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C++ CGeometry::ComputeAirfoil_Section方法代码示例

本文整理汇总了C++中CGeometry::ComputeAirfoil_Section方法的典型用法代码示例。如果您正苦于以下问题：C++ CGeometry::ComputeAirfoil_Section方法的具体用法？C++ CGeometry::ComputeAirfoil_Section怎么用？C++ CGeometry::ComputeAirfoil_Section使用的例子？那么, 这里精选的方法代码示例或许可以为您提供帮助。您也可以进一步了解该方法所在类CGeometry的用法示例。


在下文中一共展示了CGeometry::ComputeAirfoil_Section方法的2个代码示例，这些例子默认根据受欢迎程度排序。您可以为喜欢或者感觉有用的代码点赞，您的评价将有助于系统推荐出更棒的C++代码示例。

示例1: main


//.........这里部分代码省略.........
  
  if (rank == MASTER_NODE) cout << "Compute the surface curvature." << endl;
  boundary->ComputeSurf_Curvature(config);
  
  if (rank == MASTER_NODE) cout << "Writing a Tecplot file of the surface curvature." << endl;
  if (size > 1) sprintf (buffer_char, "_%d.plt", rank+1); else sprintf (buffer_char, ".plt");
  strcpy (out_file, "Surface_Curvature"); strcat(out_file, buffer_char); boundary->SetBoundTecPlot(out_file, true, config);
  
	/*--- Create plane structure ---*/
  
  if (rank == MASTER_NODE) cout << "Set plane structure." << endl;
  if (boundary->GetnDim() == 2) {
    MinXCoord = -1E6; MaxXCoord = 1E6;
    Plane_Normal[0][0] = 0.0;   Plane_P0[0][0] = 0.0;
    Plane_Normal[0][1] = 1.0;   Plane_P0[0][1] = 0.0;
    Plane_Normal[0][2] = 0.0;   Plane_P0[0][2] = 0.0;
  }
  else if (boundary->GetnDim() == 3) {
    MinPlane = config->GetSection_Location(0); MaxPlane = config->GetSection_Location(1);
    MinXCoord = -1E6; MaxXCoord = 1E6;
    for (iPlane = 0; iPlane < nPlane; iPlane++) {
      Plane_Normal[iPlane][0] = 0.0;    Plane_P0[iPlane][0] = 0.0;
      Plane_Normal[iPlane][1] = 0.0;    Plane_P0[iPlane][1] = 0.0;
      Plane_Normal[iPlane][2] = 0.0;    Plane_P0[iPlane][2] = 0.0;
      Plane_Normal[iPlane][config->GetAxis_Orientation()] = 1.0;
      Plane_P0[iPlane][config->GetAxis_Orientation()] = MinPlane + iPlane*(MaxPlane - MinPlane)/double(nPlane-1);
    }
  }

  /*--- Create airfoil section structure ---*/
  
  if (rank == MASTER_NODE) cout << "Set airfoil section structure." << endl;
  for (iPlane = 0; iPlane < nPlane; iPlane++) {
    boundary->ComputeAirfoil_Section(Plane_P0[iPlane], Plane_Normal[iPlane], iPlane, MinXCoord, MaxXCoord, NULL,
                                     Xcoord_Airfoil[iPlane], Ycoord_Airfoil[iPlane], Zcoord_Airfoil[iPlane], Variable_Airfoil[iPlane], true, config);
  }
  
  /*--- Compute the internal volume of a 3D body. ---*/
  
  if (rank == MASTER_NODE)  cout << "Computing the internal volume." << endl;
  if (boundary->GetnDim() == 3) Volume = boundary->Compute_Volume(config, true);
  
  if (rank == MASTER_NODE)
    cout << endl <<"-------------------- Objective function evaluation ----------------------" << endl;

  if (rank == MASTER_NODE) {
    
    /*--- Evaluate objective function ---*/
    for (iPlane = 0; iPlane < nPlane; iPlane++) {

      if (Xcoord_Airfoil[iPlane].size() != 0) {
        
        cout << "\nSection " << (iPlane+1) << ". Plane (yCoord): " << Plane_P0[iPlane][1] << "." << endl;
        
