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J3Cub_Datcom_aero.xml
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J3Cub_Datcom_aero.xml
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<?xml version="1.0"?>
<!-- ***********
Aerodynamics FDM for J3Cub.
This is a Datcom based FDM to replace the original by Eric Hofman in the file J3Cub_aero.xml.
Author: A J Teeder April 2019
*********** -->
<aerodynamics>
<property value="0.0">ice/wing</property>
<alphalimits unit="DEG">
<min> -4.0</min>
<max> 14.0 </max>
</alphalimits>
<function name="fcs/diff-aileron-pos-deg">
<description>
Differential Aileron (degrees)
</description>
<difference>
<property>fcs/right-aileron-pos-deg</property>
<property>fcs/left-aileron-pos-deg</property>
</difference>
</function>
<!-- Interface to j3cub-damage.xml -->
<!-- <function name="aero/moment/Roll_beta">
<value> 0.0 </value> -->
<!-- <property>aero/coefficient/ClDa</property> -->
<!-- </function> -->
<function name="aero/moment/Roll_yaw">
<value> 0.0 </value>
<!-- <property>aero/coefficient/ClDa</property> -->
</function>
<function name="aero/moment/Roll_damp">
<value> 0.0 </value>
<!-- <property>aero/coefficient/ClDa</property> -->
</function>
<!-- <function name="aero/moment/Roll_aileron">
<value> 0.0 </value>-->
<!-- <property>aero/coefficient/ClDa</property> -->
<!-- </function>-->
<axis name="LIFT">
<!--taken from SenecaII by Torsten Dreyer-->
<function name="aero/coefficient/CLicew">
<description>Lift_decrease_due_to_ice_on_wing</description>
<product>
<property>aero/qbar-area</property>
<table>
<independentVar>ice/wing</independentVar>
<tableData>
0.0 0
0.5 -0.6
1.0 -1.2
2.0 -2.4
</tableData>
</table>
</product>
</function>
<function name="aero/force/Lift_alpha">
<description>
Lift vs alpha
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table name="aero/coefficient/CL_alpha">
<independentVar lookup="row">aero/alpha-deg</independentVar>
<independentVar lookup="column">velocities/u-fps</independentVar>
<tableData>
55.29 72.75 109.12 145.49 181.87 218.24
-4 0.103 0.104 0.106 0.107 0.108 0.108
-2 0.293 0.296 0.299 0.302 0.304 0.306
-1 0.390 0.393 0.398 0.402 0.405 0.408
0 0.489 0.494 0.500 0.505 0.509 0.512
2 0.694 0.700 0.709 0.716 0.722 0.726
4 0.904 0.911 0.922 0.931 0.939 0.945
6 1.116 1.125 1.138 1.150 1.160 1.167
8 1.297 1.304 1.320 1.339 1.356 1.366
10 1.446 1.452 1.470 1.494 1.516 1.529
12 1.561 1.566 1.587 1.617 1.645 1.660
14 1.639 1.635 1.657 1.702 1.736 1.754
16 1.572 1.550 1.569 1.628 1.682 1.707
</tableData>
</table>
</product>
</function>
<function name="aero/force/Lift_q">
<description>
Lift due to pitch rate
</description>
<product>
<property>velocities/q-aero-rad_sec</property>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/ci2vel</property>
<table name="aero/coefficient/CLq">
<independentVar lookup="row">velocities/u-fps</independentVar>
<tableData>
55.29 4.2360
72.75 4.2770
109.12 4.3320
145.49 4.3700
181.87 4.4050
