jsbsim.js
Version:
JSBSim flight dynamics model ported to JavaScript
1,166 lines (1,049 loc) • 58.7 kB
text/xml
<?xml version="1.0"?>
<!--
****************** IMPORTANT NOTICES **********************
This file was generated by Datcom+, a superset of
the USAF Digital DATCOM program.
This file is considered an intermediary file in the
DATCOM/JSBSim process. This file may be overwritten without
warning, so any changes that you make in here may be lost.
If you intend to use this file as it is and modify it, make
sure that you take the necessary precautions to prevent it
from being overwritten, like renaming it.
***********************************************************
DISCLAIMER REQUIRED BY HQ USAF FOR PUBLIC RELEASE APPROVAL
THIS SOFTWARE AND ANY ACCOMPANYING DOCUMENTATION
IS RELEASED "AS IS". THE U.S. GOVERNMENT MAKES NO
WARRANTY OF ANY KIND, EXPRESS OR IMPLIED, CONCERNING
THIS SOFTWARE AND ANY ACCOMPANYING DOCUMENTATION,
INCLUDING, WITHOUT LIMITATION, ANY WARRANTIES OF
MERCHANTABILITY OR FITNESS FOR A PARTICULAR PURPOSE.
IN NO EVENT WILL THE U.S. GOVERNMENT BE LIABLE FOR ANY
DAMAGES, INCLUDING LOST PROFITS, LOST SAVINGS OR OTHER
INCIDENTAL OR CONSEQUENTIAL DAMAGES ARISING OUT OF THE
USE, OR INABILITY TO USE, THIS SOFTWARE OR ANY
ACCOMPANYING DOCUMENTATION, EVEN IF INFORMED IN ADVANCE
OF THE POSSIBILITY OF SUCH DAMAGES.
***********************************************************
-->
<!-- **********************************************************************
AERODYNAMICS
*******************************************************************-->
<aerodynamics>
<alphalimits unit="RAD">
<min> -.2793 </min>
<max> .4189 </max>
</alphalimits>
<!-- *************************
Sign Conventions
*************************
Control displacements
Stick FWD + / Aft -
Stick Left + / Right -
Wheel CCW + / CW -
Pedal Left + / Right -
Elevator trim Nose Up + / Nose down -
Surfaces
Elevator TED + / TEU -
R Ail TED + / TEU -
L Ail TED + / TEU -
Rudder TEL + / TER -
F&M, Accel, Rates, Displacements
Pitch Up + / Down -
Roll Rgt + / Left -
Yaw Rgt + / Left -
Other
Alpha Up + / Down -
Beta Wind in right ear + / Wind in left ear -
Slip Ball right of center + / left of center -
-->
<!-- **************************************
ASSUMPTIONS AND LIMITATIONS
There is no interaction between deflected surfaces modeled
so there is no change in elevator effects with the flaps
deflected, for example.
Terms known to be missing from DATCOM:
Power effects
Ground effects
Cyr, CyDr, Cyda, ClDr, Cndr
**************************************
-->
<!--
The following ground effect tables are NOT generated
by DATCOM, but provide representative effects.
These terms are not currently used in this model.
