src/FDM/JSBSim/FGAtmosphere.cpp

   1 /*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
   2
   3  Module:       FGAtmosphere.cpp
   4  Author:       Jon Berndt
   5                Implementation of 1959 Standard Atmosphere added by Tony Peden
   6  Date started: 11/24/98
   7  Purpose:      Models the atmosphere
   8  Called by:    FGSimExec
   9
  10  ------------- Copyright (C) 1999  Jon S. Berndt (jsb@hal-pc.org) -------------
  11
  12  This program is free software; you can redistribute it and/or modify it under
  13  the terms of the GNU General Public License as published by the Free Software
  14  Foundation; either version 2 of the License, or (at your option) any later
  15  version.
  16
  17  This program is distributed in the hope that it will be useful, but WITHOUT
  18  ANY WARRANTY; without even the implied warranty of MERCHANTABILITY or FITNESS
  19  FOR A PARTICULAR PURPOSE.  See the GNU General Public License for more
  20  details.
  21
  22  You should have received a copy of the GNU General Public License along with
  23  this program; if not, write to the Free Software Foundation, Inc., 59 Temple
  24  Place - Suite 330, Boston, MA  02111-1307, USA.
  25
  26  Further information about the GNU General Public License can also be found on
  27  the world wide web at http://www.gnu.org.
  28
  29 FUNCTIONAL DESCRIPTION
  30 --------------------------------------------------------------------------------
  31 Models the atmosphere. The equation used below was determined by a third order
  32 curve fit using Excel. The data is from the ICAO atmosphere model.
  33
  34 HISTORY
  35 --------------------------------------------------------------------------------
  36 11/24/98   JSB   Created
  37 07/23/99   TP    Added implementation of 1959 Standard Atmosphere
  38                  Moved calculation of Mach number to FGPropagate
  39                  Later updated to '76 model
  40 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
  41 COMMENTS, REFERENCES,  and NOTES
  42 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
  43 [1]   Anderson, John D. "Introduction to Flight, Third Edition", McGraw-Hill,
  44       1989, ISBN 0-07-001641-0
  45
  46 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
  47 INCLUDES
  48 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
  49
  50 #include "FGAtmosphere.h"
  51 #include "FGState.h"
  52 #include "FGFDMExec.h"
  53 #include "FGAircraft.h"
  54 #include "FGPropagate.h"
  55 #include "FGInertial.h"
  56 #include "FGPropertyManager.h"
  57
  58 namespace JSBSim {
  59
  60 static const char *IdSrc = "$Id$";
  61 static const char *IdHdr = ID_ATMOSPHERE;
  62
  63 /*%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
  64 CLASS IMPLEMENTATION
  65 %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%*/
  66
  67
  68 FGAtmosphere::FGAtmosphere(FGFDMExec* fdmex) : FGModel(fdmex)
  69 {
  70   Name = "FGAtmosphere";
  71   lastIndex = 0;
  72   h = 0.0;
  73   psiw = 0.0;
  74   htab[0]=0;
  75   htab[1]=36089.239;
  76   htab[2]=65616.798;
  77   htab[3]=104986.878;
  78   htab[4]=154199.475;
  79   htab[5]=170603.675;
  80   htab[6]=200131.234;
  81   htab[7]=259186.352; //ft.
