jsbsim.js/JSBSim/aircraft/ZLT-NT/Systems/datcom_aero.xml

JSBSim flight dynamics model ported to JavaScript

<?xml version="1.0"?>
<!--

  Zeppelin NT-07 airship flight model for JSBSim.

    Copyright (C) 2009 - 2010  Anders Gidenstam  (anders(at)gidenstam.org)

    This program is free software; you can redistribute it and/or modify
    it under the terms of the GNU General Public License as published by
    the Free Software Foundation; either version 2 of the License, or
    (at your option) any later version.
  
    This program is distributed in the hope that it will be useful,
    but WITHOUT ANY WARRANTY; without even the implied warranty of
    MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE.  See the
    GNU General Public License for more details.
  
    You should have received a copy of the GNU General Public License
    along with this program; if not, write to the Free Software
    Foundation, Inc., 59 Temple Place, Suite 330, Boston, MA  02111-1307  USA
  
-->
<!--
  This file contains an aerodynamic section for JSBSim based on coefficients
  computed by the USAF Digital DATCOM program.

  The coefficient data computed by DATCOM are based on the following
  configurations:
  - Envelope only
    - aero/force/L_env_aoa
    - aero/force/D_env_aoa
    - aero/moment/M_env_aoa
    - aero/moment/Cmq_envelope
    - aero/moment/Cnr_envelope
  - The two lower fins (with proper dihedral) only
    - aero/force/L_htail_alpha
    - aero/force/D_htail_alpha
    - aero/moment/M_htail_alpha
    - aero/moment/N_htail_beta
    - aero/moment/Cmq_htail
    - aero/force/L_dr
    - aero/force/D_de
    - aero/moment/M_de
  - Two horizontal fins only (interpreted as 2x vertical tail fin)
    - aero/force/D_vtail_beta
    - aero/force/Y_vtail_beta
    - aero/moment/N_vtail_beta
    - aero/moment/Cnr_vtail
    - aero/moment/Clp_tail (Should be split into htail and vtail)
    - aero/force/D_dr
    - aero/force/Y_dr
    - aero/moment/N_dr
-->
 <aerodynamics>

  <!-- Tuning parameter for CD, CL due to envelope alpha. -->
  <function name="aero/envelope-lift-force-tweak-factor">
   <value> 1.0 </value>
  </function>
  <!-- Tuning parameter for CM and CN due to alpha and beta. -->
  <function name="aero/envelope-moment-tweak-factor">
   <value> 0.5 </value>
  </function>
  <!-- Tuning parameter for CN for the vertical fin and rudder. -->
  <function name="aero/vtail-moment-tweak-factor">
   <value> 2.0 </value>
  </function>

  <!-- Relation between wind and body coordinate systems. -->
  <function name="aero/tmp/wx">
   <product>
    <cos>
     <property> aero/alpha-rad </property>
    </cos>
    <cos>
     <property> aero/beta-rad </property>
    </cos>
   </product>
  </function>
  <function name="aero/tmp/wy">
   <product>
    <cos>
     <property> aero/alpha-rad </property>
    </cos>
    <sin>
     <property> aero/beta-rad </property>
    </sin>
   </product>   
  </function>
  <function name="aero/tmp/wz">
   <sin>
    <property> aero/alpha-rad </property>
   </sin>
  </function>
  <function name="aero/tmp/h_wy_wz">
   <pow>
    <sum>
     <pow>
      <property> aero/tmp/wy </property>
      <value>2.0</value>
     </pow>
     <pow>
      <property> aero/tmp/wz </property>
      <value>2.0</value>
     </pow>
    </sum>
    <value>0.5</value>
   </pow>
  </function>

  <!-- Effective angle between envelope and relative wind. -->
  <function name="aero/envelope-aoa-mag-rad">
   <max>
    <value>0.0</value>
    <acos>
     <property> aero/tmp/wx </property>
    </acos>
   </max>
  </function>
  <function name="aero/envelope-aoa-mag-deg">
   <product>
    <value> 57.29578 </value>
    <property> aero/envelope-aoa-mag-rad </property>
   </product>
  </function>

  <!--
  === Envelope Lift Force ====================================
  -->
  <limitation>
   The current method of splitting L_env_aoa into LIFT and SIDE forces
   seems to have the wrong sign when alpha GT 90 and beta LT 0?
  </limitation>
  <function name="aero/force/L_env_aoa">
   <description>Total_lift_force_from_envelope_due_to_aoa</description>
   <!--
        Standard DATCOM formulation

           C = L / (q * Sref)

   -->
   <product>
    <property>aero/qbar-psf</property>
    <property>metrics/Sw-sqft</property>
    <!-- Start CL_env -->
    <property>aero/envelope-lift-force-tweak-factor</property>
    <table>
     <independentVar lookup="row">aero/envelope-aoa-mag-deg</independentVar>
     <!--  Body only coefficient computed by DATCOM. -->
     <tableData>
    0.0   0.000
    2.0   0.004
    4.0   0.009
    6.0   0.016
    8.0   0.025
   10.0   0.034
   15.0   0.063
   20.0   0.096
   25.0   0.132
   30.0   0.169
   45.0   0.251
   60.0   0.251
   75.0   0.155
   90.0   0.000
  105.0  -0.147
  120.0  -0.225
  135.0  -0.210
  150.0  -0.129
  165.0  -0.040
  180.0   0.000
     </tableData>
    </table>
   </product>
  </function>

  <!--
  === Envelope Moment ========================================
  -->
  <limitation>
   Same as for L_env_aoa.
  </limitation>
  <function name="aero/moment/M_env_aoa">
   <description>Total_moment_from_envelope_due_to_aoa</description>
   <!--
       Standard DATCOM formulation

           Cm = M / (q * Sref * Cbarr)