-->
<function name="aero/function/ground-effect-factor-lift">
<description>Change in lift due to ground effect factor</description>
<product>
<table>
<independentVar lookup="row">aero/h_b-mac-ft</independentVar>
<tableData>
0.0 1.203
0.1 1.127
0.15 1.090
0.2 1.073
0.3 1.046
0.4 1.055
0.5 1.019
0.6 1.013
0.7 1.008
0.8 1.006
0.9 1.003
1.0 1.002
1.1 1.0
</tableData>
</table>
</product>
</function>
<function name="aero/function/ground-effect-factor-drag">
<description>Change in drag due to ground effect</description>
<product>
<table>
<independentVar lookup="row">aero/h_b-mac-ft</independentVar>
<tableData>
0.0 0.480
0.1 0.515
0.15 0.629
0.2 0.709
0.3 0.815
0.4 0.882
0.5 0.928
0.6 0.962
0.7 0.988
0.8 1.0
0.9 1.0
1.0 1.0
1.1 1.0
</tableData>
</table>
</product>
</function>
<!-- ********************************************************************** -->
<axis name="LIFT">
<function name="aero/coefficient/CLwbh">
<description>
Lift due to alpha
Increase in CL decreases Period and damping,Dutch Roll damping
CL is low for landing
</description>
<product>
<property>aero/function/ground-effect-factor-lift</property>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<!-- The wing incidence is 3 deg. -->
<!-- value>0.90</value --> <!-- Make CL at 17-3 deg. 1.65. -->
<value>0.83</value> <!-- Make CL at 12-3 deg. 1.30. -->
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<tableData>
-.2793 -1.205
-.1745 -.5125
-.1396 -.2906
-.1047 -.7663E-01
-.6981E-01 .1375
-.3491E-01 .3586
.000 .5854
.3491E-01 .8176
.6981E-01 1.055
.1396 1.490
.1745 1.654
.2094 1.776
.2443 1.845
.2618 1.837
.2793 1.807
.2967 1.554
.3142 1.203
.3491 .6313
.3840 .1405
.4189 -.2022
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CLq">
<description>
Basic Lift Coefficient due to pitch rate(per radian)
</description>
<product>
<property>velocities/q-aero-rad_sec</property>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/ci2vel</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<tableData>
-.2793 7.488
-.1745 7.488
-.1396 7.488
-.1047 7.488
-.6981E-01 7.488
-.3491E-01 7.488
.000 7.488
.3491E-01 7.488
.6981E-01 7.488
.1396 7.488
.1745 7.488
.2094 7.488
.2443 7.488
.2618 7.488
.2793 7.488
.2967 7.488
.3142 7.488
.3491 7.488
.3840 7.488
.4189 7.488
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CLad">
<description>
Basic Lift Coefficient due to AOA rate
Important contributor to Short-Period damping
For low Cla, aircraft must land at high alpha
</description>
<product>
<property>aero/alphadot-rad_sec</property>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/ci2vel</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<tableData>
-.2793 1.783
-.1745 1.841
-.1396 1.857
-.1047 1.881
-.6981E-01 1.954
-.3491E-01 2.044
.000 2.118
.3491E-01 2.079
.6981E-01 1.933
.1396 1.536
.1745 1.196
.2094 .7401
.2443 .3574
.2618 -.6955
.2793 -1.752
.2967 -3.991
.3142 -5.246
.3491 -3.057
.3840 -2.436
.4189 -2.063
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CLdF3L">
<description>
Lift Coefficient due to Left Fowler Flaps Deflection
Positive surface deflection is trailing edge down
Ultimately, we will feed this left flap pos
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar lookup="row">fcs/flap-pos-deg</independentVar>
<tableData>
.000 .000
8.000 .2988E-01
12.00 .5975E-01
25.00 .1285
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CLdF3R">
<description>
Lift Coefficient due to Right Fowler Flaps Deflection