  82
  83   MagnitudedAccelDt = MagnitudeAccel = Magnitude = 0.0;
  84 //   turbType = ttNone;
  85   turbType = ttStandard;
  86 //   turbType = ttBerndt;
  87   TurbGain = 0.0;
  88   TurbRate = 1.0;
  89
  90   T_dev_sl = T_dev = delta_T = 0.0;
  91
  92   bind();
  93   Debug(0);
  94 }
  95
  96 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
  97
  98 FGAtmosphere::~FGAtmosphere()
  99 {
 100   unbind();
 101   Debug(1);
 102 }
 103
 104 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 105
 106 bool FGAtmosphere::InitModel(void)
 107 {
 108   FGModel::InitModel();
 109
 110   Calculate(h);
 111   SLtemperature = intTemperature;
 112   SLpressure    = intPressure;
 113   SLdensity     = intDensity;
 114   SLsoundspeed  = sqrt(SHRatio*Reng*intTemperature);
 115   rSLtemperature = 1.0/intTemperature;
 116   rSLpressure    = 1.0/intPressure;
 117   rSLdensity     = 1.0/intDensity;
 118   rSLsoundspeed  = 1.0/SLsoundspeed;
 119   temperature=&intTemperature;
 120   pressure=&intPressure;
 121   density=&intDensity;
 122
 123   useExternal=false;
 124
 125   return true;
 126 }
 127
 128 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 129
 130 bool FGAtmosphere::Run(void)
 131 {
 132   if (!FGModel::Run()) {                 // if false then execute this Run()
 133     //do temp, pressure, and density first
 134     if (!useExternal) {
 135       h = Propagate->Geth();
 136       Calculate(h);
 137     }
 138
 139     if (turbType != ttNone) {
 140       Turbulence();
 141       vWindNED += vTurbulence;
 142     }
 143
 144     if (vWindNED(1) != 0.0) psiw = atan2( vWindNED(2), vWindNED(1) );
 145
 146     if (psiw < 0) psiw += 2*M_PI;
 147
 148     soundspeed = sqrt(SHRatio*Reng*(*temperature));
 149
 150     Debug(2);
 151
 152     return false;
 153   } else {                               // skip Run() execution this time
 154     return true;
 155   }
 156 }
 157
 158 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 159 //
 160 // See reference 1
 161
 162 void FGAtmosphere::Calculate(double altitude)
 163 {
 164   double slope, reftemp, refpress;
 165   int i = 0;
 166
 167   i = lastIndex;
 168   if (altitude < htab[lastIndex]) {
 169     if (altitude <= 0) {
 170       i = 0;
 171       altitude=0;
 172     } else {
 173        i = lastIndex-1;
 174        while (htab[i] > altitude) i--;
 175     }
 176   } else if (altitude > htab[lastIndex+1]) {
 177     if (altitude >= htab[7]) {
 178       i = 7;
 179       altitude = htab[7];
 180     } else {
 181       i = lastIndex+1;
 182       while (htab[i+1] < altitude) i++;
 183     }
 184   }
 185
 186   switch(i) {
 187   case 1:     // 36089 ft.
 188     slope     = 0;
 189     reftemp   = 389.97;
 190     refpress  = 472.452;
 191     //refdens   = 0.000706032;
 192     break;
 193   case 2:     // 65616 ft.
 194     slope     = 0.00054864;
 195     reftemp   = 389.97;
 196     refpress  = 114.636;
 197     //refdens   = 0.000171306;
 198     break;
 199   case 3:     // 104986 ft.
 200     slope     = 0.00153619;
 201     reftemp   = 411.57;
 202     refpress  = 8.36364;
 203     //refdens   = 1.18422e-05;
 204     break;
 205   case 4:     // 154199 ft.
 206     slope     = 0;
 207     reftemp   = 487.17;
 208     refpress  = 0.334882;
 209     //refdens   = 4.00585e-7;
 210     break;
 211   case 5:     // 170603 ft.
 212     slope     = -0.00109728;
 213     reftemp   = 487.17;
 214     refpress  = 0.683084;
 215     //refdens   = 8.17102e-7;
 216     break;
 217   case 6:     // 200131 ft.
 218     slope     = -0.00219456;
 219     reftemp   = 454.17;
 220     refpress  = 0.00684986;
 221     //refdens   = 8.77702e-9;
 222     break;
 223   case 7:     // 259186 ft.
