forked from FGMEMBERS/f16
-
Notifications
You must be signed in to change notification settings - Fork 0
/
yf16.xml
3331 lines (3121 loc) · 183 KB
/
yf16.xml
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27
28
29
30
31
32
33
34
35
36
37
38
39
40
41
42
43
44
45
46
47
48
49
50
51
52
53
54
55
56
57
58
59
60
61
62
63
64
65
66
67
68
69
70
71
72
73
74
75
76
77
78
79
80
81
82
83
84
85
86
87
88
89
90
91
92
93
94
95
96
97
98
99
100
101
102
103
104
105
106
107
108
109
110
111
112
113
114
115
116
117
118
119
120
121
122
123
124
125
126
127
128
129
130
131
132
133
134
135
136
137
138
139
140
141
142
143
144
145
146
147
148
149
150
151
152
153
154
155
156
157
158
159
160
161
162
163
164
165
166
167
168
169
170
171
172
173
174
175
176
177
178
179
180
181
182
183
184
185
186
187
188
189
190
191
192
193
194
195
196
197
198
199
200
201
202
203
204
205
206
207
208
209
210
211
212
213
214
215
216
217
218
219
220
221
222
223
224
225
226
227
228
229
230
231
232
233
234
235
236
237
238
239
240
241
242
243
244
245
246
247
248
249
250
251
252
253
254
255
256
257
258
259
260
261
262
263
264
265
266
267
268
269
270
271
272
273
274
275
276
277
278
279
280
281
282
283
284
285
286
287
288
289
290
291
292
293
294
295
296
297
298
299
300
301
302
303
304
305
306
307
308
309
310
311
312
313
314
315
316
317
318
319
320
321
322
323
324
325
326
327
328
329
330
331
332
333
334
335
336
337
338
339
340
341
342
343
344
345
346
347
348
349
350
351
352
353
354
355
356
357
358
359
360
361
362
363
364
365
366
367
368
369
370
371
372
373
374
375
376
377
378
379
380
381
382
383
384
385
386
387
388
389
390
391
392
393
394
395
396
397
398
399
400
401
402
403
404
405
406
407
408
409
410
411
412
413
414
415
416
417
418
419
420
421
422
423
424
425
426
427
428
429
430
431
432
433
434
435
436
437
438
439
440
441
442
443
444
445
446
447
448
449
450
451
452
453
454
455
456
457
458
459
460
461
462
463
464
465
466
467
468
469
470
471
472
473
474
475
476
477
478
479
480
481
482
483
484
485
486
487
488
489
490
491
492
493
494
495
496
497
498
499
500
501
502
503
504
505
506
507
508
509
510
511
512
513
514
515
516
517
518
519
520
521
522
523
524
525
526
527
528
529
530
531
532
533
534
535
536
537
538
539
540
541
542
543
544
545
546
547
548
549
550
551
552
553
554
555
556
557
558
559
560
561
562
563
564
565
566
567
568
569
570
571
572
573
574
575
576
577
578
579
580
581
582
583
584
585
586
587
588
589
590
591
592
593
594
595
596
597
598
599
600
601
602
603
604
605
606
607
608
609
610
611
612
613
614
615
616
617
618
619
620
621
622
623
624
625
626
627
628
629
630
631
632
633
634
635
636
637
638
639
640
641
642
643
644
645
646
647
648
649
650
651
652
653
654
655
656
657
658
659
660
661
662
663
664
665
666
667
668
669
670
671
672
673
674
675
676
677
678
679
680
681
682
683
684
685
686
687
688
689
690
691
692
693
694
695
696
697
698
699
700
701
702
703
704
705
706
707
708
709
710
711
712
713
714
715
716
717
718
719
720
721
722
723
724
725
726
727
728
729
730
731
732
733
734
735
736
737
738
739
740
741
742
743
744
745
746
747
748
749
750
751
752
753
754
755
756
757
758
759
760
761
762
763
764
765
766
767
768
769
770
771
772
773
774
775
776
777
778
779
780
781
782
783
784
785
786
787
788
789
790
791
792
793
794
795
796
797
798
799
800
801
802
803
804
805
806
807
808
809
810
811
812
813
814
815
816
817
818
819
820
821
822
823
824
825
826
827
828
829
830
831
832
833
834
835
836
837
838
839
840
841
842
843
844
845
846
847
848
849
850
851
852
853
854
855
856
857
858
859
860
861
862
863
864
865
866
867
868
869
870
871
872
873
874
875
876
877
878
879
880
881
882
883
884
885
886
887
888
889
890
891
892
893
894
895
896
897
898
899
900
901
902
903
904
905
906
907
908
909
910
911
912
913
914
915
916
917
918
919
920
921
922
923
924
925
926
927
928
929
930
931
932
933
934
935
936
937
938
939
940
941
942
943
944
945
946
947
948
949
950
951
952
953
954
955
956
957
958
959
960
961
962
963
964
965
966
967
968
969
970
971
972
973
974
975
976
977
978
979
980
981
982
983
984
985
986
987
988
989
990
991
992
993
994
995
996
997
998
999
1000
<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="General Dynamics YF-16" version="2.0" release="ALPHA"
xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">
<fileheader>
<author> Erik Hofman, Nikolai V. Chr. </author>
<filecreationdate> 2001-12-28 </filecreationdate>
<version> $Revision: 1.93 $ </version>
<license>
<licenseName>GPL (General Public License)</licenseName>
<licenseURL>http://www.gnu.org/licenses/gpl.html</licenseURL>
</license>
<description> Models an YF-16 </description>
<note>
This model was created using data that is, or has been, publically
available by means of technical reports, textbooks, image graphs or
published code. This aircraft description file is in no way related
to the manufacturer of the real aircraft.
Neither the name of (any of) the authors nor the names of (any of) the
manufacturers may be used to endorse or promote products derived from
this file.
The data is provided ''as is'' and any express or implied
warranties, including, but not limitted to the implied warranties of
merchantability and fitness for a particular purpose are disclaimed.
</note>
<reference refID="ISBN 0-7232-3458-2" author="William Green" title="General Dynamics F-16 Dash-1" date="1987"/>
<reference refID="NASA TP-1538" author="Nguyen, L. T.; Ogburn, M. E.; Gilbert, W. P.; Kibler, K. S.; Brown, P. W.; Deal, P. L."
title="Simulator study of stall/post-stall characteristics of a fighter airplane with relaxed longitudinal static stability." date="12/1979"/>
<reference refID="AD A 055417" author="Marchand,Michael A" title="Pitch Rate Flight Control for the F-16 Aircraft to Improve Air-To-Air Combat" date="Dec 1977"/>
<reference refID="AD A 189675" author="Kassan, Mark W" title="F-16 Simulator for Man-in-the-Loop Testing of Aircraft Control Systems (SIMTACS)" date="Dec 1987"/>
<reference refID="AFD-070827-032" author="Goddard and Lemm" title="Simulation of the F-16 Lantirn Automatic Terrain Avoidance System" date="Aug 1986"/>
<reference refID="NASA TN-D-8176" author="Gilbert, W. P.; Nguyen, L. T.; Vangunst, R. W."