Positive surface deflection is trailing edge down
Ultimately, we will feed this right flap pos
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar lookup="row">fcs/flap-pos-deg</independentVar>
<tableData>
.000 .000
8.000 .2988E-01
12.00 .5975E-01
25.00 .1285
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CLDe">
<description>
Lift Coefficient due to Elevator Deflection
Positive surface deflection is trailing edge down
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar lookup="row">fcs/elevator-pos-rad</independentVar>
<tableData>
-.3491 -.1026
-.2618 -.9847E-01
-.1745 -.7035E-01
-.8727E-01 -.3518E-01
.000 .7035E-04
.8727E-01 .3518E-01
.1745 .7035E-01
.2618 .9847E-01
.3491 .1026
</tableData>
</table>
</product>
</function>
</axis>
<!-- ********************************************************************** -->
<axis name="DRAG">
<function name="aero/coefficient/CD">
<description>
Basic Drag Coefficient
Sense: Always positive
Main contributor to Phugoid damping: Greater Cd, Better damping
</description>
<product>
<property>aero/function/ground-effect-factor-drag</property>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<value>1.30</value> <!-- Adjusted for climb time. -->
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<tableData>
-.2793 .7340E-01
-.1745 .2602E-01
-.1396 .1883E-01
-.1047 .1537E-01
-.6981E-01 .1568E-01
-.3491E-01 .1983E-01
.000 .2837E-01
.3491E-01 .4131E-01
.6981E-01 .5898E-01
.1396 .1021
.1745 .1211
.2094 .1365
.2443 .1458
.2618 .1429
.2793 .1390
.2967 .1005
.3142 .7088E-01
.3491 .4924E-01
.3840 .4910E-01
.4189 .5829E-01
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CdDf3L">
<description>
Drag Coefficient due to Left Fowler Flaps Deflection
Positive surface deflection is trailing edge down
Ultimately, we will feed this left flap pos
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar lookup="row">aero/alpha-deg</independentVar>
<independentVar lookup="column">fcs/flap-pos-deg</independentVar>
<tableData>
.000 8.000 12.00 25.00
-16.00 .000 -.2250E-02 -.4354E-02 -.8641E-02
-10.00 .000 -.1154E-02 -.2163E-02 -.3929E-02
-8.000 .000 -.7889E-03 -.1432E-02 -.2359E-02
-6.000 .000 -.4237E-03 -.7018E-03 -.7887E-03
-4.000 .000 -.5849E-04 .2865E-04 .7817E-03
-2.000 .000 .3067E-03 .7591E-03 .2352E-02
.000 .000 .6719E-03 .1489E-02 .3922E-02
2.000 .000 .1037E-02 .2220E-02 .5493E-02
4.000 .000 .1402E-02 .2950E-02 .7063E-02
8.000 .000 .2133E-02 .4411E-02 .1020E-01
10.00 .000 .2498E-02 .5142E-02 .1177E-01
12.00 .000 .2863E-02 .5872E-02 .1334E-01
14.00 .000 .3228E-02 .6602E-02 .1492E-01
15.00 .000 .3411E-02 .6968E-02 .1570E-01
16.00 .000 .3594E-02 .7333E-02 .1649E-01
17.00 .000 .3776E-02 .7698E-02 .1727E-01
18.00 .000 .3959E-02 .8063E-02 .1806E-01
20.00 .000 .4324E-02 .8794E-02 .1963E-01
22.00 .000 .4689E-02 .9524E-02 .2120E-01
24.00 .000 .5054E-02 .1025E-01 .2277E-01
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CdDf3R">
<description>
Drag Coefficient due to Right Fowler Flaps Deflection
Positive surface deflection is trailing edge down
Ultimately, we will feed this right flap pos
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar lookup="row">aero/alpha-deg</independentVar>
<independentVar lookup="column">fcs/flap-pos-deg</independentVar>
<tableData>
.000 8.000 12.00 25.00
-16.00 .000 -.2250E-02 -.4354E-02 -.8641E-02
-10.00 .000 -.1154E-02 -.2163E-02 -.3929E-02
-8.000 .000 -.7889E-03 -.1432E-02 -.2359E-02