 224     slope     = 0;
 225     reftemp   = 325.17;
 226     refpress  = 0.000122276;
 227     //refdens   = 2.19541e-10;
 228     break;
 229   case 0:
 230   default:     // sea level
 231     slope     = -0.00356616; // R/ft.
 232     reftemp   = 518.67;    // R
 233     refpress  = 2116.22;    // psf
 234     //refdens   = 0.00237767;  // slugs/cubic ft.
 235     break;
 236
 237   }
 238
 239   T_dev = 0.0;
 240   if (delta_T != 0.0) {
 241     T_dev = delta_T;
 242   } else {
 243     if ((h < 36089.239) && (T_dev_sl != 0.0)) {
 244       T_dev = T_dev_sl * ( 1.0 - (h/36089.239));
 245     }
 246   }
 247   density_altitude = h + T_dev * 66.7;
 248
 249   reftemp+=T_dev;
 250   if (slope == 0) {
 251     intTemperature = reftemp;
 252     intPressure = refpress*exp(-Inertial->SLgravity()/(reftemp*Reng)*(altitude-htab[i]));
 253     //intDensity = refdens*exp(-Inertial->SLgravity()/(reftemp*Reng)*(altitude-htab[i]));
 254     intDensity = intPressure/(Reng*intTemperature);
 255   } else {
 256     intTemperature = reftemp+slope*(altitude-htab[i]);
 257     intPressure = refpress*pow(intTemperature/reftemp,-Inertial->SLgravity()/(slope*Reng));
 258     //intDensity = refdens*pow(intTemperature/reftemp,-(Inertial->SLgravity()/(slope*Reng)+1));
 259     intDensity = intPressure/(Reng*intTemperature);
 260   }
 261   lastIndex=i;
 262   //cout << "Atmosphere:  h=" << altitude << " rho= " << intDensity << endl;
 263 }
 264
 265 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 266 // Return the pressure at an arbitrary altitude and then restore the internal state
 267
 268 double FGAtmosphere::GetPressure(double alt) {
 269   Calculate(alt);
 270   double p = *pressure;
 271   // Reset the internal atmospheric state
 272   Run();
 273   return(p);
 274 }
 275
 276 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 277 // square a value, but preserve the original sign
 278
 279 static inline double square_signed (double value)
 280 {
 281     if (value < 0)
 282         return value * value * -1;
 283     else
 284         return value * value;
 285 }
 286
 287 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 288
 289 void FGAtmosphere::Turbulence(void)
 290 {
 291   switch (turbType) {
 292   case ttStandard: {
 293     vDirectiondAccelDt(eX) = 1 - 2.0*(double(rand())/double(RAND_MAX));
 294     vDirectiondAccelDt(eY) = 1 - 2.0*(double(rand())/double(RAND_MAX));
 295     vDirectiondAccelDt(eZ) = 1 - 2.0*(double(rand())/double(RAND_MAX));
 296
 297     MagnitudedAccelDt = 1 - 2.0*(double(rand())/double(RAND_MAX)) - Magnitude;
 298                                 // Scale the magnitude so that it moves
 299                                 // away from the peaks
 300     MagnitudedAccelDt = ((MagnitudedAccelDt - Magnitude) /
 301                          (1 + fabs(Magnitude)));
 302     MagnitudeAccel    += MagnitudedAccelDt*rate*TurbRate*State->Getdt();
 303     Magnitude         += MagnitudeAccel*rate*State->Getdt();
 304
 305     vDirectiondAccelDt.Normalize();
 306
 307                                 // deemphasise non-vertical forces
 308     vDirectiondAccelDt(eX) = square_signed(vDirectiondAccelDt(eX));
 309     vDirectiondAccelDt(eY) = square_signed(vDirectiondAccelDt(eY));
 310
 311     vDirectionAccel += vDirectiondAccelDt*rate*TurbRate*State->Getdt();