title="Simulator study of the effectiveness of an automatic control system designed to improve the high-angle-of-attack characteristics of a fighter airplane" date="1976"/>
<reference refID="NASA TP-2857" author="Dale A. Mackall" title="Development and flight test experiences with a flight-crucial digital control system" date="1988"/>
<reference refID="PW-100 Engine" author="Elodie Roux" title="Turbofan and Turbojet Engines: Database Handbook" date="2007"/>
<reference refID="Manual" author="Lockheed Martin" title="F-16C/D Block 50 Flight Manual" date="2 December 1996"/>
<reference refID="Youtube video showing speed brake actuation time (2 secs)" author="MultiplyLeadership's channel"
title="Air-to-air chase video of F-16 AB light off FTT" date="Oct 20, 2010"/>
<reference refID="None" author="Richard Murray" title="http://www.cds.caltech.edu/~murray/projects/afosr95-vehicles/models/f16/" date="n/a"/>
<reference refID="H-1999" author="NASA" title="Dynamic ground effects flight test of an F-15 aircraft" date="n/a"/>
<reference refID="H-2177" author="NASA" title="Dynamic ground effect for a Cranked Arrow Wing Airplane" date="n/a"/>
<reference refID="None" author="n/a" title="http://www.codeonemagazine.com/archives/1991/articles/jul_91/july2a_91.html" date="n/a"/>
<reference refID="F16i post stall" author="Moshe Medina" title="Post stall characteristics of highly augmented fighter aircraft" date="n/a"/>
</fileheader>
<metrics>
<wingarea unit="FT2"> 300 </wingarea>
<wingspan unit="FT"> 30 </wingspan>
<chord unit="FT"> 11.32 </chord>
<htailarea unit="FT2"> 63.7 </htailarea>
<htailarm unit="FT"> 16.46 </htailarm>
<vtailarea unit="FT2"> 54.75 </vtailarea>
<vtailarm unit="FT"> 0 </vtailarm>
<location name="AERORP" unit="IN">
<x> -198.4336 </x><!-- -198.4336 = static margin of -0.04 -->
<y> 0 </y>
<z> 0 </z>
</location>
<location name="EYEPOINT" unit="IN">
<x> -336.2 </x>
<y> 0 </y>
<z> 29.5 </z>
</location>
<location name="VRP" unit="IN">
<x> -180 </x>
<y> 0 </y>
<z> 0 </z>
</location>
</metrics>
<mass_balance>
<ixx unit="SLUG*FT2"> 9496 </ixx>
<iyy unit="SLUG*FT2"> 55814 </iyy>
<izz unit="SLUG*FT2"> 63100 </izz>
<ixy unit="SLUG*FT2"> 0 </ixy>
<ixz unit="SLUG*FT2"> 982 </ixz>
<iyz unit="SLUG*FT2"> 0 </iyz>
<emptywt unit="LBS"> 17400 </emptywt>
<location name="CG" unit="IN">
<x> -193 </x>
<y> 0 </y>
<z> 0 </z>
</location>
<pointmass name="Pilot">
<weight unit="LBS"> 159 </weight>
<location name="POINTMASS" unit="IN">
<x> -336.2 </x>
<y> 0 </y>
<z> 0 </z>
</location>
</pointmass>
</mass_balance>
<ground_reactions>
<contact type="BOGEY" name="NOSE_LG">
<location unit="IN">
<x> -299.6 </x>
<y> 0 </y>
<z> -72 </z>
</location>
<static_friction> 0.8 </static_friction>
<dynamic_friction> 0.5 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 17250 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 4250 </damping_coeff>
<max_steer unit="DEG"> 32 </max_steer><!-- as per manual -->
<brake_group> NOSE </brake_group>
<retractable>1</retractable>
</contact>
<contact type="BOGEY" name="LEFT_MLG">
<location unit="IN">
<x> -158.6 </x>
<y> -48 </y>
<z> -71.6 </z>
</location>
<static_friction> 0.8 </static_friction>
<dynamic_friction> 0.5 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 37500 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 7500 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> LEFT </brake_group>
<retractable>1</retractable>
</contact>
<contact type="BOGEY" name="RIGHT_MLG">
<location unit="IN">
<x> -158.6 </x>
<y> 48 </y>
<z> -71.6 </z>
</location>
<static_friction> 0.8 </static_friction>
<dynamic_friction> 0.5 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 37500 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 7500 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> RIGHT </brake_group>
<retractable>1</retractable>
</contact>
<contact type="STRUCTURE" name="LEFT_WT">
<location unit="IN">
<x> -121.3 </x>
<y> -189 </y>
<z> 0 </z>
</location>
<static_friction> 5.0 </static_friction>
<dynamic_friction> 4.0 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
<damping_coeff_rebound unit="LBS/FT/SEC"> 40000 </damping_coeff_rebound>
</contact>
<contact type="STRUCTURE" name="RIGHT_WT">
<location unit="IN">
<x> -121.3 </x>
<y> 189 </y>
<z> 0 </z>
</location>
<static_friction> 5.0 </static_friction>
<dynamic_friction> 4.0 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
<damping_coeff_rebound unit="LBS/FT/SEC"> 40000 </damping_coeff_rebound>
</contact>
<contact type="STRUCTURE" name="TOP_VS">
<location unit="IN">
<x> -27.2 </x>
<y> 0 </y>
<z> 123.2 </z>
</location>
<static_friction> 5.0 </static_friction>
<dynamic_friction> 4.0 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
<damping_coeff_rebound unit="LBS/FT/SEC"> 40000 </damping_coeff_rebound>
</contact>
<contact type="STRUCTURE" name="LEFT_VFT">
<location unit="IN">
<x> -97.6 </x>
<y> -24.8 </y>
<z> -52 </z>
</location>
<static_friction> 5.0 </static_friction>
<dynamic_friction> 4.0 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
<damping_coeff_rebound unit="LBS/FT/SEC"> 40000 </damping_coeff_rebound>
</contact>
<contact type="STRUCTURE" name="RIGHT_VFT">
<location unit="IN">
<x> -97.6 </x>
<y> 24.8 </y>
<z> -52 </z>
</location>
<static_friction> 5.0 </static_friction>
<dynamic_friction> 4.0 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
<damping_coeff_rebound unit="LBS/FT/SEC"> 40000 </damping_coeff_rebound>
</contact>
<contact type="STRUCTURE" name="INTAKE">
<location unit="IN">
<x> -322.4 </x>
<y> 0 </y>
<z> -36.6 </z>
</location>
<static_friction> 5.0 </static_friction>
<dynamic_friction> 4.0 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
<damping_coeff_rebound unit="LBS/FT/SEC"> 40000 </damping_coeff_rebound>
</contact>
<contact type="STRUCTURE" name="RADOME">
<location unit="IN">
<x> -486.6 </x>
<y> 0 </y>
<z> -8.7 </z>
</location>
<static_friction> 5.0 </static_friction>
<dynamic_friction> 4.0 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
<damping_coeff_rebound unit="LBS/FT/SEC"> 40000 </damping_coeff_rebound>
</contact>
</ground_reactions>
<external_reactions>
<force name="pushback" frame="BODY">
<location unit="IN">
<x> -2.98081 </x>
<y> 0.0 </y>
<z> -1.9683 </z>
</location>
<direction>
<x>1</x>
<y>0</y>
<z>0</z>
</direction>
</force>
<force name="hook" frame="BODY">
<location unit="IN">
<x> 100.669 </x>
<y> 0.0 </y>
<z> -28.818 </z>
</location>
<direction>
<x> -0.9995 </x>
<y> 0.0 </y>
<z> 0.01 </z>
</direction>
</force>
</external_reactions>
<propulsion>
<engine file="F100-PW-200">
<location unit="IN">
<x> 0 </x>
<y> 0 </y>
<z> 0 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0 </pitch>
<yaw> 0 </yaw>
</orient>
<feed>0</feed>
<feed>1</feed>
<feed>2</feed>
<feed>3</feed>
<feed>4</feed>
<feed>5</feed>
<feed>6</feed>
<thruster file="direct">
<location unit="IN">
<x> 500 </x>
<y> 0 </y>
<z> 0 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0.0 </pitch>
<yaw> 0.0 </yaw>
</orient>
</thruster>
</engine>
<!--
This is a pseudo fuel system.