   -->
   <product>
    <property>aero/qbar-psf</property>
    <property>metrics/Sw-sqft</property>
    <property>metrics/cbarw-ft</property>
    <!-- Start Cm -->
    <property>aero/envelope-moment-tweak-factor</property>
    <table>
     <independentVar lookup="row">aero/envelope-aoa-mag-deg</independentVar>
     <!--  Body only coefficient computed by DATCOM. -->
     <tableData> 
    0.0     0.0000
    2.0     0.0047
    4.0     0.0094
    6.0     0.0139
    8.0     0.0184
   10.0     0.0227
   15.0     0.0329
   20.0     0.0417
   25.0     0.0488
   30.0     0.0541
   45.0     0.0576
   60.0     0.0433
   75.0     0.0177
   90.0    -0.0098
  105.0    -0.0297
  120.0    -0.0366
  135.0    -0.0308
  150.0    -0.0176
  165.0    -0.0051
  180.0     0.0000
     </tableData>
    </table>
   </product>
  </function>


  <!--
  === Forces =================================================
  -->
  <axis name="DRAG">

   <function name="aero/force/D_env_aoa">
    <description>Drag_from_envelope_due_to_angle_of_attack</description>
    <!--
        Standard DATCOM formulation

            CD = D / (q * Sref)

    -->
    <!-- Note: This function accounts for drag due to both alpha and beta. -->
    <product>
     <property>aero/qbar-psf</property>
     <property>metrics/Sw-sqft</property>
     <!-- Start CD -->
     <property>aero/envelope-lift-force-tweak-factor</property>
     <table>
      <independentVar lookup="row">aero/envelope-aoa-mag-deg</independentVar>
      <!--  Body only coefficient computed by DATCOM. -->
      <tableData>
    0.0     0.011
    2.0     0.011
    4.0     0.012
    6.0     0.013
    8.0     0.014
   10.0     0.017
   15.0     0.027
   20.0     0.045
   25.0     0.072
   30.0     0.107
   45.0     0.258
   60.0     0.440
   75.0     0.582
   90.0     0.623
  105.0     0.546
  120.0     0.384
  135.0     0.202
  150.0     0.065
  165.0     0.000
  180.0     0.011
      </tableData>
     </table>
    </product>
   </function>

   <function name="aero/force/D_htail_alpha">
    <description>Drag_from_horizontal_tail_due_to_alpha</description>
    <!--
        Standard DATCOM formulation

            CD = D / (q * Sref)

    -->
    <product>
     <property>aero/qbar-psf</property>
     <property>metrics/Sw-sqft</property>
     <!-- Start CD -->
     <value> 0.10 </value> <!-- Sref scaling. -->
     <table>  
      <independentVar lookup="row">aero/alpha-deg</independentVar>
      <!--  Wing only coefficient computed by DATCOM. -->
      <tableData>
 -180.0     0.004
 -165.0     0.007
 -150.0     0.004
 -135.0     0.014
 -120.0     0.046
 -105.0     0.036
  -90.0     0.004
  -75.0     0.073
  -60.0     0.236
  -45.0     0.306
  -30.0     0.232
  -25.0     0.182
  -20.0     0.121
  -15.0     0.066
  -10.0     0.027
   -8.0     0.017
   -6.0     0.011
   -4.0     0.006
   -2.0     0.004
    0.0     0.004
    2.0     0.004
    4.0     0.006
    6.0     0.011
    8.0     0.017
   10.0     0.027
   15.0     0.066
   20.0     0.121
   25.0     0.182
   30.0     0.232
   45.0     0.149
   60.0     0.069
   75.0     0.022
   90.0     0.004
  105.0     0.007
  120.0     0.004
  135.0     0.009
  150.0     0.004
  165.0     0.006
  180.0     0.004
      </tableData>
     </table>
    </product>
   </function>

   <function name="aero/force/D_de">
    <description>Drag_due_to_elevator_deflection</description>
    <!--
        Standard DATCOM formulation

            CD = D / (q * Sref)