 312     vDirectionAccel.Normalize();
 313     vDirection      += vDirectionAccel*rate*State->Getdt();
 314
 315     vDirection.Normalize();
 316
 317                                 // Diminish turbulence within three wingspans
 318                                 // of the ground
 319     vTurbulence = TurbGain * Magnitude * vDirection;
 320     double HOverBMAC = Auxiliary->GetHOverBMAC();
 321     if (HOverBMAC < 3.0)
 322         vTurbulence *= (HOverBMAC / 3.0) * (HOverBMAC / 3.0);
 323
 324     vTurbulenceGrad = TurbGain*MagnitudeAccel * vDirection;
 325
 326     vBodyTurbGrad = Propagate->GetTl2b()*vTurbulenceGrad;
 327
 328     if (Aircraft->GetWingSpan() > 0) {
 329       vTurbPQR(eP) = vBodyTurbGrad(eY)/Aircraft->GetWingSpan();
 330     } else {
 331       vTurbPQR(eP) = vBodyTurbGrad(eY)/30.0;
 332     }
 333 //     if (Aircraft->GetHTailArm() != 0.0)
 334 //       vTurbPQR(eQ) = vBodyTurbGrad(eZ)/Aircraft->GetHTailArm();
 335 //     else
 336 //       vTurbPQR(eQ) = vBodyTurbGrad(eZ)/10.0;
 337
 338     if (Aircraft->GetVTailArm() > 0)
 339       vTurbPQR(eR) = vBodyTurbGrad(eX)/Aircraft->GetVTailArm();
 340     else
 341       vTurbPQR(eR) = vBodyTurbGrad(eX)/10.0;
 342
 343                                 // Clear the horizontal forces
 344                                 // actually felt by the plane, now
 345                                 // that we've used them to calculate
 346                                 // moments.
 347     vTurbulence(eX) = 0.0;
 348     vTurbulence(eY) = 0.0;
 349
 350     break;
 351   }
 352   case ttBerndt: {
 353     vDirectiondAccelDt(eX) = 1 - 2.0*(double(rand())/double(RAND_MAX));
 354     vDirectiondAccelDt(eY) = 1 - 2.0*(double(rand())/double(RAND_MAX));
 355     vDirectiondAccelDt(eZ) = 1 - 2.0*(double(rand())/double(RAND_MAX));
 356
 357
 358     MagnitudedAccelDt = 1 - 2.0*(double(rand())/double(RAND_MAX)) - Magnitude;
 359     MagnitudeAccel    += MagnitudedAccelDt*rate*State->Getdt();
 360     Magnitude         += MagnitudeAccel*rate*State->Getdt();
 361
 362     vDirectiondAccelDt.Normalize();
 363     vDirectionAccel += vDirectiondAccelDt*rate*State->Getdt();
 364     vDirectionAccel.Normalize();
 365     vDirection      += vDirectionAccel*rate*State->Getdt();
 366
 367                                 // Diminish z-vector within two wingspans
 368                                 // of the ground
 369     double HOverBMAC = Auxiliary->GetHOverBMAC();
 370     if (HOverBMAC < 2.0)
 371         vDirection(eZ) *= HOverBMAC / 2.0;
 372
 373     vDirection.Normalize();
 374
 375     vTurbulence = TurbGain*Magnitude * vDirection;
 376     vTurbulenceGrad = TurbGain*MagnitudeAccel * vDirection;
 377
 378     vBodyTurbGrad = Propagate->GetTl2b()*vTurbulenceGrad;
 379     vTurbPQR(eP) = vBodyTurbGrad(eY)/Aircraft->GetWingSpan();
 380     if (Aircraft->GetHTailArm() > 0)
 381       vTurbPQR(eQ) = vBodyTurbGrad(eZ)/Aircraft->GetHTailArm();
 382     else
 383       vTurbPQR(eQ) = vBodyTurbGrad(eZ)/10.0;
 384
 385     if (Aircraft->GetVTailArm() > 0)
 386       vTurbPQR(eR) = vBodyTurbGrad(eX)/Aircraft->GetVTailArm();
 387     else
 388       vTurbPQR(eR) = vBodyTurbGrad(eX)/10.0;
 389
 390     break;
 391   }
 392   default:
 393     break;
 394   }
 395 }
 396