As can be read in manual it should have 12 tanks,
including possibility for 3 droptanks.
And engine only draws fuel from 2 of them.
Total internal JP-4 should be: 6625
Total external JP-4 should be: 9300 (the big tanks, there is 2 sizes)
-->
<tank type="FUEL"> <!-- FWD Tank -->
<location unit="IN">
<x> -225 </x>
<y> 0 </y>
<z> 0 </z>
</location>
<capacity unit="LBS"> 2812.5 </capacity>
<contents unit="LBS"> 2812.5 </contents>
<type>JP-4</type>
<priority> 3 </priority>
</tank>
<tank type="FUEL"> <!-- AFT Tank -->
<location unit="IN">
<x> -153 </x>
<y> 0 </y>
<z> 0 </z>
</location>
<capacity unit="LBS"> 2812.5 </capacity>
<contents unit="LBS"> 2812.5 </contents>
<type>JP-4</type>
<priority> 3 </priority>
</tank>
<tank type="FUEL"> <!-- Right External Tank -->
<location unit="IN">
<x> -213 </x>
<y> 80 </y>
<z> -40 </z>
</location>
<capacity unit="LBS"> 2991 </capacity>
<contents unit="LBS"> 0 </contents>
<type>JP-4</type>
<priority> 1 </priority>
</tank>
<tank type="FUEL"> <!-- Left External Tank -->
<location unit="IN">
<x> -213 </x>
<y> -80 </y>
<z> -40 </z>
</location>
<capacity unit="LBS"> 2991 </capacity>
<contents unit="LBS"> 0 </contents>
<type>JP-4</type>
<priority> 1 </priority>
</tank>
<tank type="FUEL"> <!-- Center External Tank -->
<location unit="IN">
<x> -213 </x>
<y> 0 </y>
<z> -50 </z>
</location>
<capacity unit="LBS"> 2425 </capacity>
<contents unit="LBS"> 0 </contents>
<type>JP-4</type>
<priority> 1 </priority>
</tank>
<tank type="FUEL"> <!-- Right wing tank -->
<location unit="IN">
<x> -193 </x>
<y> 80 </y>
<z> 0 </z>
</location>
<capacity unit="LBS"> 500 </capacity>
<contents unit="LBS"> 500 </contents>
<type>JP-4</type>
<priority> 2 </priority>
</tank>
<tank type="FUEL"> <!-- Left wing tank -->
<location unit="IN">
<x> -193 </x>
<y> -80 </y>
<z> 0 </z>
</location>
<capacity unit="LBS"> 500 </capacity>
<contents unit="LBS"> 500 </contents>
<type>JP-4</type>
<priority> 2 </priority>
</tank>
</propulsion>
<system file="pushback">
<property>/sim/model/pushback/kp</property>
<property>/sim/model/pushback/ki</property>
<property>/sim/model/pushback/kd</property>
</system>
<system file="hook"/>
<flight_control file="Systems/jsb-controls"/>
<aerodynamics>
<!-- begin: aerodynamics by Nikolai V. Chr.
Note:
======
In all aero tables that do not have author listed, the numbers was typed in by Nikolai V. Chr.
Where nothing else is mentioned the aerodynamics come from TP 1538
Todo:
======
Make all coefficients functions (like Cy and Cz is)
Put in engine gyroscopic effect (160 slugs-ft2/sec)
Missing wind-tunnel data:
==========================
+Gear dynamics
Ground effect
+Wave drag
+Trailing edge flaps dynamics
Stores dynamics
Canopy dynamics
Dynamics of high speed
-->
<!--<aero_ref_pt_shift_x>
<function name="metrics/aero-rp-shift-mac">
<description>
Mach-tuck: Transonic Shift of Aerodynamic Center
An estimate by Nikolai V. Chr.
Default static margin =-0.04c (5.4336 inch)
Default CoG = 0.35c
Chord = 11.32 ft
0.19 makes the AeroRP move to 0.5c at 1.1 mach.
</description>
<table name="table/ACshift">
<independentVar>velocities/mach</independentVar>
<tableData>
0.6 0
0.8 0.05
1.1 0.19
</tableData>
</table>
</function>
</aero_ref_pt_shift_x>-->
<hysteresis_limits unit="DEG">
<description>Stall regime</description>
<min> 31 </min>
<max> 36 </max>
</hysteresis_limits>
<function name="aero/CG-pos-c">
<description>
CG position
</description>
<sum>
<v>0.35</v><!-- X_CG-ref -->
<quotient>
<product>
<difference>
<p>inertia/cg-x-in</p>
<v>-193</v><!-- X_CG-ref (inches) -->
</difference>
<v>0.083333</v><!-- in to ft -->
</product>
<property>metrics/cbarw-ft</property>
</quotient>
</sum>
</function>
<function name="aero/static-margin-c">
<description>
Static margin in fraction of chord
</description>
<quotient>
<product>
<difference>
<p>metrics/aero-rp-x-in</p>
<p>inertia/cg-x-in</p>
</difference>
<v>0.083333</v><!-- in to ft -->
</product>
<property>metrics/cbarw-ft</property>
</quotient>
</function>
<function name="aero/coefficient/CDwave">
<product>
<table name="table/CDwave">
<independentVar>velocities/mach</independentVar>
<tableData>
0.000 0.000
0.810 0.000
1.100 0.028
1.800 0.020
</tableData>
</table>
<table name="table/CDwave_sb">
<independentVar>fcs/speedbrake-pos-norm</independentVar>
<tableData>
0 1.0
1 1.5
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CDtef">
<product>
<abs>
<!-- is absolute so -2 degs up don't give negative drag -->
<property>fcs/fly-by-wire/tef/tef-pos-norm</property>
</abs>
<value>0.020</value>
</product>
</function>
<function name="aero/coefficient/CDgear">
<product>
<property>gear/gear-pos-norm</property>
<value>0.025</value>
</product>
</function>
<function name="aero/coefficient/CLtef">
<product>
<property>fcs/fly-by-wire/tef/tef-pos-norm</property>
<value>0.1221731</value>
</product>
</function>
<function name="aero/coefficient/CL_g">
<description>Change in lift due to ground effect</description>
<product>
<table>
<independentVar>aero/h_b-mac-ft</independentVar>
<tableData>
0.0000 0.2290
0.2000 0.1240
0.3000 0.1160
0.4000 0.1240
0.6000 0.1050
0.8000 0.0410
1.0000 0.0340
1.2000 0.0190
1.4000 0.0080
1.6000 0.0030
1.8000 0.0010
2.0000 0.0000
2.2000 0.0000
</tableData>
</table>
<cos>
<!-- Less lift due to ground effect when flying inverted-->
<product>
<p>/orientation/roll-deg</p>
<v>0.017453</v>
</product>
</cos>
</product>
</function>
<function name="aero/coefficient/Cx_g">
<sum>
<v>1</v>
<product>
<property>aero/coefficient/CL_g</property>
<sin>
<property>aero/alpha-rad</property>
</sin>
</product>
</sum>
</function>
<function name="aero/coefficient/Cz_g">
<sum>
<v>1</v>
<product>
<property>aero/coefficient/CL_g</property>
<v>-1</v>
<cos>
<property>aero/alpha-rad</property>
</cos>
</product>
</sum>
</function>
<axis name="X">
<function name="aero/coefficient/CDx">
<description>Drag</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<sum>
<property>aero/coefficient/CDgear</property>
<property>aero/coefficient/CDtef</property>
<property>aero/coefficient/CDwave</property>
</sum>
<cos>
<property>aero/alpha-rad</property>
</cos>
<v>-1</v>
</product>
</function>
<function name="aero/coefficient/CLx">
<description>Lift</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<sum>
<property>aero/coefficient/CLtef</property>
</sum>
<sin>
<property>aero/alpha-rad</property>
</sin>
</product>
</function>
<function name="aero/coefficient/Cx">
<description>
Cx coefficient in body coordinate system.