-6.000 .000 -.4237E-03 -.7018E-03 -.7887E-03
-4.000 .000 -.5849E-04 .2865E-04 .7817E-03
-2.000 .000 .3067E-03 .7591E-03 .2352E-02
.000 .000 .6719E-03 .1489E-02 .3922E-02
2.000 .000 .1037E-02 .2220E-02 .5493E-02
4.000 .000 .1402E-02 .2950E-02 .7063E-02
8.000 .000 .2133E-02 .4411E-02 .1020E-01
10.00 .000 .2498E-02 .5142E-02 .1177E-01
12.00 .000 .2863E-02 .5872E-02 .1334E-01
14.00 .000 .3228E-02 .6602E-02 .1492E-01
15.00 .000 .3411E-02 .6968E-02 .1570E-01
16.00 .000 .3594E-02 .7333E-02 .1649E-01
17.00 .000 .3776E-02 .7698E-02 .1727E-01
18.00 .000 .3959E-02 .8063E-02 .1806E-01
20.00 .000 .4324E-02 .8794E-02 .1963E-01
22.00 .000 .4689E-02 .9524E-02 .2120E-01
24.00 .000 .5054E-02 .1025E-01 .2277E-01
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CdDe">
<description>
Drag Coefficient due to Elevator Deflection
Positive surface deflection is trailing edge down
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">fcs/elevator-pos-rad</independentVar>
<tableData>
-.3491 -.2618 -.1745 -.8727E-01 .000 .8727E-01 .1745 .2618 .3491
-.2793 .1322E-01 .1247E-01 .7884E-02 .3304E-02 -.5331E-05 -.2029E-02 -.2784E-02 -.2468E-02 -.2352E-02
-.1745 .1010E-01 .9482E-02 .5748E-02 .2237E-02 -.3196E-05 -.9616E-03 -.6481E-03 .5232E-03 .7662E-03
-.1396 .9101E-02 .8520E-02 .5061E-02 .1893E-02 -.2508E-05 -.6180E-03 .3911E-04 .1486E-02 .1770E-02
-.1047 .8094E-02 .7554E-02 .4371E-02 .1548E-02 -.1819E-05 -.2732E-03 .7287E-03 .2452E-02 .2776E-02
-.6981E-01 .7113E-02 .6613E-02 .3699E-02 .1212E-02 -.1147E-05 .6281E-04 .1401E-02 .3393E-02 .3757E-02
-.3491E-01 .6175E-02 .5712E-02 .3056E-02 .8907E-03 -.5039E-06 .3843E-03 .2044E-02 .4293E-02 .4696E-02
.000 .5277E-02 .4851E-02 .2442E-02 .5833E-03 .1110E-06 .6917E-03 .2658E-02 .5155E-02 .5594E-02
.3491E-01 .4408E-02 .4017E-02 .1846E-02 .2855E-03 .7066E-06 .9895E-03 .3254E-02 .5989E-02 .6463E-02
.6981E-01 .3474E-02 .3121E-02 .1206E-02 -.3437E-04 .1346E-05 .1309E-02 .3894E-02 .6885E-02 .7397E-02
.1396 .1391E-02 .1122E-02 -.2204E-03 -.7477E-03 .2773E-05 .2023E-02 .5320E-02 .8883E-02 .9480E-02
.1745 .1802E-03 -.3896E-04 -.1049E-02 -.1162E-02 .3602E-05 .2437E-02 .6150E-02 .1004E-01 .1069E-01
.2094 -.1233E-02 -.1395E-02 -.2018E-02 -.1646E-02 .4570E-05 .2921E-02 .7118E-02 .1140E-01 .1210E-01
.2443 -.2847E-02 -.2943E-02 -.3123E-02 -.2199E-02 .5675E-05 .3474E-02 .8223E-02 .1295E-01 .1372E-01
.2618 -.3708E-02 -.3769E-02 -.3713E-02 -.2494E-02 .6265E-05 .3769E-02 .8813E-02 .1377E-01 .1458E-01
.2793 -.5045E-02 -.5052E-02 -.4629E-02 -.2952E-02 .7182E-05 .4227E-02 .9729E-02 .1506E-01 .1592E-01
.2967 -.6388E-02 -.6341E-02 -.5549E-02 -.3412E-02 .8102E-05 .4687E-02 .1065E-01 .1635E-01 .1726E-01
.3142 -.8765E-02 -.8621E-02 -.7177E-02 -.4226E-02 .9724E-05 .5501E-02 .1228E-01 .1863E-01 .1964E-01
.3491 -.1217E-01 -.1188E-01 -.9506E-02 -.5391E-02 .1206E-04 .6666E-02 .1461E-01 .2189E-01 .2304E-01
.3840 -.1534E-01 -.1493E-01 -.1168E-01 -.6477E-02 .1424E-04 .7752E-02 .1678E-01 .2493E-01 .2621E-01
.4189 -.1816E-01 -.1764E-01 -.1361E-01 -.7444E-02 .1615E-04 .8719E-02 .1871E-01 .2764E-01 .2903E-01
</tableData>
</table>
</product>
</function>
</axis>
<!-- ********************************************************************** -->
<axis name="SIDE">
<function name="aero/coefficient/Cyb">
<description>
Side Force coefficient due to Sideslip
Contributes to damping of Dutch Roll mode
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<sin><property>aero/beta-rad</property></sin>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<tableData>