218.24 4.4420
</tableData>
</table>
</product>
</function>
<function name="aero/force/Lift_alphadot">
<description>
Lift due to AOA rate
</description>
<product>
<property>aero/alphadot-rad_sec</property>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/ci2vel</property>
<table name="aero/coefficient/CLad">
<independentVar lookup="row">aero/alpha-deg</independentVar>
<independentVar lookup="column">velocities/u-fps</independentVar>
<tableData>
55.29 72.75 109.12 145.49 181.87 218.24
-4 1.1960 1.2140 1.2380 1.2550 1.2710 1.2860
-2 1.2650 1.2830 1.3080 1.3260 1.3430 1.3590
-1 1.3190 1.3370 1.3620 1.3810 1.3980 1.4140
0 1.3590 1.3760 1.3990 1.4160 1.4330 1.4490
2 1.3700 1.3840 1.4050 1.4220 1.4380 1.4540
4 1.3470 1.3590 1.3790 1.3980 1.4170 1.4330
6 1.2580 1.2640 1.2830 1.3100 1.3370 1.3550
8 1.0790 1.0770 1.0950 1.1300 1.1670 1.1870
10 0.8492 0.8447 0.8598 0.8944 0.9266 0.9443
12 0.6051 0.5858 0.5960 0.6361 0.6655 0.6811
14 0.2208 0.1598 0.1571 0.2235 0.2808 0.3049
</tableData>
</table>
</product>
</function>
<function name="aero/force/Lift_ground_effect">
<description>
Lift due to ground effect
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table name="aero/coefficient/CLground">
<independentVar lookup="row">position/h-agl-ft</independentVar>
<independentVar lookup="column">velocities/u-fps</independentVar>
<tableData>
5.0 10.0 20.0 30.0
-4 -0.0160 -0.0070 -0.0050 0.0
-2 -0.0370 -0.0170 -0.0070 0.0
-1 -0.0490 -0.0220 -0.0060 0.0
0 -0.0600 -0.0280 -0.0030 0.0
2 -0.0800 -0.0370 -0.0030 0.0
4 -0.1000 -0.0470 -0.0110 0.0
6 -0.1030 -0.0490 -0.0190 0.0
8 -0.1000 -0.0480 -0.0250 0.0
10 -0.0930 -0.0460 -0.0270 0.0
12 -0.0750 -0.0370 -0.0210 0.0
14 0.0040 0.0020 0.0150 0.0
</tableData>
</table>
</product>
</function>
<function name="aero/force/Lift_elevator">
<description>
Lift due to Elevator Deflection
Positive surface deflection is trailing edge down
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table name="aero/coefficient/CLDe">
<independentVar lookup="row">fcs/elevator-pos-deg</independentVar>
<tableData>
-32 -0.122
-20 -0.101
-10 -0.068
-5 -0.034
0 0
5 0.034
10 0.068
20 0.101
27 0.111
</tableData>
</table>
</product>
</function>
</axis>
<!-- ********************************************************************** -->
<axis name="DRAG">
<!--taken from SenecaII by Torsten Dreyer-->
<function name="aero/coefficient/CDicew">
<description>Drag_due_to_ice_on_wing</description>
<product>
<property>aero/qbar-area</property>
<table>
<independentVar>ice/wing</independentVar>
<tableData>
0.0 0
0.5 0.12
1.0 0.24
2.0 0.6
</tableData>
</table>
</product>
</function>
<function name="aero/force/Drag_Alpha">
<description>
Drag vs alpha
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table name="aero/coefficient/CD">
<independentVar lookup="row">aero/alpha-deg</independentVar>
<independentVar lookup="column">velocities/u-fps</independentVar>
<tableData>
55.29 72.75 109.12 145.49 181.87 218.24