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<p>aero/coefficient/Cx_g</p>
<table name="table/Cx">
<independentVar lookup="row">aero/alpha-deg</independentVar>
<independentVar lookup="column">aero/beta-deg</independentVar>
<independentVar lookup="table">fcs/fly-by-wire/pitch/horz-tail-deflection-deg</independentVar>
<tableData breakPoint="-25.0">
-30 -25 -20 -15 -10 -8 -6 -4 -2 0 2 4 6 8 10 15 20 25 30
-20 -.1837 -.1953 -.1904 -.1899 -.1949 -.1914 -.1872 -.1860 -.1860 -.1868 -.1899 -.1902 -.1900 -.1896 -.1883 -.1833 -.1838 -.1787 -.1771
-15 -.1714 -.1765 -.1792 -.1827 -.1816 -.1834 -.1852 -.1853 -.1877 -.1875 -.1898 -.1876 -.1868 -.1846 -.1841 -.1852 -.1817 -.1790 -.1739
-10 -.1531 -.1627 -.1692 -.1718 -.1695 -.1693 -.1707 -.1735 -.1772 -.1787 -.1769 -.1729 -.1711 -.1706 -.1698 -.1721 -.1695 -.1630 -.1534
-05 -.1151 -.1232 -.1276 -.1317 -.1390 -.1415 -.1420 -.1425 -.1437 -.1432 -.1425 -.1422 -.1410 -.1397 -.1372 -.1299 -.1258 -.1214 -.1133
00 -.0907 -.0985 -.1043 -.1093 -.1120 -.1115 -.1122 -.1124 -.1130 -.1132 -.1129 -.1119 -.1110 -.1102 -.1092 -.1065 -.1015 -.0957 -.0879
05 -.0514 -.0567 -.0603 -.0640 -.0653 -.0661 -.0668 -.0675 -.0690 -.0693 -.0686 -.0680 -.0664 -.0650 -.0649 -.0631 -.0594 -.0558 -.0505
10 -.0079 -.0108 -.0099 -.0101 -.0074 -.0070 -.0078 -.0090 -.0116 -.0120 -.0123 -.0106 -.0088 -.0083 -.0080 -.0107 -.0105 -.0114 -.0085
15 0.0354 0.0358 0.0388 0.0402 0.0477 0.0503 0.0535 0.0553 0.0538 0.0537 0.0533 0.0536 0.0527 0.0509 0.0485 0.0410 0.0396 0.0366 0.0362
20 0.0740 0.0756 0.0746 0.0745 0.0867 0.0888 0.0924 0.0941 0.0948 0.0951 0.0975 0.0939 0.0913 0.0867 0.0824 0.0702 0.0703 0.0713 0.0697
25 0.1092 0.1124 0.1102 0.1067 0.1101 0.1121 0.1126 0.1129 0.1123 0.1111 0.1122 0.1125 0.1136 0.1115 0.1075 0.1041 0.1076 0.1098 0.1066
30 0.0915 0.1010 0.0975 0.1079 0.1188 0.1333 0.1399 0.1422 0.1443 0.1435 0.1431 0.1407 0.1379 0.1359 0.1323 0.1214 0.1110 0.1145 0.1050
35 0.1079 0.1137 0.1198 0.1278 0.1402 0.1425 0.1478 0.1570 0.1623 0.1663 0.1667 0.1664 0.1637 0.1560 0.1460 0.1336 0.1256 0.1195 0.1137
40 0.1306 0.1437 0.1350 0.1441 0.1574 0.1585 0.1601 0.1682 0.1726 0.1739 0.1711 0.1699 0.1655 0.1611 0.1567 0.1434 0.1343 0.1430 0.1299
45 0.1535 0.1603 0.1605 0.1604 0.1637 0.1671 0.1664 0.1639 0.1674 0.1659 0.1649 0.1650 0.1625 0.1597 0.1573 0.1540 0.1541 0.1539 0.1471
50 0.1471 0.1584 0.1646 0.1671 0.1712 0.1712 0.1676 0.1644 0.1656 0.1693 0.1714 0.1728 0.1749 0.1725 0.1730 0.1537 0.1457 0.1435 0.1362
55 0.1554 0.1615 0.1568 0.1661 0.1778 0.1769 0.1765 0.1749 0.1762 0.1804 0.1743 0.1666 0.1677 0.1724 0.1761 0.1722 0.1347 0.1448 0.1442
60 0.1501 0.1599 0.1647 0.1525 0.1664 0.1662 0.1794 0.1710 0.1719 0.1718 0.1728 0.1730 0.1734 0.1721 0.1688 0.1471 0.1462 0.1486 0.1460
70 0.1501 0.1536 0.1569 0.1420 0.1573 0.1595 0.1788 0.1715 0.1738 0.1695 0.1710 0.1712 0.1730 0.1720 0.1686 0.1474 0.1567 0.1557 0.1545
80 0.1685 0.1615 0.1559 0.1520 0.1521 0.1521 0.1535 0.1585 0.1566 0.1598 0.1573 0.1563 0.1586 0.1558 0.1572 0.1410 0.1410 0.1467 0.1538
90 0.1712 0.1651 0.1608 0.1648 0.1676 0.1660 0.1686 0.1667 0.1669 0.1660 0.1672 0.1662 0.1664 0.1711 0.1677 0.1531 0.1493 0.1549 0.1624
</tableData>
<tableData breakPoint="-10.0">
-30 -25 -20 -15 -10 -8 -6 -4 -2 0 2 4 6 8 10 15 20 25 30
-20 -.1362 -.1351 -.1419 -.1386 -.1374 -.1330 -.1268 -.1249 -.1222 -.1223 -.1246 -.1247 -.1252 -.1257 -.1282 -.1294 -.1327 -.1259 -.1270
-15 -.1216 -.1245 -.1235 -.1208 -.1176 -.1176 -.1170 -.1177 -.1184 -.1188 -.1185 -.1187 -.1182 -.1178 -.1184 -.1216 -.1243 -.1253 -.1224
-10 -.1018 -.1066 -.1068 -.1071 -.1061 -.1068 -.1072 -.1083 -.1094 -.1147 -.1095 -.1084 -.1077 -.1063 -.1069 -.1079 -.1076 -.1074 -.1026
-05 -.0655 -.0706 -.0746 -.0771 -.0836 -.0864 -.0876 -.0887 -.0889 -.0893 -.0885 -.0875 -.0859 -.0842 -.0812 -.0747 -.0722 -.0682 -.0631
00 -.0483 -.0509 -.0532 -.0544 -.0578 -.0589 -.0597 -.0606 -.0613 -.0617 -.0611 -.0603 -.0595 -.0577 -.0561 -.0527 -.0515 -.0492 -.0466
05 -.0118 -.0106 -.0096 -.0102 -.0142 -.0148 -.0155 -.0161 -.0177 -.0172 -.0178 -.0167 -.0156 -.0141 -.0133 -.0093 -.0087 -.0106 -.0127
10 0.0268 0.0328 0.0367 0.0399 0.0412 0.0417 0.0408 0.0413 0.0406 0.0399 0.0399 0.0409 0.0415 0.0414 0.0412 0.0399 0.0367 0.0328 0.0268
15 0.0735 0.0800 0.0887 0.0934 0.0983 0.1006 0.1024 0.1034 0.1033 0.1027 0.1031 0.1027 0.1018 0.1008 0.0983 0.0934 0.0887 0.0800 0.0735
20 0.1222 0.1275 0.1258 0.1249 0.1326 0.1347 0.1350 0.1349 0.1325 0.1322 0.1332 0.1338 0.1343 0.1310 0.1298 0.1221 0.1230 0.1247 0.1194