 397 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 398
 399 void FGAtmosphere::UseExternal(void) {
 400   temperature=&exTemperature;
 401   pressure=&exPressure;
 402   density=&exDensity;
 403   useExternal=true;
 404 }
 405
 406 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 407
 408 void FGAtmosphere::UseInternal(void) {
 409   temperature=&intTemperature;
 410   pressure=&intPressure;
 411   density=&intDensity;
 412   useExternal=false;
 413 }
 414
 415 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 416
 417 void FGAtmosphere::bind(void)
 418 {
 419   typedef double (FGAtmosphere::*PMF)(int) const;
 420   PropertyManager->Tie("atmosphere/T-R", this,
 421                        &FGAtmosphere::GetTemperature);
 422   PropertyManager->Tie("atmosphere/rho-slugs_ft3", this,
 423                        &FGAtmosphere::GetDensity);
 424 //  PropertyManager->Tie("atmosphere/P-psf", this,
 425 //                       &FGAtmosphere::GetPressure);
 426   PropertyManager->Tie("atmosphere/a-fps", this,
 427                        &FGAtmosphere::GetSoundSpeed);
 428   PropertyManager->Tie("atmosphere/T-sl-R", this,
 429                        &FGAtmosphere::GetTemperatureSL);
 430   PropertyManager->Tie("atmosphere/rho-sl-slugs_ft3", this,
 431                        &FGAtmosphere::GetDensitySL);
 432   PropertyManager->Tie("atmosphere/P-sl-psf", this,
 433                        &FGAtmosphere::GetPressureSL);
 434   PropertyManager->Tie("atmosphere/a-sl-fps", this,
 435                        &FGAtmosphere::GetSoundSpeedSL);
 436   PropertyManager->Tie("atmosphere/theta-norm", this,
 437                        &FGAtmosphere::GetTemperatureRatio);
 438   PropertyManager->Tie("atmosphere/sigma-norm", this,
 439                        &FGAtmosphere::GetDensityRatio);
 440   PropertyManager->Tie("atmosphere/delta-norm", this,
 441                        &FGAtmosphere::GetPressureRatio);
 442   PropertyManager->Tie("atmosphere/a-norm", this,
 443                        &FGAtmosphere::GetSoundSpeedRatio);
 444   PropertyManager->Tie("atmosphere/psiw-rad", this,
 445                        &FGAtmosphere::GetWindPsi);
 446   PropertyManager->Tie("atmosphere/delta-T", this,
 447                        &FGAtmosphere::GetDeltaT, &FGAtmosphere::SetDeltaT);
 448   PropertyManager->Tie("atmosphere/T-sl-dev-F", this,
 449                        &FGAtmosphere::GetSLTempDev, &FGAtmosphere::SetSLTempDev);
 450   PropertyManager->Tie("atmosphere/density-altitude", this,
 451                        &FGAtmosphere::GetDensityAltitude);
 452   PropertyManager->Tie("atmosphere/p-turb-rad_sec", this,1,
 453                        (PMF)&FGAtmosphere::GetTurbPQR);
 454   PropertyManager->Tie("atmosphere/q-turb-rad_sec", this,2,
 455                        (PMF)&FGAtmosphere::GetTurbPQR);
 456   PropertyManager->Tie("atmosphere/r-turb-rad_sec", this,3,
 457                        (PMF)&FGAtmosphere::GetTurbPQR);
 458 }
 459
 460 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 461
 462 void FGAtmosphere::unbind(void)
 463 {
 464   PropertyManager->Untie("atmosphere/T-R");
 465   PropertyManager->Untie("atmosphere/rho-slugs_ft3");
 466 //  PropertyManager->Untie("atmosphere/P-psf");
 467   PropertyManager->Untie("atmosphere/a-fps");
 468   PropertyManager->Untie("atmosphere/T-sl-R");
