src/FDM/UIUCModel/uiuc_coefficients.cpp

   1 /**********************************************************************
   2
   3  FILENAME:     uiuc_coefficients.cpp
   4
   5 ----------------------------------------------------------------------
   6
   7  DESCRIPTION:  computes aggregated aerodynamic coefficients
   8
   9 ----------------------------------------------------------------------
  10
  11  STATUS:       alpha version
  12
  13 ----------------------------------------------------------------------
  14
  15  REFERENCES:
  16
  17 ----------------------------------------------------------------------
  18
  19  HISTORY:      01/29/2000   initial release
  20                02/01/2000   (JS) changed map name from aeroData to
  21                             aeroPart
  22                02/18/2000   (JS) added calls to 1Dinterpolation
  23                             function from CLfa and CDfa switches
  24                02/24/2000   added icing model functions
  25                02/29/2000   (JS) added calls to 2Dinterpolation
  26                             function from CLfade, CDfade, Cmfade,
  27                             CYfada, CYfbetadr, Clfada, Clfbetadr,
  28                             Cnfada, and Cnfbetadr switches
  29                04/15/2000   (JS) broke up into multiple
  30                             uiuc_coef_xxx functions
  31
  32 ----------------------------------------------------------------------
  33
  34  AUTHOR(S):    Bipin Sehgal       <bsehgal@uiuc.edu>
  35                Jeff Scott         <jscott@mail.com>
  36
  37 ----------------------------------------------------------------------
  38
  39  VARIABLES:
  40
  41 ----------------------------------------------------------------------
  42
  43  INPUTS:       -V_rel_wind (or U_body)
  44                -dyn_on_speed
  45                -ice on/off
  46                -phugoid on/off
  47
  48 ----------------------------------------------------------------------
  49
  50  OUTPUTS:      -CL
  51                -CD
  52                -Cm
  53                -CY
  54                -Cl
  55                -Cn
  56
  57 ----------------------------------------------------------------------
  58
  59  CALLED BY:    uiuc_wrapper
  60
  61 ----------------------------------------------------------------------
  62
  63  CALLS TO:     uiuc_coef_lift
  64                uiuc_coef_drag
  65                uiuc_coef_pitch
  66                uiuc_coef_sideforce
  67                uiuc_coef_roll
  68                uiuc_coef_yaw
  69                uiuc_controlInput
  70
  71 ----------------------------------------------------------------------
  72
  73  COPYRIGHT:    (C) 2000 by Michael Selig
  74
  75  This program is free software; you can redistribute it and/or
  76  modify it under the terms of the GNU General Public License
  77  as published by the Free Software Foundation.
  78
  79  This program is distributed in the hope that it will be useful,
  80  but WITHOUT ANY WARRANTY; without even the implied warranty of
  81  MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE.  See the
  82  GNU General Public License for more details.
  83
  84  You should have received a copy of the GNU General Public License
  85  along with this program; if not, write to the Free Software
  86  Foundation, Inc., 59 Temple Place - Suite 330, Boston, MA 02111-1307,
  87  USA or view http://www.gnu.org/copyleft/gpl.html.
  88
  89 **********************************************************************/
  90
  91 #include "uiuc_coefficients.h"
  92
  93
  94 void uiuc_coefficients()
  95 {
  96   // calculate rate derivative nondimensionalization factors
  97   // check if speed is sufficient to compute dynamic pressure terms
  98   if (nondim_rate_V_rel_wind)         // c172_aero uses V_rel_wind
  99     {
 100       if (V_rel_wind > dyn_on_speed)
 101         {
 102           cbar_2U = cbar / (2.0 * V_rel_wind);
 103           b_2U = bw / (2.0 * V_rel_wind);
 104           ch_2U = ch / (2.0 * V_rel_wind);
 105         }
 106       else
 107         {
 108           cbar_2U = 0.0;
 109           b_2U = 0.0;
 110           ch_2U = 0.0;
 111         }
 112     }
 113   else      // use U_body which is probably more correct
 114     {
 115       if (U_body > dyn_on_speed)
 116         {
 117           cbar_2U = cbar / (2.0 * U_body);
 118           b_2U = bw / (2.0 * U_body);
 119           ch_2U = ch / (2.0 * U_body);
 120         }
 121       else
 122         {
 123           cbar_2U = 0.0;
 124           b_2U = 0.0;
 125           ch_2U = 0.0;
 126         }
 127     }
 128
 129   // check to see if icing model engaged
 130   if (ice_model)
 131     {
 132       uiuc_ice_eta();
 133     }
 134
 135   // check to see if phugoid mode engaged
 136   if (elevator_step || elevator_singlet || elevator_doublet || elevator_input)
 137     {
 138       uiuc_controlInput();
 139     }
 140
 141   CD = CX = CL = CZ = Cm = CY = Cl = Cn = 0.0;
 142   CLclean_wing = CLiced_wing = CLclean_tail = CLiced_tail = 0.0;
 143   CZclean_wing = CZiced_wing = CZclean_tail = CZiced_tail = 0.0;
 144   CXclean_wing = CXiced_wing = CXclean_tail = CXiced_tail = 0.0;
 145
 146   uiuc_coef_lift();
 147   uiuc_coef_drag();
 148   uiuc_coef_pitch();
 149   uiuc_coef_sideforce();
 150   uiuc_coef_roll();
 151   uiuc_coef_yaw();
 152
 153   return;
 154 }
 155
 156 // end uiuc_coefficients.cpp