25 0.1374 0.1474 0.1466 0.1454 0.1465 0.1485 0.1485 0.1453 0.1429 0.1407 0.1418 0.1443 0.1457 0.1442 0.1439 0.1428 0.1440 0.1448 0.1348
30 0.1056 0.1261 0.1297 0.1437 0.1500 0.1619 0.1655 0.1660 0.1663 0.1651 0.1640 0.1643 0.1624 0.1615 0.1593 0.1530 0.1390 0.1354 0.1149
35 0.1075 0.1154 0.1299 0.1377 0.1523 0.1591 0.1722 0.1789 0.1801 0.1795 0.1793 0.1804 0.1782 0.1749 0.1675 0.1529 0.1451 0.1306 0.1227
40 0.1335 0.1412 0.1365 0.1456 0.1597 0.1622 0.1725 0.1762 0.1798 0.1798 0.1810 0.1771 0.1710 0.1702 0.1659 0.1518 0.1427 0.1474 0.1397
45 0.1521 0.1486 0.1517 0.1520 0.1608 0.1613 0.1597 0.1671 0.1667 0.1671 0.1664 0.1653 0.1629 0.1597 0.1569 0.1481 0.1478 0.1447 0.1482
50 0.1346 0.1410 0.1422 0.1486 0.1561 0.1570 0.1538 0.1511 0.1515 0.1544 0.1549 0.1547 0.1560 0.1538 0.1544 0.1469 0.1405 0.1393 0.1329
55 0.1375 0.1367 0.1251 0.1336 0.1467 0.1472 0.1475 0.1465 0.1462 0.1488 0.1433 0.1361 0.1370 0.1405 0.1431 0.1300 0.1215 0.1331 0.1339
60 0.1316 0.1360 0.1355 0.1154 0.1285 0.1289 0.1336 0.1351 0.1372 0.1383 0.1356 0.1320 0.1387 0.1323 0.1310 0.1179 0.1380 0.1385 0.1341
70 0.1171 0.1174 0.1185 0.1108 0.1161 0.1187 0.1376 0.1312 0.1353 0.1328 0.1301 0.1263 0.1270 0.1281 0.1268 0.1215 0.1292 0.1281 0.1278
80 0.1201 0.1161 0.1136 0.1124 0.1158 0.1148 0.1149 0.1194 0.1177 0.1211 0.1195 0.1195 0.1225 0.1204 0.1177 0.1143 0.1155 0.1180 0.1220
90 0.1287 0.1241 0.1214 0.1221 0.1265 0.1256 0.1257 0.1236 0.1248 0.1247 0.1262 0.1256 0.1256 0.1297 0.1257 0.1213 0.1206 0.1233 0.1279
</tableData>
<tableData breakPoint="0.0">
-30 -25 -20 -15 -10 -8 -6 -4 -2 0 2 4 6 8 10 15 20 25 30
-20 -.1072 -.1061 -.1129 -.1096 -.1084 -.1040 -.0978 -.0959 -.0932 -.0933 -.0956 -.0957 -.0962 -.0967 -.0992 -.1004 -.1037 -.0969 -.0980
-15 -.1006 -.1035 -.1025 -.0998 -.0966 -.0966 -.0960 -.0967 -.0974 -.0978 -.0975 -.0977 -.0972 -.0968 -.0974 -.1006 -.1033 -.1043 -.1014
-10 -.0853 -.0901 -.0903 -.0906 -.0896 -.0903 -.0907 -.0918 -.0929 -.0982 -.0930 -.0919 -.0912 -.0898 -.0904 -.0914 -.0911 -.0909 -.0861
-05 -.0546 -.0597 -.0637 -.0662 -.0727 -.0755 -.0767 -.0778 -.0780 -.0784 -.0776 -.0766 -.0750 -.0733 -.0703 -.0638 -.0613 -.0573 -.0522
00 -.0355 -.0381 -.0404 -.0416 -.0450 -.0461 -.0469 -.0478 -.0485 -.0489 -.0483 -.0475 -.0467 -.0449 -.0433 -.0399 -.0387 -.0364 -.0338
05 -.0012 0.0000 0.0010 0.0004 -.0036 -.0042 -.0049 -.0055 -.0071 -.0066 -.0072 -.0061 -.0050 -.0035 -.0027 0.0013 0.0019 0.0000 -.0021
10 0.0359 0.0491 0.0458 0.0490 0.0503 0.0508 0.0499 0.0509 0.0497 0.0490 0.0490 0.0500 0.0506 0.0505 0.0503 0.0490 0.0458 0.0419 0.0359
15 0.0780 0.0845 0.0932 0.0979 0.1028 0.1051 0.1069 0.1079 0.1078 0.1072 0.1076 0.1072 0.1063 0.1053 0.1028 0.0979 0.0932 0.0845 0.0780
20 0.1183 0.1236 0.1219 0.1210 0.1287 0.1308 0.1311 0.1310 0.1286 0.1283 0.1293 0.1299 0.1304 0.1271 0.1259 0.1182 0.1191 0.1208 0.1155
25 0.1267 0.1367 0.1359 0.1347 0.1358 0.1378 0.1378 0.1346 0.1322 0.1300 0.1311 0.1336 0.1350 0.1335 0.1332 0.1321 0.1333 0.1341 0.1241
30 0.0941 0.1146 0.1182 0.1322 0.1385 0.1504 0.1540 0.1545 0.1548 0.1536 0.1525 0.1528 0.1509 0.1500 0.1478 0.1415 0.1275 0.1239 0.1034
35 0.0885 0.0964 0.1109 0.1189 0.1333 0.1391 0.1532 0.1599 0.1611 0.1605 0.1603 0.1614 0.1592 0.1559 0.1485 0.1339 0.1261 0.1116 0.1037
40 0.1089 0.1166 0.1119 0.1210 0.1351 0.1376 0.1479 0.1516 0.1552 0.1552 0.1564 0.1525 0.1464 0.1456 0.1413 0.1272 0.1181 0.1228 0.1151
45 0.1232 0.1197 0.1228 0.1231 0.1319 0.1324 0.1308 0.1332 0.1378 0.1382 0.1375 0.1364 0.1340 0.1380 0.1280 0.1192 0.1189 0.1158 0.1193
50 0.1135 0.1185 0.1184 0.1171 0.1243 0.1279 0.1279 0.1258 0.1257 0.1281 0.1258 0.1228 0.1221 0.1186 0.1180 0.1108 0.1121 0.1122 0.1072
55 0.1137 0.1195 0.1146 0.1161 0.1209 0.1211 0.1211 0.1195 0.1183 0.1200 0.1185 0.1153 0.1160 0.1152 0.1135 0.1087 0.1072 0.1121 0.1063
60 0.1037 0.1090 0.1094 0.1049 0.1109 0.1123 0.1181 0.1184 0.1170 0.1147 0.1141 0.1126 0.1129 0.1129 0.1109 0.1049 0.1094 0.1090 0.1037
70 0.0857 0.0858 0.0857 0.0796 0.0851 0.0919 0.1150 0.1087 0.1089 0.1025 0.1022 0.1007 0.1012 0.0994 0.0952 0.0897 0.0958 0.0959 0.0958
80 0.0842 0.0807 0.0787 0.0778 0.0791 0.0793 0.0805 0.0846 0.0808 0.0821 0.0802 0.0799 0.0826 0.0800 0.0709 0.0756 0.0765 0.0785 0.0820
90 0.0847 0.0813 0.0798 0.0824 0.0843 0.0843 0.0853 0.0841 0.0858 0.0864 0.0857 0.0828 0.0817 0.0857 0.0816 0.0797 0.0771 0.0786 0.0820
</tableData>
<tableData breakPoint="10.0">
-30 -25 -20 -15 -10 -8 -6 -4 -2 0 2 4 6 8 10 15 20 25 30