        ObjectiveFunc[iPlane]           = boundary->Compute_MaxThickness(Plane_P0[iPlane], Plane_Normal[iPlane], iPlane, config, Xcoord_Airfoil[iPlane], Ycoord_Airfoil[iPlane], Zcoord_Airfoil[iPlane], true);
        ObjectiveFunc[1*nPlane+iPlane]  = boundary->Compute_Thickness(Plane_P0[iPlane], Plane_Normal[iPlane], iPlane, 0.250000, config, Xcoord_Airfoil[iPlane], Ycoord_Airfoil[iPlane], Zcoord_Airfoil[iPlane], true);
        ObjectiveFunc[2*nPlane+iPlane]  = boundary->Compute_Thickness(Plane_P0[iPlane], Plane_Normal[iPlane], iPlane, 0.333333, config, Xcoord_Airfoil[iPlane], Ycoord_Airfoil[iPlane], Zcoord_Airfoil[iPlane], true);
        ObjectiveFunc[3*nPlane+iPlane]  = boundary->Compute_Thickness(Plane_P0[iPlane], Plane_Normal[iPlane], iPlane, 0.500000, config, Xcoord_Airfoil[iPlane], Ycoord_Airfoil[iPlane], Zcoord_Airfoil[iPlane], true);
        ObjectiveFunc[4*nPlane+iPlane]  = boundary->Compute_Thickness(Plane_P0[iPlane], Plane_Normal[iPlane], iPlane, 0.666666, config, Xcoord_Airfoil[iPlane], Ycoord_Airfoil[iPlane], Zcoord_Airfoil[iPlane], true);
        ObjectiveFunc[5*nPlane+iPlane]  = boundary->Compute_Thickness(Plane_P0[iPlane], Plane_Normal[iPlane], iPlane, 0.750000, config, Xcoord_Airfoil[iPlane], Ycoord_Airfoil[iPlane], Zcoord_Airfoil[iPlane], true);
        ObjectiveFunc[6*nPlane+iPlane]  = boundary->Compute_Area(Plane_P0[iPlane], Plane_Normal[iPlane], iPlane, config, Xcoord_Airfoil[iPlane], Ycoord_Airfoil[iPlane], Zcoord_Airfoil[iPlane], true);
        ObjectiveFunc[7*nPlane+iPlane]  = boundary->Compute_AoA(Plane_P0[iPlane], Plane_Normal[iPlane], iPlane, Xcoord_Airfoil[iPlane], Ycoord_Airfoil[iPlane], Zcoord_Airfoil[iPlane], true);
        ObjectiveFunc[8*nPlane+iPlane]  = boundary->Compute_Chord(Plane_P0[iPlane], Plane_Normal[iPlane], iPlane, Xcoord_Airfoil[iPlane], Ycoord_Airfoil[iPlane], Zcoord_Airfoil[iPlane], true);
        
        cout << "Maximum thickness: "   << ObjectiveFunc[iPlane] << "." << endl;
        cout << "1/4 chord thickness: " << ObjectiveFunc[1*nPlane+iPlane] << "." << endl;
开发者ID:DulcetMech，项目名称:SU2，代码行数:67，代码来源:SU2_GEO.cpp

示例2: main

int main(int argc, char *argv[]) {
  
  /*--- Local variables ---*/
	unsigned short iDV, nZone = 1, iFFDBox, iPlane, nPlane = 5, iVar;
	double ObjectiveFunc[100], ObjectiveFunc_New[100], Gradient[100], delta_eps, MinPlane, MaxPlane, Plane_P0[5][3], Plane_Normal[5][3];
  vector<double> Xcoord_Airfoil[5], Ycoord_Airfoil[5], Zcoord_Airfoil[5];
  
	char *cstr;
	ofstream Gradient_file, ObjFunc_file;
	int rank = MASTER_NODE;
  
  /*--- Initialization ---*/
  for (iVar = 0; iVar < 100; iVar++) {
    ObjectiveFunc[iVar] = 0.0;
    ObjectiveFunc_New[iVar] = 0.0;
    Gradient[iVar] = 0.0;
  }
  
#ifndef NO_MPI
	/*--- MPI initialization, and buffer setting ---*/
	MPI::Init(argc,argv);
	rank = MPI::COMM_WORLD.Get_rank();
#endif
	
	/*--- Pointer to different structures that will be used throughout the entire code ---*/
	CFreeFormDefBox** FFDBox = NULL;
	CConfig *config = NULL;
	CGeometry *boundary = NULL;
	CSurfaceMovement *surface_mov = NULL;
	
	/*--- Definition of the Class for the definition of the problem ---*/
	if (argc == 2) config = new CConfig(argv[1], SU2_GDC, ZONE_0, nZone, VERB_HIGH);
	else {
		char grid_file[200];
		strcpy (grid_file, "default.cfg");
		config = new CConfig(grid_file, SU2_GDC, ZONE_0, nZone, VERB_HIGH);
	}
	