-4 0.0230 0.0210 0.0200 0.0180 0.0180 0.0170
-2 0.0260 0.0250 0.0230 0.0220 0.0210 0.0210
-1 0.0280 0.0270 0.0260 0.0250 0.0240 0.0240
0 0.0320 0.0310 0.0300 0.0290 0.0280 0.0280
2 0.0430 0.0420 0.0410 0.0410 0.0400 0.0400
4 0.0580 0.0580 0.0570 0.0570 0.0570 0.0570
6 0.0780 0.0780 0.0780 0.0780 0.0780 0.0780
8 0.0980 0.0980 0.0980 0.0990 0.1010 0.1010
10 0.1170 0.1170 0.1170 0.1200 0.1220 0.1230
12 0.1340 0.1340 0.1350 0.1380 0.1410 0.1430
14 0.1480 0.1450 0.1470 0.1520 0.1560 0.1580
16 0.1400 0.1360 0.1360 0.1420 0.1490 0.1520
</tableData>
</table>
</product>
</function>
<function name="aero/force/Drag_ground_effect">
<description>
Drag due to ground effect
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table name="aero/coefficient/CDground">
<independentVar lookup="row">position/h-agl-ft</independentVar>
<independentVar lookup="column">velocities/u-fps</independentVar>
<tableData>
5.0 10.0 20.0 30.0
-4 0.0010 0.0000 0.0000 0.0
-2 0.0020 0.0010 0.0000 0.0
-1 0.0020 0.0010 0.0000 0.0
0 0.0030 0.0020 0.0010 0.0
2 0.0070 0.0040 0.0020 0.0
4 0.0110 0.0060 0.0020 0.0
6 0.0160 0.0080 0.0030 0.0
8 0.0200 0.0110 0.0040 0.0
10 0.0250 0.0130 0.0040 0.0
12 0.0290 0.0150 0.0050 0.0
14 0.0300 0.0160 0.0060 0.0
</tableData>
</table>
</product>
</function>
<function name="aero/force/Drag_elevator">
<description>
Drag due to Elevator Deflection
Positive surface deflection is trailing edge down
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table name="aero/coefficient/CdDe">
<independentVar lookup="row">fcs/elevator-pos-deg</independentVar>
<tableData>
-32 0.02368
-20 0.00992
-10 0.00354
-5 0.00177
0 0.0
5 0.00177
10 0.00354
20 0.00992
27 0.0175
</tableData>
</table>
</product>
</function>
<function name="aero/force/Drag_gear">
<!-- Taken from Eric Hofman version -->
<description>Drag due to gear</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<value> 0.0040 </value>
<property>gear/drag-coef[1]</property> <!-- 36 Bush Wheels" -->
<property>gear/drag-coef[2]</property> <!-- Floats -->
<property>gear/drag-coef[3]</property> <!-- Amphibious -->
<property>gear/drag-coef[4]</property> <!-- Ski -->
<property>gear/drag-coef[5]</property> <!-- Ski Lite -->
<property>gear/drag-coef[6]</property> <!-- Sprayer -->
<property>gear/drag-coef[7]</property> <!-- Door Open/Off -->
<property>gear/drag-coef[8]</property> <!-- Window Open/Off -->
<property>gear/drag-coef[9]</property> <!-- Amphibious gear extended -->
</product>
</function>
</axis>
<!-- ********************************************************************** -->
<axis name="SIDE">
<function name="aero/force/Side_beta">
<description>
Side Force due to Sideslip
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/beta-rad</property>
<table name="aero/coefficient/Cyb">
<independentVar lookup="row">velocities/u-fps</independentVar>
<tableData>
55.29 -0.2337
72.75 -0.2341
109.12 -0.2345
145.49 -0.2348
181.87 -0.2350
218.24 -0.2352
</tableData>