-20 -.1023 -.1012 -.1080 -.1047 -.1035 -.0991 -.0929 -.0910 -.0884 -.0884 -.0907 -.0908 -.0913 -.0918 -.0943 -.0955 -.0988 -.0920 -.0931
-15 -.1038 -.1067 -.1057 -.1030 -.0998 -.0988 -.0992 -.0999 -.1006 -.1010 -.1007 -.1009 -.1004 -.1000 -.1006 -.1038 -.1065 -.1075 -.1046
-10 -.0963 -.1011 -.1013 -.1016 -.1006 -.1013 -.1017 -.1028 -.1039 -.1092 -.1040 -.1029 -.1022 -.1008 -.1014 -.1024 -.1021 -.1019 -.0971
-05 -.0664 -.0715 -.0755 -.0780 -.0845 -.0873 -.0885 -.0896 -.0898 -.0902 -.0894 -.0884 -.0868 -.0851 -.0821 -.0756 -.0731 -.0691 -.0640
00 -.0472 -.0498 -.0521 -.0533 -.0567 -.0578 -.0586 -.0595 -.0602 -.0606 -.0600 -.0592 -.0584 -.0566 -.0550 -.0516 -.0504 -.0481 -.0455
05 -.0146 -.0134 -.0124 -.0130 -.0170 -.0176 -.0183 -.0189 -.0205 -.0200 -.0206 -.0195 -.0184 -.0169 -.0161 -.0121 -.0115 -.0134 -.0155
10 0.0182 0.0242 0.0281 0.0313 0.0326 0.0331 0.0322 0.0327 0.0320 0.0313 0.0313 0.0323 0.0329 0.0328 0.0326 0.0313 0.0281 0.0242 0.0182
15 0.0537 0.0602 0.0689 0.0736 0.0785 0.0808 0.0826 0.0836 0.0835 0.0829 0.0833 0.0829 0.0820 0.0810 0.0785 0.0736 0.0689 0.0602 0.0537
20 0.0871 0.0924 0.0907 0.0898 0.0975 0.0996 0.0999 0.0998 0.0974 0.0971 0.0981 0.0987 0.0992 0.0959 0.0947 0.0870 0.0879 0.0896 0.0843
25 0.0916 0.1016 0.1008 0.0996 0.1007 0.1027 0.1027 0.0995 0.0971 0.0949 0.0960 0.0985 0.0999 0.0984 0.0981 0.0970 0.0982 0.0990 0.0890
30 0.0509 0.0714 0.0750 0.0890 0.0953 0.1072 0.1108 0.1113 0.1116 0.1104 0.1093 0.1096 0.1077 0.1068 0.1046 0.0983 0.0843 0.0807 0.0602
35 0.0481 0.0560 0.0705 0.0783 0.0929 0.0987 0.1128 0.1195 0.1207 0.1201 0.1199 0.1210 0.1188 0.1155 0.1081 0.0935 0.0857 0.0712 0.0633
40 0.0664 0.0741 0.0694 0.0785 0.0926 0.0951 0.1054 0.1091 0.1127 0.1127 0.1139 0.1100 0.1039 0.1031 0.0988 0.0847 0.0756 0.0803 0.0726
45 0.0846 0.0811 0.0842 0.0845 0.0933 0.0938 0.0922 0.0946 0.0992 0.0996 0.0989 0.0978 0.0954 0.0922 0.0894 0.0806 0.0803 0.0772 0.0807
50 0.0908 0.0985 0.1011 0.0999 0.1063 0.1061 0.1018 0.0996 0.1021 0.1071 0.1071 0.1064 0.1070 0.1036 0.1032 0.0968 0.0980 0.0954 0.0877
55 0.0842 0.0869 0.0790 0.0882 0.1025 0.1010 0.0993 0.0980 0.0991 0.1030 0.0972 0.0897 0.0914 0.0969 0.1015 0.0872 0.0780 0.0859 0.0832
60 0.0749 0.0823 0.0849 0.0794 0.0831 0.0841 0.0896 0.0908 0.0915 0.0914 0.0908 0.0893 0.0895 0.0889 0.0868 0.0831 0.0886 0.0860 0.0786
70 0.0504 0.0500 0.0504 0.0467 0.0813 0.0811 0.0972 0.0950 0.1075 0.1190 0.1101 0.1001 0.0967 0.0958 0.0931 0.0585 0.0622 0.0618 0.0622
80 0.0421 0.0380 0.0355 0.0397 0.0420 0.0417 0.0424 0.0478 0.0473 0.0519 0.0484 0.0465 0.0489 0.0472 0.0450 0.0427 0.0385 0.0410 0.0451
90 0.0433 0.0404 0.0395 0.0467 0.0495 0.0492 0.0499 0.0484 0.0500 0.0504 0.0495 0.0463 0.0457 0.0510 0.0482 0.0454 0.0382 0.0391 0.0420
</tableData>
<tableData breakPoint="25.0">
-30 -25 -20 -15 -10 -8 -6 -4 -2 0 2 4 6 8 10 15 20 25 30
-20 -.1068 -.1102 -.1160 -.1176 -.1291 -.1289 -.1244 -.1158 -.1137 -.1141 -.1164 -.1192 -.1200 -.1240 -.1243 -.1128 -.1112 -.1054 -.1020
-15 -.1122 -.1180 -.1227 -.1292 -.1365 -.1397 -.1406 -.1416 -.1442 -.1450 -.1448 -.1428 -.1408 -.1440 -.1397 -.1324 -.1259 -.1212 -.1154
-10 -.1102 -.1212 -.1319 -.1359 -.1403 -.1427 -.1454 -.1480 -.1520 -.1633 -.1518 -.1482 -.1457 -.1438 -.1419 -.1375 -.1335 -.1228 -.1118
-05 -.0911 -.1027 -.1093 -.1144 -.1244 -.1304 -.1316 -.1320 -.1333 -.1337 -.1340 -.1322 -.1309 -.1280 -.1243 -.1143 -.1092 -.1026 -.0910
00 -.0811 -.0889 -.0955 -.0996 -.1015 -.1037 -.1056 -.1065 -.1077 -.1075 -.1072 -.1061 -.1045 -.1024 -.1003 -.0984 -.0943 -.0877 -.0799
05 -.0575 -.0588 -.0631 -.0676 -.0671 -.0694 -.0715 -.0739 -.0775 -.0785 -.0787 -.0744 -.0704 -.0688 -.0669 -.0674 -.0624 -.0586 -.0573
10 -.0183 -.0188 -.0211 -.0241 -.0226 -.0254 -.0291 -.0333 -.0370 -.0336 -.0345 -.0326 -.0283 -.0247 -.0236 -.0251 -.0221 -.0198 -.0193
15 0.0195 0.0186 0.0204 0.0186 0.0194 0.0181 0.0154 0.0162 0.0198 0.0212 0.0157 0.0131 0.0136 0.0158 0.0179 0.0171 0.0189 0.0171 0.0180
20 0.0494 0.0626 0.0562 0.0477 0.0323 0.0279 0.0289 0.0263 0.0204 0.0187 0.0173 0.0255 0.0183 0.0165 0.0119 0.0273 0.0358 0.0422 0.0290
25 0.0699 0.0695 0.0627 0.0557 0.0366 0.0316 0.0263 0.0207 0.0160 0.0198 0.0165 0.0218 0.0244 0.0228 0.0214 0.0405 0.0475 0.0543 0.0547
30 0.0207 0.0324 0.0323 0.0293 0.0304 0.0404 0.0419 0.0404 0.0385 0.0381 0.0374 0.0379 0.0389 0.0417 0.0446 0.0435 0.0465 0.0466 0.0349
35 0.0211 0.0282 0.0309 0.0263 0.0307 0.0334 0.0437 0.0466 0.0458 0.0479 0.0495 0.0495 0.0487 0.0467 0.0434 0.0390 0.0435 0.0409 0.0338