-.2793 -.5277
-.1745 -.5277
-.1396 -.5277
-.1047 -.5277
-.6981E-01 -.5277
-.3491E-01 -.5277
.000 -.5277
.3491E-01 -.5277
.6981E-01 -.5277
.1396 -.5277
.1745 -.5277
.2094 -.5277
.2443 -.5277
.2618 -.5277
.2793 -.5277
.2967 -.5277
.3142 -.5277
.3491 -.5277
.3840 -.5277
.4189 -.5277
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Cyp">
<description>
Side Force Coefficient due to Roll Rate
</description>
<product>
<property>velocities/p-aero-rad_sec</property>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/bi2vel</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<tableData>
-.2793 -.8364E-01
-.1745 -.1082
-.1396 -.1154
-.1047 -.1221
-.6981E-01 -.1295
-.3491E-01 -.1385
.000 -.1496
.3491E-01 -.1635
.6981E-01 -.1827
.1396 .1989
.1745 -.1426
.2094 -.1626
.2443 -.1731
.2618 -.1675
.2793 -.1696
.2967 -.1282
.3142 -.7662E-01
.3491 .3365E-02
.3840 .7152E-01
.4189 .1194
</tableData>
</table>
</product>
</function>
<!-- ************************
Not calculated by DATCOM
************************
-->
<function name="aero/coefficient/Cyr">
<description>
Side Force due to Yaw Rate (DATCOM does not calculate)
Effect is small
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/bi2vel</property>
<property>velocities/r-aero-rad_sec</property>
<value> .000 </value>
</product>
</function>
<!-- ************************
Not calculated by DATCOM
************************
-->
<function name="aero/coefficient/CyDr">
<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> .000 </value>
</product>
</function>
<!-- ************************
Not calculated by DATCOM
************************
-->
<function name="aero/coefficient/CyDa">
<description>
Side Force due to aileron (DATCOM does not calculate)
Usually neglected
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/Sw-sqft</property>
<property>fcs/left-aileron-pos-rad</property>
<value> .000 </value>
</product>
</function>
</axis>
<!-- ********************************************************************** -->
<axis name="ROLL">
<function name="aero/coefficient/Clb">
<description>
Roll Moment coefficient due to Beta
Decrease of Clb to small negative value improves Dutch Roll Damping
High Positive value leads to excessive spiral instability
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<sin><property>aero/beta-rad</property></sin>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<tableData>
-.2793 -.1357
-.1745 -.1271
-.1396 -.1240
-.1047 -.1208
-.6981E-01 -.1175
-.3491E-01 -.1142
.000 -.1110
.3491E-01 -.1079
.6981E-01 -.1048
.1396 -.9820E-01
.1745 -.9428E-01
.2094 -.8986E-01
.2443 -.8483E-01
.2618 -.8170E-01
.2793 -.7824E-01
.2967 -.7208E-01
.3142 -.6456E-01
.3491 -.5134E-01
.3840 -.3930E-01
.4189 -.2910E-01
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Clp">
<description>
Roll Moment coefficient due to roll rate
Clp alone determines damping-in-roll characteristics
</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>
<value>-1.0</value>
<table>
<independentVar lookup="row">aero/alpha-deg</independentVar>
<tableData>
-16.00 .3294
-10.00 .3162
-8.000 .3085
-6.000 .3066
-4.000 .3176
-2.000 .3313
.000 .3415
2.000 .3479
4.000 .3366
8.000 .2403
10.00 .1712
12.00 .9202E-01
14.00 -.8719E-01
15.00 -.1715
16.00 -.6740
17.00 -1.212
18.00 -1.159
20.00 -.8836
22.00 -.6817
24.00 -.4080
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Clr">
<description>