</table>
</product>
</function>
<function name="aero/force/Side_rollrate">
<description>
Side Force due to Roll Rate(per radian)
</description>
<product>
<property>velocities/p-aero-rad_sec</property>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/bi2vel</property>
<table name="aero/coefficient/Cyp">
<independentVar lookup="row">aero/alpha-deg</independentVar>
<independentVar lookup="column">velocities/u-fps</independentVar>
<tableData>
55.29 72.75 109.12 145.49 181.87 218.24
-4 -0.0154 -0.0154 -0.0155 -0.0155 -0.0155 -0.0156
-2 -0.0021 -0.0020 -0.0019 -0.0019 -0.0018 -0.0018
-1 0.0048 0.0048 0.0050 0.0051 0.0052 0.0052
0 0.0117 0.0118 0.0120 0.0122 0.0123 0.0124
2 0.0257 0.0259 0.0263 0.0265 0.0267 0.0269
4 0.0399 0.0402 0.0407 0.0411 0.0414 0.0416
6 0.0546 0.0550 0.0556 0.0561 0.0564 0.0566
8 0.0677 0.0681 0.0688 0.0697 0.0704 0.0708
10 0.0791 0.0793 0.0802 0.0814 0.0824 0.0829
12 0.0886 0.0890 0.0900 0.0913 0.0926 0.0932
14 0.0992 0.0998 0.1011 0.1027 0.1038 0.1044
</tableData>
</table>
</product>
</function>
<function name="aero/force/Side_rudder">
<description>
Side Force due to rudder(DATCOM does not calculate)
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/rudder-pos-rad</property>
<value> 0.1</value> <!-- Estimate -->
</product>
</function>
</axis>
<!-- ********************************************************************** -->
<axis name="ROLL">
<function name="aero/moment/Roll_beta">
<description>
Roll Moment due to Beta(per radian)
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/beta-rad</property>
<table name="aero/coefficient/Clb">
<independentVar lookup="row">aero/alpha-deg</independentVar>
<independentVar lookup="column">velocities/u-fps</independentVar>
<tableData>
55.29 72.75 109.12 145.49 181.87 218.24
-4 -0.0521 -0.0523 -0.0526 -0.0529 -0.0531 -0.0532
-2 -0.0651 -0.0654 -0.0658 -0.0661 -0.0664 -0.0666
-1 -0.0717 -0.0721 -0.0726 -0.0729 -0.0732 -0.0735
0 -0.0785 -0.0789 -0.0794 -0.0799 -0.0802 -0.0805
2 -0.0923 -0.0927 -0.0934 -0.0939 -0.0944 -0.0948
4 -0.1062 -0.1068 -0.1075 -0.1082 -0.1088 -0.1092
6 -0.1185 -0.1192 -0.1203 -0.1212 -0.1220 -0.1226
8 -0.1316 -0.1319 -0.1330 -0.1342 -0.1355 -0.1362
10 -0.1374 -0.1379 -0.1392 -0.1410 -0.1428 -0.1438
12 -0.1458 -0.1459 -0.1471 -0.1491 -0.1510 -0.1521
14 -0.1482 -0.1477 -0.1490 -0.1520 -0.1543 -0.1555
</tableData>
</table>
</product>
</function>
<function name="aero/moment/Roll_rollrate">
<description>
Roll Moment moment due to roll rate(per radian)
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/p-aero-rad_sec</property>
<table name="aero/coefficient/Clp">
<independentVar lookup="row">aero/alpha-deg</independentVar>
<independentVar lookup="column">velocities/u-fps</independentVar>
<tableData>
55.29 72.75 109.12 145.49 181.87 218.24
-4 -0.4591 -0.4623 -0.4658 -0.4677 -0.4690 -0.4704
-2 -0.4812 -0.4843 -0.4877 -0.4898 -0.4916 -0.4932
-1 -0.4921 -0.4950 -0.4984 -0.5007 -0.5027 -0.5043
0 -0.5019 -0.5047 -0.5079 -0.5106 -0.5128 -0.5144
