src/FDM/UIUCModel/uiuc_betaprobe.cpp

   1 /**********************************************************************
   2
   3  FILENAME:     uiuc_betaprobe.cpp
   4
   5 ----------------------------------------------------------------------
   6
   7  DESCRIPTION:  Computes flow angle, beta, for use in ice detection
   8                scheme
   9
  10 ----------------------------------------------------------------------
  11
  12  STATUS:       alpha version
  13
  14 ----------------------------------------------------------------------
  15
  16  REFERENCES:
  17
  18 ----------------------------------------------------------------------
  19
  20  HISTORY:      05/15/2000   initial release
  21
  22 ----------------------------------------------------------------------
  23
  24  AUTHOR(S):    Jeff Scott         <jscott@mail.com>
  25
  26 ----------------------------------------------------------------------
  27
  28  VARIABLES:
  29
  30 ----------------------------------------------------------------------
  31
  32  INPUTS:       CLclean_wing
  33                CLiced_wing
  34                CLclean_tail
  35                CLiced_tail
  36
  37 ----------------------------------------------------------------------
  38
  39  OUTPUTS:      Dbeta_flow_wing
  40                Dbeta_flow_tail
  41
  42 ----------------------------------------------------------------------
  43
  44  CALLED BY:    uiuc_wrapper
  45
  46 ----------------------------------------------------------------------
  47
  48  CALLS TO:     none
  49
  50 ----------------------------------------------------------------------
  51
  52  COPYRIGHT:    (C) 2000 by Michael Selig
  53
  54  This program is free software; you can redistribute it and/or
  55  modify it under the terms of the GNU General Public License
  56  as published by the Free Software Foundation.
  57
  58  This program is distributed in the hope that it will be useful,
  59  but WITHOUT ANY WARRANTY; without even the implied warranty of
  60  MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE.  See the
  61  GNU General Public License for more details.
  62
  63  You should have received a copy of the GNU General Public License
  64  along with this program; if not, write to the Free Software
  65  Foundation, Inc., 59 Temple Place - Suite 330, Boston, MA 02111-1307,
  66  USA or view http://www.gnu.org/copyleft/gpl.html.
  67
  68 **********************************************************************/
  69
  70 #include "uiuc_betaprobe.h"
  71
  72
  73 void uiuc_betaprobe()
  74 {
  75   if (CX && CZ)
  76     {
  77       CLclean_wing = CXclean_wing * sin(Alpha) - CZclean_wing * cos(Alpha);
  78       CLiced_wing  = CXiced_wing * sin(Alpha) - CZiced_wing * cos(Alpha);
  79       CLclean_tail = CXclean_tail * sin(Alpha) - CZclean_tail * cos(Alpha);
  80       CLiced_tail  = CXiced_tail * sin(Alpha) - CZiced_tail * cos(Alpha);
  81     }
  82
  83   /* calculate lift per unit span*/
  84   Lift_clean_wing = CLclean_wing * Dynamic_pressure * Sw / bw;
  85   Lift_iced_wing = CLiced_wing * Dynamic_pressure * Sw / bw;
  86   Lift_clean_tail = CLclean_tail * Dynamic_pressure * Sh / bh;
  87   Lift_iced_tail = CLiced_tail * Dynamic_pressure * Sh / bh;
  88
  89   Gamma_clean_wing = Lift_clean_wing / (Density * V_rel_wind);
  90   Gamma_iced_wing = Lift_iced_wing / (Density * V_rel_wind);
  91   Gamma_clean_tail = Lift_clean_tail / (Density * V_rel_wind);
  92   Gamma_iced_tail = Lift_iced_tail / (Density * V_rel_wind);
  93
  94   w_clean_wing = Gamma_clean_wing / (2 * LS_PI * x_probe_wing);
  95   w_iced_wing = Gamma_iced_wing / (2 * LS_PI * x_probe_wing);
  96   w_clean_tail = Gamma_clean_tail / (2 * LS_PI * x_probe_tail);
  97   w_iced_tail = Gamma_iced_tail / (2 * LS_PI * x_probe_tail);
  98
  99   V_total_clean_wing = sqrt(w_clean_wing*w_clean_wing +
 100                             V_rel_wind*V_rel_wind -
 101                             2*w_clean_wing*V_rel_wind *
 102                             cos(LS_PI/2 + Alpha));
 103   V_total_iced_wing = sqrt(w_iced_wing*w_iced_wing +
 104                            V_rel_wind*V_rel_wind -
 105                            2*w_iced_wing*V_rel_wind *
 106                            cos(LS_PI/2 + Alpha));
 107   V_total_clean_tail = sqrt(w_clean_tail*w_clean_tail +
 108                             V_rel_wind*V_rel_wind -
 109                             2*w_clean_tail*V_rel_wind *
 110                             cos(LS_PI/2 + Alpha));
 111   V_total_iced_tail = sqrt(w_iced_tail*w_iced_tail +
 112                            V_rel_wind*V_rel_wind -
 113                            2*w_iced_tail*V_rel_wind *
 114                            cos(LS_PI/2 + Alpha));
 115
 116   beta_flow_clean_wing = asin((w_clean_wing / V_total_clean_wing) *
 117                               sin (LS_PI/2 + Alpha));
 118   beta_flow_iced_wing = asin((w_iced_wing / V_total_iced_wing) *
 119                              sin (LS_PI/2 + Alpha));
 120   beta_flow_clean_tail = asin((w_clean_tail / V_total_clean_tail) *
 121                               sin (LS_PI/2 + Alpha));
 122   beta_flow_iced_tail = asin((w_iced_tail / V_total_iced_tail) *
 123                              sin (LS_PI/2 + Alpha));
 124
 125   Dbeta_flow_wing = fabs(beta_flow_clean_wing - beta_flow_iced_wing);
 126   Dbeta_flow_tail = fabs(beta_flow_clean_tail - beta_flow_iced_tail);
 127
 128   pct_beta_flow_wing = beta_flow_iced_wing / beta_flow_clean_wing;
 129   pct_beta_flow_tail = beta_flow_iced_tail / beta_flow_clean_tail;
 130 }
 131
 132 //end uiuc_betaprobe.cpp