Roll Moment coefficient due to yaw rate
Considerable effect on Spiral mode. Large
positive values leads to strong sprial instability
</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>
<independentVar lookup="row">aero/alpha-deg</independentVar>
<tableData>
-16.00 -.1690
-10.00 -.4933E-01
-8.000 -.1181E-01
-6.000 .2396E-01
-4.000 .6027E-01
-2.000 .9837E-01
.000 .1379
2.000 .1786
4.000 .2199
8.000 .2927
10.00 .3160
12.00 .3307
14.00 .3341
15.00 .3227
16.00 .3091
17.00 .2319
18.00 .1476
20.00 .2074E-01
22.00 -.8871E-01
24.00 -.1616
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/ClDs4">
<description>
Roll Moment coefficient due to Left Double Slotted Flaps Deflection
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<table>
<independentVar lookup="row">fcs/left-aileron-pos-rad</independentVar>
<tableData>
-.6981 -.7359E-01
-.3491 -.4245E-01
-.1745 -.2123E-01
-.8727E-01 -.1061E-01
.000 .000
.8727E-01 .1061E-01
.1745 .2123E-01
.3491 .4245E-01
.6981 .7359E-01
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CldF3">
<description>
Roll Moment Coefficient due to Asymetrical Fowler Flaps Deflection
calculated as difference between left and right flap lift coef,
times distance from centerline to MAC of surface.
</description>
<product>
<value> 12.24</value>
<difference>
<property>aero/coefficient/CLdF3R</property>
<property>aero/coefficient/CLdF3L</property>
</difference>
</product>
</function>
<!-- ************************
Not calculated by DATCOM
************************
-->
<function name="aero/coefficient/ClDr">
<description>
Roll moment due to rudder (DATCOM does not calculate)
Usually insignificant in dynamic stability considerations
but is used in autopilot work
</description>
<product>
<property>metrics/bw-ft</property>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/rudder-pos-rad</property>
<value> .000 </value>
</product>
</function>
</axis>
<!-- ********************************************************************** -->
<axis name="PITCH">
<function name="aero/coefficient/Cm_basic">
<description>
Basic_Pitch_moment_coefficient
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<tableData>
-.2793 .3419
-.1745 .2024
-.1396 .1567
-.1047 .1096
-.6981E-01 .6524E-01
-.3491E-01 .2272E-01
.000 -.1663E-01
.3491E-01 -.5525E-01
.6981E-01 -.9550E-01
.1396 -.1824
.1745 -.2293
.2094 -.2787
.2443 -.2787
.2618 -.2787
.2793 -.2787
.2967 -.2787
.3142 -.2787
.3491 -.2787
.3840 -.2787
.4189 -.2787
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Cmq">
<description>
Pitch moment coefficient due to pitch rate(per radian)
Pitch Damping Derivative
Very important to Short Period damping of oscillations
</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>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<tableData>
-.2793 -11.21
-.1745 -11.21
-.1396 -11.21
-.1047 -11.21
-.6981E-01 -11.21
-.3491E-01 -11.21
.000 -11.21
.3491E-01 -11.21
.6981E-01 -11.21
.1396 -11.21
.1745 -11.21
.2094 -11.21
.2443 -11.21
.2618 -11.21
.2793 -11.21
.2967 -11.21
.3142 -11.21
.3491 -11.21
.3840 -11.21
.4189 -11.21
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Cmadot">
<description>
Pitch moment coefficient due to AOA rate(per radian)
Negitive Cmad increase Short Period damping
</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>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<tableData>
-.2793 -5.541
-.1745 -5.721
-.1396 -5.770
-.1047 -5.845
-.6981E-01 -6.073
-.3491E-01 -6.351