2 -0.5192 -0.5216 -0.5249 -0.5279 -0.5305 -0.5324
4 -0.5336 -0.5358 -0.5390 -0.5424 -0.5455 -0.5476
6 -0.4983 -0.4961 -0.4998 -0.5108 -0.5217 -0.5264
8 -0.4162 -0.4119 -0.4161 -0.4315 -0.4468 -0.4531
10 -0.3358 -0.3329 -0.3375 -0.3511 -0.3646 -0.3705
12 -0.2482 -0.2334 -0.2387 -0.2655 -0.2818 -0.2888
14 -0.0079 0.0286 0.0293 -0.0104 -0.0461 -0.0611
</tableData>
</table>
</product>
</function>
<function name="aero/moment/Roll_yawrate">
<description>
Roll Moment coefficient due to yaw rate(per radian)
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/r-aero-rad_sec</property>
<table name="aero/coefficient/Clr">
<independentVar lookup="row">aero/alpha-deg</independentVar>
<independentVar lookup="column">velocities/u-fps</independentVar>
<tableData>
55.29 72.75 109.12 145.49 181.87 218.24
-4 0.0703 0.0710 0.0719 0.0725 0.0731 0.0736
-2 0.0986 0.0996 0.1010 0.1022 0.1032 0.1042
-1 0.1129 0.1140 0.1157 0.1171 0.1185 0.1197
0 0.1273 0.1286 0.1306 0.1323 0.1338 0.1353
2 0.1565 0.1580 0.1606 0.1628 0.1649 0.1668
4 0.1859 0.1878 0.1909 0.1937 0.1964 0.1988
6 0.2207 0.2233 0.2269 0.2295 0.2320 0.2347
8 0.2565 0.2589 0.2630 0.2668 0.2703 0.2737
10 0.2897 0.2919 0.2964 0.3014 0.3062 0.3101
12 0.3220 0.3266 0.3313 0.3346 0.3401 0.3444
14 0.3885 0.3964 0.4032 0.4062 0.4080 0.4110
</tableData>
</table>
</product>
</function>
<function name="aero/moment/Roll_aileron">
<description>
Roll Moment due to Ailerons
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<table name="aero/coefficient/ClAileron">
<independentVar lookup="row">fcs/diff-aileron-pos-deg</independentVar>
<tableData>
-56 0.09823
-42 0.08842
-28 0.06971
-14 0.03551
14 -0.03551
28 -0.06971
42 -0.08842
56 -0.09823
</tableData>
</table>
</product>
</function>
<function name="aero/moment/Roll_rudder">
<description>
Roll moment due to rudder(DATCOM does not calculate)
</description>
<product>
<property>metrics/bw-ft</property>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/rudder-pos-rad</property>
<value> .01 </value> <!-- Estimate -->
</product>
</function>
</axis>
<!-- ********************************************************************** -->
<axis name="PITCH">
<function name="aero/moment/Pitch_alpha">
<description>
Pitch_moment due to alpha
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<table name="aero/coefficient/CM_alpha">
<independentVar lookup="row">aero/alpha-deg</independentVar>
<independentVar lookup="column">velocities/u-fps</independentVar>
<tableData>
55.29 72.75 109.12 145.49 181.87 218.24
-4 0.0230 0.0239 0.0251 0.0259 0.0266 0.0274
-2 0.0206 0.0217 0.0230 0.0239 0.0247 0.0254
-1 0.0188 0.0199 0.0213 0.0222 0.0230 0.0237
0 0.0150 0.0161 0.0174 0.0183 0.0191 0.0197
2 0.0015 0.0026 0.0040 0.0050 0.0058 0.0063
4 -0.0154 -0.0143 -0.0129 -0.0118 -0.0109 -0.0104
6 -0.0360 -0.0350 -0.0336 -0.0323 -0.0313 -0.0309
8 -0.0641 -0.0635 -0.0621 -0.0603 -0.0587 -0.0581
10 -0.1006 -0.1004 -0.0991 -0.0968 -0.0947 -0.0941