    -->
    <product>
     <property>aero/qbar-psf</property>
     <property>metrics/Sw-sqft</property>
     <!-- Start CD -->
     <value> 0.10 </value> <!-- Sref scaling. -->
     <table>
      <independentVar lookup="row">aero/alpha-deg</independentVar>
      <independentVar lookup="column">fcs/elevator-pos-deg</independentVar>
      <!--  Wing only coefficient computed by DATCOM. -->
      <tableData>
                -20.0     -15.0     -10.0      -5.0       0.0       5.0      10.0      15.0      20.0
  -180.0        1.79E-01  1.63E-01  1.12E-01  5.58E-02 -1.11E-04 -5.52E-02 -1.10E-01 -1.58E-01 -1.73E-01
  -165.0        1.65E-01  1.51E-01  1.03E-01  5.14E-02 -1.01E-04 -5.08E-02 -1.01E-01 -1.46E-01 -1.59E-01
  -150.0        1.50E-01  1.37E-01  9.42E-02  4.68E-02 -9.27E-05 -4.62E-02 -9.18E-02 -1.32E-01 -1.44E-01
  -135.0        1.36E-01  1.24E-01  8.49E-02  4.21E-02 -8.37E-05 -4.15E-02 -8.25E-02 -1.19E-01 -1.30E-01
  -120.0        1.21E-01  1.10E-01  7.56E-02  3.75E-02 -7.40E-05 -3.69E-02 -7.32E-02 -1.05E-01 -1.15E-01
  -105.0        1.06E-01  9.68E-02  6.63E-02  3.28E-02 -6.46E-05 -3.22E-02 -6.39E-02 -9.18E-02 -1.00E-01
   -90.0        9.14E-02  8.34E-02  5.70E-02  2.82E-02 -5.56E-05 -2.76E-02 -5.46E-02 -7.83E-02 -8.54E-02
   -75.0        7.67E-02  6.99E-02  4.77E-02  2.35E-02 -4.64E-05 -2.29E-02 -4.53E-02 -6.49E-02 -7.07E-02
   -60.0        6.19E-02  5.64E-02  3.84E-02  1.89E-02 -3.73E-05 -1.83E-02 -3.60E-02 -5.14E-02 -5.59E-02
   -45.0        4.72E-02  4.29E-02  2.91E-02  1.42E-02 -2.78E-05 -1.36E-02 -2.67E-02 -3.79E-02 -4.12E-02
   -30.0        3.25E-02  2.95E-02  1.98E-02  9.60E-03 -1.86E-05 -9.00E-03 -1.74E-02 -2.44E-02 -2.65E-02
   -25.0        2.76E-02  2.50E-02  1.67E-02  8.05E-03 -1.55E-05 -7.45E-03 -1.43E-02 -1.99E-02 -2.15E-02
   -20.0        2.27E-02  2.05E-02  1.36E-02  6.50E-03 -1.24E-05 -5.90E-03 -1.12E-02 -1.55E-02 -1.66E-02
   -15.0        1.77E-02  1.60E-02  1.05E-02  4.95E-03 -9.30E-06 -4.35E-03 -8.10E-03 -1.10E-02 -1.17E-02
   -10.0        1.28E-02  1.15E-02  7.40E-03  3.40E-03 -6.20E-06 -2.80E-03 -5.00E-03 -6.47E-03 -6.82E-03
    -8.0        1.09E-02  9.70E-03  6.16E-03  2.78E-03 -4.96E-06 -2.18E-03 -3.76E-03 -4.67E-03 -4.85E-03
    -6.0        8.90E-03  7.91E-03  4.92E-03  2.16E-03 -3.72E-06 -1.56E-03 -2.52E-03 -2.87E-03 -2.89E-03
    -4.0        6.94E-03  6.11E-03  3.68E-03  1.54E-03 -2.48E-06 -9.40E-04 -1.28E-03 -1.08E-03 -9.22E-04
    -2.0        4.97E-03  4.31E-03  2.44E-03  9.19E-04 -1.24E-06 -3.20E-04 -4.21E-05  7.19E-04  1.04E-03
     0.0        3.01E-03  2.52E-03  1.20E-03  2.99E-04  1.20E-09  2.99E-04  1.20E-03  2.52E-03  3.01E-03
     2.0        1.04E-03  7.19E-04 -4.21E-05 -3.20E-04  1.24E-06  9.19E-04  2.44E-03  4.31E-03  4.97E-03
     4.0       -9.22E-04 -1.08E-03 -1.28E-03 -9.40E-04  2.48E-06  1.54E-03  3.68E-03  6.11E-03  6.94E-03
     6.0       -2.89E-03 -2.87E-03 -2.52E-03 -1.56E-03  3.72E-06  2.16E-03  4.92E-03  7.91E-03  8.90E-03
     8.0       -4.85E-03 -4.67E-03 -3.76E-03 -2.18E-03  4.96E-06  2.78E-03  6.16E-03  9.70E-03  1.09E-02
    10.0       -6.82E-03 -6.47E-03 -5.00E-03 -2.80E-03  6.20E-06  3.40E-03  7.40E-03  1.15E-02  1.28E-02
    15.0       -1.17E-02 -1.10E-02 -8.10E-03 -4.35E-03  9.30E-06  4.95E-03  1.05E-02  1.60E-02  1.77E-02
    20.0       -1.66E-02 -1.55E-02 -1.12E-02 -5.90E-03  1.24E-05  6.50E-03  1.36E-02  2.05E-02  2.27E-02
    25.0       -2.15E-02 -1.99E-02 -1.43E-02 -7.45E-03  1.55E-05  8.05E-03  1.67E-02  2.50E-02  2.76E-02
    30.0       -2.65E-02 -2.44E-02 -1.74E-02 -9.00E-03  1.86E-05  9.60E-03  1.98E-02  2.95E-02  3.25E-02
    45.0       -4.12E-02 -3.79E-02 -2.67E-02 -1.36E-02  2.80E-05  1.42E-02  2.91E-02  4.29E-02  4.72E-02
    60.0       -5.59E-02 -5.14E-02 -3.60E-02 -1.83E-02  3.73E-05  1.89E-02  3.84E-02  5.64E-02  6.19E-02
    75.0       -7.07E-02 -6.49E-02 -4.53E-02 -2.29E-02  4.67E-05  2.35E-02  4.77E-02  6.99E-02  7.67E-02
    90.0       -8.54E-02 -7.83E-02 -5.46E-02 -2.76E-02  5.62E-05  2.82E-02  5.70E-02  8.34E-02  9.14E-02
   105.0       -1.00E-01 -9.18E-02 -6.39E-02 -3.22E-02  6.56E-05  3.28E-02  6.63E-02  9.68E-02  1.06E-01
   120.0       -1.15E-01 -1.05E-01 -7.32E-02 -3.69E-02  7.39E-05  3.75E-02  7.56E-02  1.10E-01  1.21E-01
   135.0       -1.30E-01 -1.19E-01 -8.25E-02 -4.15E-02  8.42E-05  4.21E-02  8.49E-02  1.24E-01  1.36E-01
   150.0       -1.44E-01 -1.32E-01 -9.18E-02 -4.62E-02  9.37E-05  4.68E-02  9.42E-02  1.37E-01  1.50E-01
   165.0       -1.59E-01 -1.46E-01 -1.01E-01 -5.08E-02  1.05E-04  5.14E-02  1.03E-01  1.51E-01  1.65E-01
   180.0       -1.73E-01 -1.58E-01 -1.10E-01 -5.52E-02  1.12E-04  5.58E-02  1.12E-01  1.63E-01  1.79E-01
      </tableData>
     </table>
    </product>
   </function>