.000 -6.583
.3491E-01 -6.461
.6981E-01 -6.006
.1396 -4.772
.1745 -3.715
.2094 -2.300
.2443 -1.111
.2618 2.161
.2793 5.443
.2967 12.40
.3142 16.30
.3491 9.499
.3840 7.571
.4189 6.410
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CmDe">
<description>
Pitch moment coefficient 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>
<independentVar lookup="row">fcs/elevator-pos-rad</independentVar>
<tableData>
-.3491 .2876
-.2618 .2748
-.1745 .1961
-.8727E-01 .9804E-01
.000 -.1961E-03
.8727E-01 -.9804E-01
.1745 -.1961
.2618 -.2748
.3491 -.2880
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CmDf3L">
<description>
Pitch moment coefficient due to left Fowler Flaps Deflection
Positive surface deflection is trailing edge down
Ultimately, we will feed this left flap pos
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<table>
<independentVar lookup="row">fcs/flap-pos-deg</independentVar>
<tableData>
.000 .000
8.000 -.1259E-02
12.00 -.2519E-02
25.00 -.5416E-02
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CmDf3R">
<description>
Pitch moment coefficient due to right Fowler Flaps Deflection
Positive surface deflection is trailing edge down
Ultimately, we will feed this right flap pos
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<table>
<independentVar lookup="row">fcs/flap-pos-deg</independentVar>
<tableData>
.000 .000
8.000 -.1259E-02
12.00 -.2519E-02
25.00 -.5416E-02
</tableData>
</table>
</product>
</function>
</axis>
<!-- ********************************************************************** -->
<axis name="YAW">
<function name="aero/coefficient/Cnb">
<description>
Yaw moment coefficient due to sideslip(per radian)
Determines Dutch Roll and Spiral characteristics
Prevents side-slip and yawing moments
</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<sin><property>aero/beta-rad</property></sin>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<tableData>
-.2793 .7888E-01
-.1745 .7888E-01
-.1396 .7888E-01
-.1047 .7888E-01
-.6981E-01 .7888E-01
-.3491E-01 .7888E-01
.000 .7888E-01
.3491E-01 .7888E-01
.6981E-01 .7888E-01
.1396 .7888E-01
.1745 .7888E-01
.2094 .7888E-01
.2443 .7888E-01
.2618 .7888E-01
.2793 .7888E-01
.2967 .7888E-01
.3142 .7888E-01
.3491 .7888E-01
.3840 .7888E-01
.4189 .7888E-01
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Cnp">
<description>
Yaw moment coefficient due to roll rate(per radian)
Reduces Dutch Roll damping
positive value desireable
</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>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<tableData>
-.2793 .1331
-.1745 .6090E-01
-.1396 .3657E-01
-.1047 .1245E-01
-.6981E-01 -.1281E-01
-.3491E-01 -.4026E-01
.000 -.7038E-01
.3491E-01 -.1042
.6981E-01 -.1439
.1396 .3362
.1745 -.1310
.2094 -.1723
.2443 -.1992
.2618 -.2013
.2793 -.2039
.2967 -.1671
.3142 -.1321
.3491 -.8233E-01
.3840 -.3845E-01
.4189 -.1051E-01
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Cnr">
<description>
Yaw Moment coefficient due to yaw rate(per radian)
Main contributor to damping of Dutch Roll
</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>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<tableData>
-.2793 -.1414
-.1745 -.1455
-.1396 -.1472
-.1047 -.1490
-.6981E-01 -.1509
-.3491E-01 -.1528
.000 -.1549
.3491E-01 -.1571
.6981E-01 -.1595
.1396 -.1641
.1745 -.1653
.2094 -.1656
.2443 -.1647
.2618 -.1630
.2793 -.1610
.2967 -.1543
.3142 -.1486
.3491 -.1422
.3840 -.1388
.4189 -.1367