12 -0.1458 -0.1461 -0.1450 -0.1423 -0.1400 -0.1395
</tableData>
</table>
</product>
</function>
<function name="aero/moment/Pitch_pitchrate">
<description>
Pitch moment due to pitch rate(per radian)
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>aero/ci2vel</property>
<property>velocities/q-aero-rad_sec</property>
<table name="aero/coefficient/CMq">
<independentVar lookup="row">velocities/u-fps</independentVar>
<tableData>
55.29 -6.0460
72.75 -6.0950
109.12 -6.1590
145.49 -6.2020
181.87 -6.2450
218.24 -6.2920
</tableData>
</table>
</product>
</function>
<function name="aero/moment/Pitch_alphadot">
<description>
Pitch moment coefficient due to AOA rate
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>aero/ci2vel</property>
<property>aero/alphadot-rad_sec</property>
<table name="aero/coefficient/CMadot">
<independentVar lookup="row">aero/alpha-deg</independentVar>
<independentVar lookup="column">velocities/u-fps</independentVar>
<tableData>
55.29 72.75 109.12 145.49 181.87 218.24
-4 -2.9590 -3.0030 -3.0620 -3.1050 -3.1440 -3.1820
-2 -3.1300 -3.1750 -3.2360 -3.2810 -3.3230 -3.3630
-1 -3.2640 -3.3080 -3.3700 -3.4160 -3.4580 -3.4990
0 -3.3620 -3.4040 -3.4610 -3.5050 -3.5460 -3.5860
2 -3.3910 -3.4260 -3.4760 -3.5180 -3.5590 -3.5970
4 -3.3320 -3.3620 -3.4110 -3.4590 -3.5060 -3.5450
6 -3.1120 -3.1260 -3.1730 -3.2400 -3.3080 -3.3530
8 -2.6690 -2.6660 -2.7090 -2.7970 -2.8860 -2.9370
10 -2.1010 -2.0900 -2.1270 -2.2130 -2.2930 -2.3360
12 -1.4970 -1.4500 -1.4750 -1.5740 -1.6470 -1.6850
14 -0.5463 -0.3954 -0.3888 -0.5529 -0.6947 -0.7544
</tableData>
</table>
</product>
</function>
<function name="aero/moment/Pitch_ground_effect">
<description>
Pitch Moment due to ground effect
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<table name="aero/coefficient/CMground">
<independentVar lookup="row">position/h-agl-ft</independentVar>
<independentVar lookup="column">velocities/u-fps</independentVar>
<tableData>
5.0 10.0 20.0 30.0
-4 0.0058 0.0025 0.0008 0.0
-2 0.0132 0.0053 0.0017 0.0
-1 0.0213 0.0083 0.0027 0.0
0 0.0288 0.0124 0.0040 0.0
2 0.0395 0.0170 0.0055 0.0
4 0.0523 0.0220 0.0072 0.0
6 0.0686 0.0291 0.0095 0.0
8 0.0857 0.0382 0.0126 0.0
10 0.1017 0.0476 0.0161 0.0
12 0.1157 0.0567 0.0192 0.0
14 0.1290 0.0669 0.0243 0.0
</tableData>
</table>
</product>
</function>
<function name="aero/moment/Pitch_elevator">
<description>
Pitch moment due to elevator deflection
Positive surface deflection is trailing edge down
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<table name="aero/coefficient/CMDe">
<independentVar lookup="row">fcs/elevator-pos-deg</independentVar>
<tableData>
-32 0.3049
-20 0.2512
-10 0.1685
-5 0.0843
0 -0.0002
5 -0.0843
10 -0.1685
20 -0.2512
27 -0.2767
</tableData>
</table>
</product>
</function>
</axis>
<!-- ********************************************************************** -->
<axis name="YAW">
<function name="aero/moment/Yaw_beta">
<description>