   <function name="aero/force/D_vtail_beta">
    <description>Drag_from_vertical_tail_fin_due_to_beta</description>
    <!--
        Standard DATCOM formulation

            CD = D / (q * Sref)

    -->
    <product>
     <property>aero/qbar-psf</property>
     <property>metrics/Sw-sqft</property>
     <!-- Start CD -->
     <value> 0.10 </value> <!-- Sref scaling. -->
     <value> 0.50 </value> <!-- There is only one vertical tail fin. -->
     <table>  
      <independentVar lookup="row">aero/beta-deg</independentVar>
      <!--  Wing only coefficient computed by DATCOM. -->
      <tableData>
 -180.0     0.004
 -165.0     0.008
 -150.0     0.005
 -135.0     0.008
 -120.0     0.034
 -105.0     0.030
  -90.0     0.004
  -75.0     0.064
  -60.0     0.212
  -45.0     0.282
  -30.0     0.219
  -25.0     0.175
  -20.0     0.119
  -15.0     0.065
  -10.0     0.027
   -8.0     0.017
   -6.0     0.011
   -4.0     0.007
   -2.0     0.005
    0.0     0.004
    2.0     0.005
    4.0     0.007
    6.0     0.011
    8.0     0.017
   10.0     0.027
   15.0     0.065
   20.0     0.119
   25.0     0.175
   30.0     0.219
   45.0     0.131
   60.0     0.062
   75.0     0.021
   90.0     0.004
  105.0     0.006
  120.0     0.006
  135.0     0.015
  150.0     0.006
  165.0     0.008
  180.0     0.004
      </tableData>
     </table>
    </product>
   </function>

   <function name="aero/force/D_dr">
    <description>Drag_due_to_rudder_deflection</description>
    <!--
        Standard DATCOM formulation

            CD = D / (q * Sref)

