x> 82.44 </x>
1811                 <y> -58.03 </y>
1812                 <z> -65.75 </z>
1813             </location>
1814             <direction>
1815                 <x>0</x>
1816                 <y>0</y>
1817                 <z>1</z>
1818             </direction>
1819         </force>
1820         <force name="right-gear-bump" frame="BODY">
1821             <location unit="IN">
1822                 <x> 82.44 </x>
1823                 <y> 58.03 </y>
1824                 <z> -65.75 </z>
1825             </location>
1826             <direction>
1827                 <x>0</x>
1828                 <y>0</y>
1829                 <z>1</z>
1830             </direction>
1831         </force>
1832
1833         <force name="fusedragx" frame="BODY">
1834             <location unit="IN">
1835                 <x>  0 </x>
1836                 <y>  0.0 </y>
1837                 <z>  0 </z>
1838             </location>
1839             <direction>
1840                 <x>-1</x>
1841                 <y>0</y>
1842                 <z>0.1</z>
1843             </direction>
1844         </force>
1845
1846         <force name="catapult_free" frame="BODY">
1847             <location unit="IN">
1848                 <x> -30.0 </x>
1849                 <y>  0.0 </y>
1850                 <z>  0 </z>
1851             </location>
1852             <direction>
1853                 <x> 1</x>
1854                 <y>  0 </y>
1855                 <z> 0.35 </z>
1856             </direction>
1857         </force>
1858
1859         <force name="holdback_free" frame="BODY">
1860             <location unit="IN">
1861                 <x> 40 </x>
1862                 <y>  0.0 </y>
1863                 <z>  -20.0 </z>
1864             </location>
1865             <direction>
1866                 <x>   -1.0 </x>
1867                 <y>    0.0 </y>
1868                 <z>    0.0 </z>
1869             </direction>
1870         </force>
1871
1872
1873         <force name="crash-force" frame="LOCAL">
1874             <location unit="IN">
1875                 <x> 0 </x>
1876                 <y>  0 </y>
1877                 <z> 0 </z>
1878             </location>
1879             <direction>
1880                 <x>   0 </x>
1881                 <y>    0.0 </y>
1882                 <z>    1.0 </z>
1883             </direction>
1884         </force>
1885
1886         <force name="crash-force-y" frame="BODY">
1887             <location unit="IN">
1888                 <x> 0 </x>
1889                 <y>  10 </y>
1890                 <z> 0 </z>
1891             </location>
1892             <direction>
1893                 <x>   0 </x>
1894                 <y>    0.0 </y>
1895                 <z>    1.0 </z>
1896             </direction>
1897         </force>
1898
1899         <force name="crash-force-x" frame="BODY">
1900             <location unit="IN">
1901                 <x> 100 </x>
1902                 <y>  0 </y>
1903                 <z> 0 </z>
1904             </location>
1905             <direction>
1906                 <x>   0 </x>
1907                 <y>    0.0 </y>
1908                 <z>    1.0 </z>
1909             </direction>
1910         </force>
1911
1912         <!--ONLY FOR TESTING-->
1913         <force name="testing1" frame="BODY">
1914             <location unit="IN">
1915                 <x>200</x>
1916                 <y>  0 </y>
1917                 <z> 0 </z>
1918             </location>
1919             <direction>
1920                 <x>   0 </x>
1921                 <y>    0.0 </y>
1922                 <z>    -1.0 </z>
1923             </direction>
1924         </force>
1925         <!--ONLY FOR TESTING-->
1926         <force name="testing2" frame="BODY">
1927             <location unit="IN">
1928                 <x>-36</x>
1929                 <y>  0 </y>
1930                 <z> 0 </z>
1931             </location>
1932             <direction>
1933                 <x>   0 </x>
1934                 <y>    0.0 </y>
1935                 <z>    -1.0 </z>
1936             </direction>
1937         </force>
1938         <!--ONLY FOR TESTING-->
1939         <force name="testing3" frame="BODY">
1940             <location unit="IN">
1941                 <x>72</x>
1942                 <y> -200 </y>
1943                 <z> 0 </z>
1944             </location>
1945             <direction>
1946                 <x>   0 </x>
1947                 <y>    0.0 </y>
1948                 <z>    -1.0 </z>
1949             </direction>
1950         </force>
1951         <!--ONLY FOR TESTING-->
1952         <force name="testing4" frame="BODY">
1953             <location unit="IN">
1954                 <x>72</x>
1955                 <y> 200 </y>
1956                 <z> 0 </z>
1957             </location>
1958             <direction>
1959                 <x>   0 </x>
1960                 <y>    0.0 </y>
1961                 <z>    -1.0 </z>
1962             </direction>
1963         </force>
1964
1965
1966
1967  </external_reactions>
1968
1969 </fdm_config>