Yaw moment due to sideslip(per radian)
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/beta-rad</property>
<table name="aero/coefficient/CNb">
<independentVar lookup="row">aero/alpha-deg</independentVar>
<independentVar lookup="column">velocities/u-fps</independentVar>
<tableData>
55.29 72.75 109.12 145.49 181.87 218.24
-4 0.0193 0.0182 0.0166 0.0155 0.0146 0.0139
-2 0.0179 0.0168 0.0152 0.0141 0.0132 0.0125
-1 0.0168 0.0158 0.0142 0.0130 0.0121 0.0114
0 0.0156 0.0145 0.0129 0.0118 0.0109 0.0102
2 0.0124 0.0113 0.0096 0.0085 0.0076 0.0069
4 0.0082 0.0071 0.0054 0.0042 0.0033 0.0025
6 0.0030 0.0019 0.0002 -0.0011 -0.0020 -0.0028
8 -0.0028 -0.0039 -0.0057 -0.0070 -0.0081 -0.0089
10 -0.0089 -0.0100 -0.0118 -0.0133 -0.0145 -0.0153
12 -0.0151 -0.0162 -0.0181 -0.0197 -0.0210 -0.0219
14 -0.0209 -0.0219 -0.0238 -0.0258 -0.0273 -0.0283
</tableData>
</table>
</product>
</function>
<function name="aero/moment/Yaw_rollrate">
<description>
Yaw moment coefficient due to roll rate(per radian)
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/p-aero-rad_sec</property>
<table name="aero/coefficient/CNp">
<independentVar lookup="row">aero/alpha-deg</independentVar>
<independentVar lookup="column">velocities/u-fps</independentVar>
<tableData>
55.29 72.75 109.12 145.49 181.87 218.24
-4 0.0195 0.0197 0.0198 0.0198 0.0199 0.0199
-2 -0.0097 -0.0098 -0.0100 -0.0101 -0.0101 -0.0102
-1 -0.0249 -0.0251 -0.0254 -0.0257 -0.0258 -0.0259
0 -0.0405 -0.0409 -0.0413 -0.0416 -0.0418 -0.0420
2 -0.0728 -0.0734 -0.0741 -0.0746 -0.0750 -0.0752
4 -0.1061 -0.1068 -0.1078 -0.1085 -0.1091 -0.1095
6 -0.1370 -0.1376 -0.1388 -0.1403 -0.1416 -0.1423
8 -0.1581 -0.1583 -0.1599 -0.1627 -0.1655 -0.1666
10 -0.1715 -0.1716 -0.1736 -0.1771 -0.1804 -0.1819
12 -0.1752 -0.1731 -0.1756 -0.1823 -0.1870 -0.1890
14 -0.1370 -0.1285 -0.1301 -0.1424 -0.1527 -0.1570
</tableData>
</table>
</product>
</function>
<function name="aero/moment/Yaw_yawrate">
<description>
Yaw Moment coefficient due to yaw rate(per radian)
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/r-aero-rad_sec</property>
<table name="aero/coefficient/CNr">
<independentVar lookup="row">aero/alpha-deg</independentVar>
<independentVar lookup="column">velocities/u-fps</independentVar>
<tableData>
55.29 72.75 109.12 145.49 181.87 218.24
-4 -0.0403 -0.0403 -0.0403 -0.0403 -0.0404 -0.0404
-2 -0.0407 -0.0407 -0.0407 -0.0408 -0.0408 -0.0409
-1 -0.0410 -0.0410 -0.0411 -0.0411 -0.0412 -0.0412
0 -0.0414 -0.0414 -0.0415 -0.0415 -0.0416 -0.0417
2 -0.0425 -0.0426 -0.0427 -0.0427 -0.0428 -0.0429
4 -0.0441 -0.0442 -0.0443 -0.0444 -0.0445 -0.0445
6 -0.0458 -0.0459 -0.0461 -0.0463 -0.0464 -0.0465
8 -0.0459 -0.0459 -0.0461 -0.0466 -0.0470 -0.0470
10 -0.0439 -0.0438 -0.0441 -0.0447 -0.0452 -0.0453
12 -0.0389 -0.0383 -0.0386 -0.0399 -0.0407 -0.0408
14 -0.0224 -0.0202 -0.0202 -0.0227 -0.0248 -0.0254
</tableData>
</table>
</product>
</function>
<function name="aero/moment/Yaw_aileron">
<description>