    -->
    <product>
     <property>aero/qbar-psf</property>
     <property>metrics/Sw-sqft</property>
     <!-- Start CD -->
     <value> 0.10 </value> <!-- Sref scaling. -->
     <value> 0.50 </value> <!-- There is only one vertical tail fin. -->
     <table>  
      <independentVar lookup="row">aero/beta-deg</independentVar>
      <independentVar lookup="column">fcs/rudder-pos-deg</independentVar>
      <!--  Wing only coefficient computed by DATCOM. -->
      <tableData>
                -20.0     -15.0     -10.0      -5.0       0.0       5.0      10.0      15.0      20.0
  -180.0        1.53E-01  1.40E-01  9.62E-02  4.79E-02 -9.51E-05 -4.74E-02 -9.43E-02 -1.36E-01 -1.48E-01
  -165.0        1.41E-01  1.29E-01  8.87E-02  4.41E-02 -8.75E-05 -4.37E-02 -8.69E-02 -1.25E-01 -1.36E-01
  -150.0        1.28E-01  1.18E-01  8.08E-02  4.01E-02 -7.96E-05 -3.97E-02 -7.89E-02 -1.14E-01 -1.24E-01
  -135.0        1.16E-01  1.06E-01  7.28E-02  3.62E-02 -7.18E-05 -3.57E-02 -7.09E-02 -1.02E-01 -1.11E-01
  -120.0        1.03E-01  9.44E-02  6.48E-02  3.22E-02 -6.46E-05 -3.17E-02 -6.29E-02 -9.05E-02 -9.84E-02
  -105.0        9.05E-02  8.29E-02  5.68E-02  2.82E-02 -5.64E-05 -2.77E-02 -5.49E-02 -7.89E-02 -8.58E-02
   -90.0        7.79E-02  7.13E-02  4.88E-02  2.42E-02 -4.77E-05 -2.37E-02 -4.70E-02 -6.74E-02 -7.32E-02
   -75.0        6.53E-02  5.98E-02  4.08E-02  2.02E-02 -3.98E-05 -1.97E-02 -3.90E-02 -5.58E-02 -6.06E-02
   -60.0        5.27E-02  4.82E-02  3.29E-02  1.62E-02 -3.19E-05 -1.57E-02 -3.10E-02 -4.43E-02 -4.80E-02
   -45.0        4.01E-02  3.66E-02  2.49E-02  1.22E-02 -2.39E-05 -1.17E-02 -2.30E-02 -3.27E-02 -3.54E-02
   -30.0        2.75E-02  2.51E-02  1.69E-02  8.22E-03 -1.60E-05 -7.75E-03 -1.50E-02 -2.12E-02 -2.28E-02
   -25.0        2.33E-02  2.12E-02  1.42E-02  6.89E-03 -1.33E-05 -6.42E-03 -1.24E-02 -1.73E-02 -1.87E-02
   -20.0        1.91E-02  1.74E-02  1.16E-02  5.56E-03 -1.07E-05 -5.09E-03 -9.70E-03 -1.34E-02 -1.45E-02
   -15.0        1.49E-02  1.35E-02  8.92E-03  4.23E-03 -8.00E-06 -3.76E-03 -7.04E-03 -9.59E-03 -1.03E-02
   -10.0        1.07E-02  9.67E-03  6.26E-03  2.90E-03 -5.32E-06 -2.43E-03 -4.38E-03 -5.74E-03 -6.06E-03
    -8.0        9.05E-03  8.13E-03  5.20E-03  2.36E-03 -4.25E-06 -1.89E-03 -3.32E-03 -4.20E-03 -4.38E-03
    -6.0        7.37E-03  6.59E-03  4.13E-03  1.83E-03 -3.19E-06 -1.36E-03 -2.25E-03 -2.66E-03 -2.70E-03
    -4.0        5.69E-03  5.05E-03  3.07E-03  1.30E-03 -2.13E-06 -8.30E-04 -1.19E-03 -1.12E-03 -1.02E-03
    -2.0        4.01E-03  3.51E-03  2.00E-03  7.67E-04 -1.06E-06 -2.98E-04 -1.26E-04  4.26E-04  6.55E-04
     0.0        2.33E-03  1.97E-03  9.38E-04  2.34E-04  9.38E-10  2.34E-04  9.38E-04  1.97E-03  2.33E-03
     2.0        6.55E-04  4.26E-04 -1.26E-04 -2.98E-04  1.07E-06  7.67E-04  2.00E-03  3.51E-03  4.01E-03
     4.0       -1.02E-03 -1.12E-03 -1.19E-03 -8.30E-04  2.13E-06  1.30E-03  3.07E-03  5.05E-03  5.69E-03
     6.0       -2.70E-03 -2.66E-03 -2.25E-03 -1.36E-03  3.19E-06  1.83E-03  4.13E-03  6.59E-03  7.37E-03
     8.0       -4.38E-03 -4.20E-03 -3.32E-03 -1.89E-03  4.26E-06  2.36E-03  5.20E-03  8.13E-03  9.05E-03
    10.0       -6.06E-03 -5.74E-03 -4.38E-03 -2.43E-03  5.32E-06  2.90E-03  6.26E-03  9.67E-03  1.07E-02
    15.0       -1.03E-02 -9.59E-03 -7.04E-03 -3.76E-03  7.97E-06  4.23E-03  8.92E-03  1.35E-02  1.49E-02
    20.0       -1.45E-02 -1.34E-02 -9.70E-03 -5.09E-03  1.06E-05  5.56E-03  1.16E-02  1.74E-02  1.91E-02
    25.0       -1.87E-02 -1.73E-02 -1.24E-02 -6.42E-03  1.33E-05  6.89E-03  1.42E-02  2.12E-02  2.33E-02
    30.0       -2.28E-02 -2.12E-02 -1.50E-02 -7.75E-03  1.59E-05  8.22E-03  1.69E-02  2.51E-02  2.75E-02
    45.0       -3.54E-02 -3.27E-02 -2.30E-02 -1.17E-02  2.40E-05  1.22E-02  2.49E-02  3.66E-02  4.01E-02
    60.0       -4.80E-02 -4.43E-02 -3.10E-02 -1.57E-02  3.18E-05  1.62E-02  3.29E-02  4.82E-02  5.27E-02
    75.0       -6.06E-02 -5.58E-02 -3.90E-02 -1.97E-02  3.99E-05  2.02E-02  4.08E-02  5.98E-02  6.53E-02
    90.0       -7.32E-02 -6.74E-02 -4.70E-02 -2.37E-02  4.80E-05  2.42E-02  4.88E-02  7.13E-02  7.79E-02
   105.0       -8.58E-02 -7.89E-02 -5.49E-02 -2.77E-02  5.51E-05  2.82E-02  5.68E-02  8.29E-02  9.05E-02
   120.0       -9.84E-02 -9.05E-02 -6.29E-02 -3.17E-02  6.29E-05  3.22E-02  6.48E-02  9.44E-02  1.03E-01
   135.0       -1.11E-01 -1.02E-01 -7.09E-02 -3.57E-02  7.30E-05  3.62E-02  7.28E-02  1.06E-01  1.16E-01
   150.0       -1.24E-01 -1.14E-01 -7.89E-02 -3.97E-02  8.01E-05  4.01E-02  8.08E-02  1.18E-01  1.28E-01
   165.0       -1.36E-01 -1.25E-01 -8.69E-02 -4.37E-02  8.73E-05  4.41E-02  8.87E-02  1.29E-01  1.41E-01
   180.0       -1.48E-01 -1.36E-01 -9.43E-02 -4.74E-02  9.47E-05  4.79E-02  9.62E-02  1.40E-01  1.53E-01
      </tableData>
     </table>
    </product>
   </function>

   <function name="aero/force/D_car">
    <description>Drag_from_car_and_rigging</description>
    <!--
        Standard DATCOM formulation

            CD = D / (q * Sref)

    -->
    <product>
     <property>aero/qbar-psf</property>
     <property>metrics/Sw-sqft</property>
     <!-- Start CD -->
     <!-- According to [WD:1941:AATM]
          the envelope on a small non-rigid contributes approximately
          35% to the total air resistance.
          I think they mean 'at zero alpha and beta'.
          I assume the envelope's fraction would be much larger for the
          NT07 than a pre-WWII blimp, in particular as the drag from the
          fins have already been accounted for.
     -->  
     <value> 0.100 </value>
     <value> 0.011 </value>
    </product>
   </function>

  </axis>

  <!-- ================================================== -->
  <axis name="SIDE">

   <function name="aero/force/Y_env_beta">
    <description>Side_force_from_envelope_due_to_beta</description>
    <product>
     <value> -1.0 </value>  <!-- Note the sign! -->
     <property> aero/force/L_env_aoa </property>
     <quotient>
      <property> aero/tmp/wy </property>
      <max>
       <value> 0.00001 </value>
       <property> aero/tmp/h_wy_wz </property>
      </max>
     </quotient>
    </product>
   </function>

   <function name="aero/force/Y_vtail_beta">
    <description>Side_force_from_vertical_tail_fin_due_to_beta</description>
    <!--
        Standard DATCOM formulation

            CL = L / (q * Sref)