40 0.0386 0.0462 0.0331 0.0339 0.0365 0.0407 0.0394 0.0411 0.0407 0.0418 0.0413 0.0426 0.0392 0.0405 0.0381 0.0355 0.0347 0.0478 0.0402
45 0.0460 0.0438 0.0341 0.0311 0.0348 0.0373 0.0362 0.0335 0.0338 0.0363 0.0325 0.0340 0.0342 0.0356 0.0338 0.0301 0.0331 0.0428 0.0450
50 0.0394 0.0479 0.0513 0.0447 0.0538 0.0528 0.0483 0.0441 0.0444 0.0472 0.0488 0.0497 0.0507 0.0487 0.0495 0.0478 0.0525 0.0476 0.0376
55 0.0336 0.0411 0.0380 0.0471 0.0543 0.0508 0.0471 0.0445 0.0450 0.0484 0.0442 0.0383 0.0410 0.0471 0.0522 0.0432 0.0272 0.0347 0.0315
60 0.0158 0.0284 0.0361 0.0335 0.0487 0.0443 0.0442 0.0432 0.0451 0.0460 0.0451 0.0433 0.0435 0.0438 0.0416 0.0363 0.0397 0.0340 0.0246
70 -.0186 -.0121 -.0057 -.0070 0.0410 0.0451 0.0655 0.0604 0.0655 0.0641 0.0677 0.0701 0.0702 0.0636 0.0546 0.0033 0.0020 -.0005 0.0058
80 -.0242 -.0267 -.0277 -.0200 -.0215 -.0224 -.0223 -.0180 -.0202 -.0173 -.0046 0.0281 0.0311 0.0053 -.0210 -.0288 -.0312 -.0240 -.0152
90 -.0208 -.0271 -.0315 -.0229 -.0156 -.0165 -.0141 -.0184 -.0173 -.0173 -.0168 -.0185 -.0183 -.0130 -.0157 -.0237 -.0323 -.0246 -.0150
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/dCx_lef">
<description>
Cx due to leading edge flaps coefficient.
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/fly-by-wire/lef/lef-pos-r-norm</property>
<difference>
<table name="table/Cx_lef">
<independentVar lookup="row">aero/alpha-deg</independentVar>
<independentVar lookup="column">aero/beta-deg</independentVar>
<tableData>
-30 -25 -20 -15 -10 -8 -6 -4 -2 0 2 4 6 8 10 15 20 25 30
-20 -.0277 -.0285 -.0318 -.0256 -.0184 -.0156 -.0159 -.0162 -.0174 -.0181 -.0179 -.0167 -.0168 -.0156 -.0153 -.0225 -.0287 -.0254 -.0246
-15 -.0314 -.0310 -.0259 -.0191 -.0161 -.0157 -.0162 -.0173 -.0189 -.0193 -.0186 -.0186 -.0170 -.0155 -.0154 -.0184 -.0252 -.0303 -.0307
-10 -.0295 -.0298 -.0260 -.0233 -.0209 -.0215 -.0214 -.0224 -.0230 -.0224 -.0220 -.0217 -.0213 -.0205 -.0199 -.0223 -.0250 -.0288 -.0285
-05 -.0148 -.0153 -.0163 -.0150 -.0167 -.0173 -.0185 -.0189 -.0193 -.0196 -.0192 -.0185 -.0179 -.0178 -.0162 -.0155 -.0168 -.0158 -.0153
00 -.0136 -.0149 -.0143 -.0136 -.0168 -.0178 -.0182 -.0188 -.0197 -.0202 -.0196 -.0188 -.0180 -.0172 -.0160 -.0144 -.0151 -.0149 -.0144
05 -.0029 -.0010 -.0003 -.0005 -.0004 -.0006 -.0017 -.0027 -.0033 -.0033 -.0033 -.0024 -.0014 -.0004 0.0004 0.0013 0.0011 -.0002 -.0021
10 0.0085 0.0104 0.0116 0.0121 0.0131 0.0125 0.0122 0.0119 0.0104 0.0099 0.0096 0.0106 0.0117 0.0126 0.0127 0.0117 0.0112 0.0100 0.0081
15 0.0145 0.0168 0.0196 0.0218 0.0225 0.0231 0.0238 0.0238 0.0231 0.0224 0.0224 0.0226 0.0227 0.0223 0.0222 0.0215 0.0193 0.0165 0.0142
20 0.0165 0.0170 0.0205 0.0226 0.0252 0.0245 0.0236 0.0232 0.0233 0.0221 0.0232 0.0241 0.0250 0.0267 0.0276 0.0250 0.0229 0.0212 0.0189
25 0.0138 0.0172 0.0157 0.0178 0.0226 0.0251 0.0264 0.0274 0.0271 0.0278 0.0275 0.0271 0.0267 0.0249 0.0252 0.0203 0.0183 0.0198 0.0164
30 0.0092 0.0122 0.0129 0.0165 0.0202 0.0253 0.0279 0.0295 0.0296 0.0301 0.0309 0.0306 0.0278 0.0261 0.0247 0.0200 0.0174 0.0167 0.0137
35 0.0099 0.0134 0.0162 0.0149 0.0208 0.0229 0.0273 0.0286 0.0303 0.0305 0.0286 0.0307 0.0292 0.0259 0.0253 0.0194 0.0207 0.0179 0.0144
40 0.0206 0.0202 0.0236 0.0246 0.0289 0.0293 0.0290 0.0320 0.0317 0.0328 0.0314 0.0305 0.0289 0.0281 0.0262 0.0219 0.0209 0.0175 0.0179
45 0.0257 0.0274 0.0266 0.0236 0.0266 0.0283 0.0236 0.0298 0.0268 0.0309 0.0307 0.0280 0.0238 0.0284 0.0254 0.0224 0.0254 0.0262 0.0245
</tableData>
</table>
<table name="table/Cx_dh0">
<independentVar lookup="row">aero/alpha-deg</independentVar>
<independentVar lookup="column">aero/beta-deg</independentVar>
<tableData>
-30 -25 -20 -15 -10 -8 -6 -4 -2 0 2 4 6 8 10 15 20 25 30
-20 -.1072 -.1061 -.1129 -.1096 -.1084 -.1040 -.0978 -.0959 -.0932 -.0933 -.0956 -.0957 -.0962 -.0967 -.0992 -.1004 -.1037 -.0969 -.0980
-15 -.1006 -.1035 -.1025 -.0998 -.0966 -.0966 -.0960 -.0967 -.0974 -.0978 -.0975 -.0977 -.0972 -.0968 -.0974 -.1006 -.1033 -.1043 -.1014
-10 -.0853 -.0901 -.0903 -.0906 -.0896 -.0903 -.0907 -.0918 -.0929 -.0982 -.0930 -.0919 -.0912 -.0898 -.0904 -.0914 -.0911 -.0909 -.0861
-05 -.0546 -.0597 -.0637 -.0662 -.0727 -.0755 -.0767 -.0778 -.0780 -.0784 -.0776 -.0766 -.0750 -.0733 -.0703 -.0638 -.0613 -.0573 -.0522
00 -.0355 -.0381 -.0404 -.0416 -.0450 -.0461 -.0469 -.0478 -.0485 -.0489 -.0483 -.0475 -.0467 -.0449 -.0433 -.0399 -.0387 -.0364 -.0338
05 -.0012 0.0000 0.0010 0.0004 -.0036 -.0042 -.0049 -.0055 -.0071 -.0066 -.0072 -.0061 -.0050 -.0035 -.0027 0.0013 0.0019 0.0000 -.0021