Yaw Moment due to Ailerons
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<value>0.005</value> <!-- Cub has Frise style ailerons - so reduce datcom aileron yaw moment estimate -->
<table name="aero/coefficient/CNDa">
<independentVar lookup="row">aero/alpha-deg</independentVar>
<independentVar lookup="column">fcs/diff-aileron-pos-deg</independentVar>
<tableData>
-56 -42 -28 -14 0 14 28 42 56
-4 -0.00244 -0.00220 -0.00173 -0.00088 0.00000 0.00088 0.00173 0.00220 0.00244
-2 -0.00516 -0.00464 -0.00366 -0.00187 0.00000 0.00187 0.00366 0.00464 0.00516
-1 -0.00656 -0.00591 -0.00466 -0.00237 0.00000 0.00237 0.00466 0.00591 0.00656
0 -0.00799 -0.00719 -0.00567 -0.00289 0.00000 0.00289 0.00567 0.00719 0.00799
2 -0.01091 -0.00982 -0.00775 -0.00395 0.00000 0.00395 0.00775 0.00982 0.01091
4 -0.01390 -0.01251 -0.00987 -0.00503 0.00000 0.00503 0.00987 0.01251 0.01390
6 -0.01692 -0.01523 -0.01201 -0.00612 0.00000 0.00612 0.01201 0.01523 0.01692
8 -0.01942 -0.01748 -0.01378 -0.00702 0.00000 0.00702 0.01378 0.01748 0.01942
10 -0.02140 -0.01926 -0.01518 -0.00773 0.00000 0.00773 0.01518 0.01926 0.02140
12 -0.02285 -0.02057 -0.01622 -0.00826 0.00000 0.00826 0.01622 0.02057 0.02285
14 -0.02369 -0.02132 -0.01681 -0.00856 0.00000 0.00856 0.01681 0.02132 0.02369
16 -0.02214 -0.01993 -0.01571 -0.00800 0.00000 0.00800 0.01571 0.01993 0.02214
</tableData>
</table>
</product>
</function>
<function name="aero/moment/Yaw_rudder">
<description>
Yaw Coefficient due to rudder(Estimated value)
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/rudder-pos-rad</property>
<value> -.06</value> <!-- Estimate -->
</product>
</function>
</axis>
<!-- ********************************************************************** -->
<function name="aero/elev_hinge_moment_ft_lbs">
<description>
Elevator hinge moment in ft-lbs
HM = q * S * Cbar * ( Ch0 + Cha*alpha + Chd*delta )
Positive causes trailing edge down movement
Ch0 is used to artificially trim HM to zero
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<value> 5.325 </value> <!-- surface area of elevator -->
<value> 1.212 </value> <!-- MAC of elevator -->
<sum>
<!--
<property>aero/Ch0_elev</property>
-->
<product>
<property>aero/alpha-rad</property>
<table> <!-- Ch-alpha -->
<independentVar lookup="row">
aero/alpha-rad</independentVar>
<tableData>
-.6981E-01 -.2741E-02
-.3491E-01 -.2741E-02
-.1745E-01 -.2741E-02
.000 -.2741E-02
.3491E-01 -.2741E-02
.6981E-01 -.2741E-02
.1047 -.2741E-02
.1396 -.2741E-02
.1745 -.2741E-02
.2094 -.2741E-02
.2443 .5350E-03
</tableData>
</table>
</product>
<product>
<property>fcs/elevator-pos-rad</property>
<table> <!-- Ch-delta elevator -->
<independentVar lookup="row">
fcs/elevator-pos-rad</independentVar>
<tableData>
-.3491 .5350E-03
-.2618 .1175E-02
-.1745 .1369E-02
-.8727E-01 .1369E-02
.000 .1369E-02
.8727E-01 .1369E-02
.1745 .1369E-02
.2618 .1175E-02
.3491 .5350E-03
</tableData>
</table>
</product>
</sum>
</product>
</function>
</aerodynamics>