    -->
    <product>
     <property>aero/qbar-psf</property>
     <property>metrics/Sw-sqft</property>
     <!-- Start CY -->
     <value> 0.10 </value> <!-- Sref scaling. -->
     <value> 0.50 </value> <!-- There is only one vertical tail fin. -->
     <value> -1.0 </value> <!-- Note the sign! -->
     <table>
      <independentVar lookup="row">aero/beta-deg</independentVar>
      <!--  Wing only coefficient computed by DATCOM. -->
      <tableData>
 -180.0    -0.016
 -165.0    -0.096
 -150.0    -0.035
 -135.0     0.094
 -120.0     0.247
 -105.0     0.228
  -90.0     0.000
  -75.0    -0.348
  -60.0    -0.648
  -45.0    -0.750
  -30.0    -0.660
  -25.0    -0.588
  -20.0    -0.481
  -15.0    -0.352
  -10.0    -0.215
   -8.0    -0.164
   -6.0    -0.117
   -4.0    -0.074
   -2.0    -0.035
    0.0     0.000
    2.0     0.035
    4.0     0.074
    6.0     0.117
    8.0     0.164
   10.0     0.215
   15.0     0.352
   20.0     0.481
   25.0     0.588
   30.0     0.660
   45.0     0.507
   60.0     0.344
   75.0     0.186
   90.0     0.000
  105.0    -0.066
  120.0     0.058
  135.0     0.148
  150.0     0.064
  165.0     0.093
  180.0     0.010
      </tableData>
     </table>
    </product>
   </function>  

   <function name="aero/force/Y_dr">
    <description>Side_force_due_to_rudder</description>
    <!--
        Standard DATCOM formulation

            CL = L / (q * Sref)

    -->
    <product>
     <property>aero/qbar-psf</property>
     <property>metrics/Sw-sqft</property>
     <!-- Start CY -->
     <value> 0.10 </value> <!-- Sref scaling. -->
     <value> 0.50 </value> <!-- There is only one vertical tail fin. -->
     <value> -1.0 </value> <!-- Note the sign! -->
     <table>
      <independentVar lookup="row">fcs/rudder-pos-deg</independentVar>
      <!--  Wing only coefficient computed by DATCOM. -->
      <tableData>
      -20.0     -0.058
      -15.0     -0.053
      -10.0     -0.036
       -5.0     -0.018
        0.0      0.000
        5.0      0.018
       10.0      0.036
       15.0      0.053
       20.0      0.058
      </tableData>
     </table>
    </product>
   </function>

  </axis>

  <!-- ================================================== -->
  <axis name="LIFT">

   <function name="aero/force/L_env_alpha">
    <description>Lift_from_envelope_due_to_alpha</description>
    <product>
     <property>aero/force/L_env_aoa</property>
     <quotient>
      <property> aero/tmp/wz </property>
      <max>
       <value> 0.00001 </value>
       <property> aero/tmp/h_wy_wz </property>
      </max>
     </quotient>
    </product>
   </function>

   <function name="aero/force/L_htail_alpha">
    <description>Lift_from_horizontal_tail_due_to_alpha</description>
    <!--
        Standard DATCOM formulation

            CL = L / (q * Sref)

    -->
    <product>
     <property>aero/qbar-psf</property>
     <property>metrics/Sw-sqft</property>
     <!-- Start CL -->
     <value> 0.10 </value> <!-- Sref scaling. -->
     <table>
      <independentVar lookup="row">aero/alpha-deg</independentVar>
      <!--  Wing only coefficient computed by DATCOM. -->
      <tableData>
 -180.0    -0.015
 -165.0    -0.082
 -150.0    -0.001
 -135.0     0.137
 -120.0     0.284
 -105.0     0.249
  -90.0     0.000
  -75.0    -0.363
  -60.0    -0.666
  -45.0    -0.760
  -30.0    -0.660
  -25.0    -0.583
  -20.0    -0.474
  -15.0    -0.343
  -10.0    -0.208
   -8.0    -0.159
   -6.0    -0.113
   -4.0    -0.071
   -2.0    -0.033
    0.0     0.000
    2.0     0.033
    4.0     0.071
    6.0     0.113
    8.0     0.159
   10.0     0.208
   15.0     0.343
   20.0     0.474
   25.0     0.583
   30.0     0.660
   45.0     0.527
   60.0     0.353
   75.0     0.188
   90.0     0.000
  105.0    -0.074
  120.0     0.029
  135.0     0.096
  150.0     0.024
  165.0     0.067
  180.0     0.008
      </tableData>
     </table>
    </product>
   </function>

   <function name="aero/force/L_dr">
    <description>Lift_due_to_elevator</description>
    <!--
        Standard DATCOM formulation

            CL = L / (q * Sref)

    -->
    <product>
     <property>aero/qbar-psf</property>
     <property>metrics/Sw-sqft</property>
     <!-- Start CL -->
     <value> 0.10 </value> <!-- Sref scaling. -->
     <table>
      <independentVar lookup="row">fcs/elevator-pos-deg</independentVar>
      <!--  Wing only coefficient computed by DATCOM. -->
      <tableData>
      -20.0     -0.067
      -15.0     -0.061
      -10.0     -0.042
       -5.0     -0.021
        0.0      0.000
        5.0      0.021
       10.0      0.042
       15.0      0.061
       20.0      0.067
      </tableData>
     </table>
    </product>
   </function>

  </axis>

  <!-- Moments =============================================== -->

  <!-- ================================================== -->  
  <axis name="ROLL">

   <function name="aero/moment/Clp_tail">
    <description>
     Roll Moment coefficient due to roll rate (per radian/sec).
     This is roll moment due to the difference in angle of attack
     induced by the roll rate.
    </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>
     <!-- Clp -->
     <value> 0.10 </value> <!-- Sref scaling. -->
     <value> 1.5  </value> <!-- 3 fins. -->
     <!--  Wing only coefficient computed by DATCOM for alpha = 0. -->
     <!--  This should be extended to use the full table. -->
     <value> -4.574E-01 </value>
    </product>
   </function>