10 0.0359 0.0491 0.0458 0.0490 0.0503 0.0508 0.0499 0.0509 0.0497 0.0490 0.0490 0.0500 0.0506 0.0505 0.0503 0.0490 0.0458 0.0419 0.0359
15 0.0780 0.0845 0.0932 0.0979 0.1028 0.1051 0.1069 0.1079 0.1078 0.1072 0.1076 0.1072 0.1063 0.1053 0.1028 0.0979 0.0932 0.0845 0.0780
20 0.1183 0.1236 0.1219 0.1210 0.1287 0.1308 0.1311 0.1310 0.1286 0.1283 0.1293 0.1299 0.1304 0.1271 0.1259 0.1182 0.1191 0.1208 0.1155
25 0.1267 0.1367 0.1359 0.1347 0.1358 0.1378 0.1378 0.1346 0.1322 0.1300 0.1311 0.1336 0.1350 0.1335 0.1332 0.1321 0.1333 0.1341 0.1241
30 0.0941 0.1146 0.1182 0.1322 0.1385 0.1504 0.1540 0.1545 0.1548 0.1536 0.1525 0.1528 0.1509 0.1500 0.1478 0.1415 0.1275 0.1239 0.1034
35 0.0885 0.0964 0.1109 0.1189 0.1333 0.1391 0.1532 0.1599 0.1611 0.1605 0.1603 0.1614 0.1592 0.1559 0.1485 0.1339 0.1261 0.1116 0.1037
40 0.1089 0.1166 0.1119 0.1210 0.1351 0.1376 0.1479 0.1516 0.1552 0.1552 0.1564 0.1525 0.1464 0.1456 0.1413 0.1272 0.1181 0.1228 0.1151
45 0.1232 0.1197 0.1228 0.1231 0.1319 0.1324 0.1308 0.1332 0.1378 0.1382 0.1375 0.1364 0.1340 0.1380 0.1280 0.1192 0.1189 0.1158 0.1193
50 0.1135 0.1185 0.1184 0.1171 0.1243 0.1279 0.1279 0.1258 0.1257 0.1281 0.1258 0.1228 0.1221 0.1186 0.1180 0.1108 0.1121 0.1122 0.1072
55 0.1137 0.1195 0.1146 0.1161 0.1209 0.1211 0.1211 0.1195 0.1183 0.1200 0.1185 0.1153 0.1160 0.1152 0.1135 0.1087 0.1072 0.1121 0.1063
60 0.1037 0.1090 0.1094 0.1049 0.1109 0.1123 0.1181 0.1184 0.1170 0.1147 0.1141 0.1126 0.1129 0.1129 0.1109 0.1049 0.1094 0.1090 0.1037
70 0.0857 0.0858 0.0857 0.0796 0.0851 0.0919 0.1150 0.1087 0.1089 0.1025 0.1022 0.1007 0.1012 0.0994 0.0952 0.0897 0.0958 0.0959 0.0958
80 0.0842 0.0807 0.0787 0.0778 0.0791 0.0793 0.0805 0.0846 0.0808 0.0821 0.0802 0.0799 0.0826 0.0800 0.0709 0.0756 0.0765 0.0785 0.0820
90 0.0847 0.0813 0.0798 0.0824 0.0843 0.0843 0.0853 0.0841 0.0858 0.0864 0.0857 0.0828 0.0817 0.0857 0.0816 0.0797 0.0771 0.0786 0.0820
</tableData>
</table>
</difference>
</product>
</function>
<!--<function name="aero/coefficient/dCx_sb">
<description>
Cx due speed brake coefficient.
These values are wrong. Mistake in TP 1538.
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/speedbrake-pos-norm</property>
<table name="table/dCx_sb">
<independentVar lookup="row">aero/alpha-deg</independentVar>
<tableData>
-20 -.0101
-15 -.0101
-10 -.0101
-05 -.0101
00 -.0101
05 -.0358
10 -.0790
15 -.1227
20 -.1827
25 -.1892
30 -.1988
35 -.2000
40 -.1874
45 -.1673
50 -.1476
55 -.1310
60 -.1279
70 -.1325
80 -.1250
90 -.1250
</tableData>
</table>
</product>
</function>-->
<function name="aero/coefficient/dCx_sb">
<description>
Cx due speed brake coefficient.
Source: TN-D-8176
</description>
<product>
<property>aero/qbar-psf</property>
<!--<property>metrics/Sw-sqft</property>--><v>280</v>
<property>fcs/speedbrake-pos-norm</property>
<table name="table/dCx_sb">
<independentVar lookup="row">aero/alpha-deg</independentVar>
<tableData>
-10 -.0790
-05 -.0498
00 -.0500
05 -.0498
10 -.0493
15 -.0483
20 -.0470
25 -.0453
30 -.0433
35 -.0410
40 -.0383
45 -.0354
50 -.0322
55 -.0287
60 -.0250
70 -.0171
80 -.0087
90 0.0000
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Cx_q">
<description>
Cx due to pitch rate coefficient.
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/ci2vel</property>
<property>velocities/q-rad_sec</property>
<table name="table/Cx_q">
<independentVar lookup="row">aero/alpha-deg</independentVar>
<tableData>
-20 .953
-15 .953
-10 .953
-05 1.55
00 1.90
05 2.46
10 2.92
15 3.30
20 2.76
25 2.05
30 1.50
35 1.49
40 1.83
45 1.21
50 1.33
55 1.61
60 .910
70 3.43
80 .617
90 .273
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/dCx_q-lef">
<description>
Cx due to pitch rate due to leading edge flaps coefficient.
Source for alpha 50+: TN-D-8176
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/ci2vel</property>
<property>velocities/q-rad_sec</property>
<property>fcs/fly-by-wire/lef/lef-pos-r-norm</property>
<table name="table/dCx_q-lef">
<independentVar lookup="row">aero/alpha-deg</independentVar>
<tableData>
-20 -1.22
-15 -1.22
-10 -1.22
-05 -1.66
00 -1.62
05 -1.58
10 -1.96
15 -2.51
20 -2.04
25 -1.64
30 -.824
35 -.817
40 -1.10
45 -.550
50 0.000
55 0.000
60 0.000
70 0.000
80 0.000
90 0.000
</tableData>
</table>
</product>
</function>
</axis>
<function name="aero/coefficient/CDz">
<description>Drag</description>
<product>
<sum>
<property>aero/coefficient/CDgear</property>
<property>aero/coefficient/CDtef</property>