 469   PropertyManager->Untie("atmosphere/rho-sl-slugs_ft3");
 470   PropertyManager->Untie("atmosphere/P-sl-psf");
 471   PropertyManager->Untie("atmosphere/a-sl-fps");
 472   PropertyManager->Untie("atmosphere/delta-T");
 473   PropertyManager->Untie("atmosphere/T-sl-dev-F");
 474   PropertyManager->Untie("atmosphere/density-altitude");
 475   PropertyManager->Untie("atmosphere/theta-norm");
 476   PropertyManager->Untie("atmosphere/sigma-norm");
 477   PropertyManager->Untie("atmosphere/delta-norm");
 478   PropertyManager->Untie("atmosphere/a-norm");
 479   PropertyManager->Untie("atmosphere/psiw-rad");
 480   PropertyManager->Untie("atmosphere/p-turb-rad_sec");
 481   PropertyManager->Untie("atmosphere/q-turb-rad_sec");
 482   PropertyManager->Untie("atmosphere/r-turb-rad_sec");
 483 }
 484
 485 //%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
 486 //    The bitmasked value choices are as follows:
 487 //    unset: In this case (the default) JSBSim would only print
 488 //       out the normally expected messages, essentially echoing
 489 //       the config files as they are read. If the environment
 490 //       variable is not set, debug_lvl is set to 1 internally
 491 //    0: This requests JSBSim not to output any messages
 492 //       whatsoever.
 493 //    1: This value explicity requests the normal JSBSim
 494 //       startup messages
 495 //    2: This value asks for a message to be printed out when
 496 //       a class is instantiated
 497 //    4: When this value is set, a message is displayed when a
 498 //       FGModel object executes its Run() method
 499 //    8: When this value is set, various runtime state variables
 500 //       are printed out periodically
 501 //    16: When set various parameters are sanity checked and
 502 //       a message is printed out when they go out of bounds
 503
 504 void FGAtmosphere::Debug(int from)
 505 {
 506   if (debug_lvl <= 0) return;
 507
 508   if (debug_lvl & 1) { // Standard console startup message output
 509     if (from == 0) { // Constructor
 510     }
 511   }
 512   if (debug_lvl & 2 ) { // Instantiation/Destruction notification
 513     if (from == 0) cout << "Instantiated: FGAtmosphere" << endl;
 514     if (from == 1) cout << "Destroyed:    FGAtmosphere" << endl;
 515   }
 516   if (debug_lvl & 4 ) { // Run() method entry print for FGModel-derived objects
 517   }
 518   if (debug_lvl & 8 ) { // Runtime state variables
 519   }
 520   if (debug_lvl & 16) { // Sanity checking
 521   }
 522   if (debug_lvl & 32) { // Turbulence
 523     if (frame == 0 && from == 2) {
 524       cout << "vTurbulence(X), vTurbulence(Y), vTurbulence(Z), "
 525            << "vTurbulenceGrad(X), vTurbulenceGrad(Y), vTurbulenceGrad(Z), "
 526            << "vDirection(X), vDirection(Y), vDirection(Z), "
 527            << "Magnitude, "
 528            << "vTurbPQR(P), vTurbPQR(Q), vTurbPQR(R), " << endl;
 529     } else if (from == 2) {
 530       cout << vTurbulence << ", " << vTurbulenceGrad << ", " << vDirection << ", " << Magnitude << ", " << vTurbPQR << endl;
 531     }
 532   }
 533   if (debug_lvl & 64) {
 534     if (from == 0) { // Constructor
 535       cout << IdSrc << endl;
 536       cout << IdHdr << endl;
 537     }
 538   }
 539 }
 540
 541 } // namespace JSBSim