   <function name="aero/moment/Cl_tail_damp">
    <description>
     Damping Roll Moment coefficient due to roll rate (per radian/sec).
     Guessed and added to retain some damping effect at low airspeed.
     Assumed to be due to the considerable area of the fins.
    </description>
    <product>
     <value>1.0</value>
     <property>metrics/Sw-sqft</property>
     <property>metrics/bw-ft</property>
     <property>velocities/p-aero-rad_sec</property>
     <!-- Clp (copied) -->
     <value> 0.10 </value> <!-- Sref scaling. -->
     <value> 1.5  </value> <!-- 3 fins. -->
     <value> -4.574E-01 </value>
    </product>
   </function>

  </axis>

  <!-- ================================================== -->
  <axis name="PITCH">

   <function name="aero/moment/Cmq_envelope">
    <description>
     Pitch Moment coefficient due to pitch rate (per radian/sec).
    </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>
     <!-- Cmq -->
     <!--  Body only coefficient computed by DATCOM for alpha = 0. -->
      <value> -2.331E-02 </value>
    </product>
   </function>

   <function name="aero/moment/Cmq_htail">
    <description>
     Pitch Moment coefficient due to pitch rate (per radian/sec).
    </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>
     <!-- Cmq -->
     <value> 0.10 </value> <!-- Sref scaling. -->
     <!--  Wing only coefficient computed by DATCOM for alpha = 0. -->
     <!--  FIXME: This value is from the 0 dihedral case. -->
     <value> -2.054E-01 </value>
    </product>
   </function>

   <function name="aero/moment/M_env_alpha">
    <description>Pitch_moment_from_envelope_due_to_alpha</description>
    <product>
     <property>aero/moment/M_env_aoa</property>
     <quotient>
      <property> aero/tmp/wz </property>
      <max>
       <value> 0.00001 </value>
       <property> aero/tmp/h_wy_wz </property>
      </max>
     </quotient>
    </product>
   </function>

   <function name="aero/moment/M_htail_alpha">
    <description>Pitch_moment_from_horizontal_tail_due_to_alpha</description>
    <!--
        Standard DATCOM formulation

            Cm = M / (q * Sref * Cbarr)

    -->
    <product>
     <property>aero/qbar-psf</property>
     <property>metrics/Sw-sqft</property>
     <property>metrics/cbarw-ft</property>
     <!-- Start Cm -->
     <value> 0.10 </value> <!-- Sref scaling. -->
     <table>
      <independentVar lookup="row">aero/alpha-deg</independentVar>
      <!--  Wing only coefficient computed by DATCOM. -->
      <tableData>
 -180.0    -0.0038
 -165.0    -0.0214
 -150.0    -0.0003
 -135.0     0.0471
 -120.0     0.1462
 -105.0     0.2689
  -90.0     0.3892
  -75.0     0.3892
  -60.0     0.3803
  -45.0     0.3280
  -30.0     0.2469
  -25.0     0.2123
  -20.0     0.1692
  -15.0     0.1211
  -10.0     0.0730
   -8.0     0.0557
   -6.0     0.0397
   -4.0     0.0249
   -2.0     0.0117
    0.0     0.0000
    2.0    -0.0117
    4.0    -0.0252
    6.0    -0.0404
    8.0    -0.0573
   10.0    -0.0758
   15.0    -0.1283
   20.0    -0.1834
   25.0    -0.2357
   30.0    -0.2806
   45.0    -0.2748
   60.0    -0.2611
   75.0    -0.2726
   90.0    -0.2627
  105.0    -0.1105
  120.0     0.0225
  135.0     0.0545
  150.0     0.0114
  165.0     0.0287
  180.0     0.0033
      </tableData>
     </table>
    </product>
   </function>

   <function name="aero/moment/M_de">
    <description>Pitch_moment_due_to_elevator</description>
    <!--
        Standard DATCOM formulation

            Cm = M / (q * Sref * Cbarr)

    -->
    <product>
     <property>aero/qbar-psf</property>
     <property>metrics/Sw-sqft</property>
     <property>metrics/cbarw-ft</property>
     <!-- Start Cmdr = -->
     <value> 0.10 </value> <!-- Sref scaling. -->
     <table>
      <independentVar lookup="row">fcs/elevator-pos-deg</independentVar>
      <!--  Wing only coefficient computed by DATCOM. -->
      <tableData>
      -20.0      0.0255
      -15.0      0.0252
      -10.0      0.0173
       -5.0      0.0087
        0.0      0.0000
        5.0     -0.0087
       10.0     -0.0173
       15.0     -0.0252
       20.0     -0.0285
      </tableData>
     </table>
    </product>
   </function>

  </axis>

  <!-- ================================================== -->
  <axis name="YAW">

   <function name="aero/moment/Cnr_envelope">
    <description>
     Yaw Moment coefficient due to yaw rate (per radian/sec).
     (Assumed to be equal to Cmq)
    </description>
    <product>
     <property>aero/qbar-psf</property>
     <property>metrics/Sw-sqft</property>
     <property>metrics/cbarw-ft</property>
     <property>aero/ci2vel</property>
     <property>velocities/r-aero-rad_sec</property>
     <!-- Cnr -->
     <!--  Body only coefficient computed by DATCOM for alpha = 0. -->
      <value> -2.331E-02 </value>
    </product>
   </function>

   <function name="aero/moment/Cnr_vtail">
    <description>
     Yaw Moment coefficient due to yaw rate (per radian/sec).
     (Assumed to be equal to Cmq)
    </description>
    <product>
     <property>aero/qbar-psf</property>
     <property>metrics/Sw-sqft</property>
     <property>metrics/cbarw-ft</property>
     <property>aero/ci2vel</property>
     <property>velocities/r-aero-rad_sec</property>
     <!-- Cnr -->
     <value> 0.10 </value> <!-- Sref scaling. -->
     <value> 0.50 </value>
     <!--  Wing only coefficient computed by DATCOM. -->
     <value> -2.054E-01 </value>
    </product>
   </function>

   <function name="aero/moment/N_env_beta">
    <description>Yaw_moment_from_envelope_due_to_beta</description>
    <product>
     <value> -1.0 </value>  <!-- Note the sign! -->
     <property> aero/moment/M_env_aoa </property>
     <quotient>
      <property> aero/tmp/wy </property>
      <max>
       <value> 0.00001 </value>
       <property> aero/tmp/h_wy_wz </property>
      </max>
     </quotient>
    </product>
   </function>

   <function name="aero/moment/N_vtail_beta">
    <description>Yaw_moment_from_vertical_tail_fin_due_to_beta</description>
    <!--
        Standard DATCOM formulation

            Cm = M / (q * Sref * Cbarr)

    -->
    <product>
     <property>aero/qbar-psf</property>
     <property>metrics/Sw-sqft</property>
     <property>metrics/cbarw-ft</property>
     <!-- Start Cn -->
     <value> -1.0 </value> <!-- Note the sign! -->
     <value> 0.10 </value> <!-- Sref scaling. -->
     <value> 0.50 </value> <!-- There is only one vertical tail fin. -->
     <property>aero/vtail-moment-tweak-factor</property>
     <table>
      <independentVar lookup="row">aero/beta-deg</independentVar>
      <!--  Wing only coefficient computed by DATCOM. -->
      <tableData>
 -180.0    -0.0041
 -165.0    -0.0255
 -150.0    -0.0102
 -135.0     0.0334
 -120.0     0.1301
 -105.0     0.2514
  -90.0     0.2659
  -75.0     0.4313
  -60.0     0.3819
  -45.0     0.3281
  -30.0     0.2492
  -25.0     0.2159
  -20.0     0.1733
  -15.0     0.1250
  -10.0     0.0759
   -8.0     0.0580
   -6.0     0.0414
   -4.0     0.0261
   -2.0     0.0123
    0.0     0.0000
    2.0    -0.0123
    4.0    -0.0264
    6.0    -0.0421
    8.0    -0.0595
   10.0    -0.0784
   15.0    -0.1320
   20.0    -0.1871
   25.0    -0.2386
   30.0    -0.2815
   45.0    -0.2648
   60.0    -0.2548
   75.0    -0.2707
   90.0    -0.2659
  105.0    -0.0993
  120.0     0.0455
  135.0     0.0842
  150.0     0.0301
  165.0     0.0399
  180.0     0.0041
      </tableData>
     </table>
    </product>
   </function>

   <function name="aero/moment/N_dr">
    <description>Yaw_moment_due_to_rudder</description>
    <!--
        Standard DATCOM formulation

            Cm = M / (q * Sref * Cbarr)

    -->
    <product>
     <property>aero/qbar-psf</property>
     <property>metrics/Sw-sqft</property>
     <property>metrics/cbarw-ft</property>
     <!-- Start CY -->
     <value> 0.10 </value> <!-- Sref scaling. -->
     <value> 0.50 </value> <!-- There is only one vertical tail fin. -->
     <property>aero/vtail-moment-tweak-factor</property>
     <!-- Start Cndr = -->
     <table>
      <independentVar lookup="row">fcs/rudder-pos-deg</independentVar>
      <!--  Wing only coefficient computed by DATCOM. -->
      <tableData>
      -20.0         0.0222
      -15.0         0.0224
      -10.0         0.0154
       -5.0         0.0077
        0.0         0.0000
        5.0        -0.0077
       10.0        -0.0154
       15.0        -0.0224
       20.0        -0.0254
      </tableData>
     </table>
    </product>
   </function>

   <function name="aero/moment/N_htail_beta">
    <description>
     Yaw moment coefficient for the horizontal fins due to sideslip (per radian).
     DATCOM formulation: Cn = M / (q * Sref * BLref)
    </description>
    <product>
     <property>aero/qbar-psf</property>
     <property>metrics/Sw-sqft</property>
     <property>metrics/bw-ft</property>
     <property>aero/beta-rad</property>
     <!-- Start Cnb -->
     <value> 0.10 </value> <!-- Sref scaling. -->
     <table>
      <independentVar lookup="row">aero/alpha-deg</independentVar>
      <!--  Wing only coefficient computed by DATCOM. -->
      <tableData>
 -180.0    2.849E-05
 -165.0    8.831E-04
 -150.0    1.972E-07
 -135.0    2.438E-03
 -120.0    1.061E-02
 -105.0    8.195E-03
  -90.0    9.185E-02
  -75.0    1.740E-02
  -60.0    5.812E-02
  -45.0    7.551E-02
  -30.0    5.693E-02
  -25.0    4.449E-02
  -20.0    2.937E-02
  -15.0    1.543E-02
  -10.0    5.678E-03
   -8.0    3.306E-03
   -6.0    1.671E-03
   -4.0    6.588E-04
   -2.0    1.439E-04
    0.0    0.000E+00
    2.0    1.440E-04
    4.0    6.589E-04
    6.0    1.672E-03
    8.0    3.306E-03
   10.0    5.679E-03
   15.0    1.543E-02
   20.0    2.938E-02
   25.0    4.450E-02
   30.0    5.694E-02
   45.0    3.636E-02
   60.0    1.636E-02
   75.0    4.681E-03
   90.0    2.602E-15
  105.0    7.225E-04
  120.0    1.074E-04
  135.0    1.213E-03
  150.0    7.723E-05
  165.0    5.876E-04
  180.0    8.055E-06
      </tableData>
     </table>
    </product>
   </function>

  </axis>

 </aerodynamics>