#ifndef NO_MPI
	/*--- Change the name of the input-output files for the
	 parallel computation ---*/
	config->SetFileNameDomain(rank+1);
#endif
	
	/*--- Definition of the Class for the boundary of the geometry ---*/
	boundary = new CBoundaryGeometry(config, config->GetMesh_FileName(), config->GetMesh_FileFormat());
  
	if (rank == MASTER_NODE)
		cout << endl <<"----------------------- Preprocessing computations ----------------------" << endl;
	
  /*--- Boundary geometry preprocessing ---*/
	if (rank == MASTER_NODE) cout << "Identify vertices." <<endl;
	boundary->SetVertex();
	
	/*--- Create the control volume structures ---*/
	if (rank == MASTER_NODE) cout << "Set boundary control volume structure." << endl;
	boundary->SetBoundControlVolume(config, ALLOCATE);
	
	/*--- Create plane structure ---*/
  if (rank == MASTER_NODE) cout << "Set plane structure." << endl;
  if (boundary->GetnDim() == 2) {
    nPlane = 1;
    Plane_Normal[0][0] = 0.0;   Plane_P0[0][0] = 0.0;
    Plane_Normal[0][1] = 1.0;   Plane_P0[0][1] = 0.0;
    Plane_Normal[0][2] = 0.0;   Plane_P0[0][2] = 0.0;
  }
  else if (boundary->GetnDim() == 3) {
    nPlane = 5; MinPlane = config->GetSection_Limit(0); MaxPlane = config->GetSection_Limit(1);
    for (iPlane = 0; iPlane < nPlane; iPlane++) {
      Plane_Normal[iPlane][0] = 0.0;    Plane_P0[iPlane][0] = 0.0;
      Plane_Normal[iPlane][1] = 1.0;    Plane_P0[iPlane][1] = MinPlane + iPlane*(MaxPlane - MinPlane)/double(nPlane-1);
      Plane_Normal[iPlane][2] = 0.0;    Plane_P0[iPlane][2] = 0.0;
    }
  }

  /*--- Create airfoil section structure ---*/
  if (rank == MASTER_NODE) cout << "Set airfoil section structure." << endl;
  for (iPlane = 0; iPlane < nPlane; iPlane++) {
    boundary->ComputeAirfoil_Section(Plane_P0[iPlane], Plane_Normal[iPlane], iPlane, config,
                                     Xcoord_Airfoil[iPlane], Ycoord_Airfoil[iPlane], Zcoord_Airfoil[iPlane], true);
  }
  
  if (rank == MASTER_NODE)
    cout << endl <<"-------------------- Objective function evaluation ----------------------" << endl;

  if (rank == MASTER_NODE) {
    
    /*--- Evaluate objective function ---*/
    for (iPlane = 0; iPlane < nPlane; iPlane++) {

      if (Xcoord_Airfoil[iPlane].size() != 0) {
        
        cout << "\nSection " << (iPlane+1) << ". Plane (yCoord): " << Plane_P0[iPlane][1] << "." << endl;
        
        ObjectiveFunc[iPlane]           = boundary->Compute_MaxThickness(Plane_P0[iPlane], Plane_Normal[iPlane], iPlane, Xcoord_Airfoil[iPlane], Ycoord_Airfoil[iPlane], Zcoord_Airfoil[iPlane], true);
        ObjectiveFunc[1*nPlane+iPlane]  = boundary->Compute_Thickness(Plane_P0[iPlane], Plane_Normal[iPlane], iPlane, 0.250000, Xcoord_Airfoil[iPlane], Ycoord_Airfoil[iPlane], Zcoord_Airfoil[iPlane], true);
        ObjectiveFunc[2*nPlane+iPlane]  = boundary->Compute_Thickness(Plane_P0[iPlane], Plane_Normal[iPlane], iPlane, 0.333333, Xcoord_Airfoil[iPlane], Ycoord_Airfoil[iPlane], Zcoord_Airfoil[iPlane], true);
        ObjectiveFunc[3*nPlane+iPlane]  = boundary->Compute_Thickness(Plane_P0[iPlane], Plane_Normal[iPlane], iPlane, 0.500000, Xcoord_Airfoil[iPlane], Ycoord_Airfoil[iPlane], Zcoord_Airfoil[iPlane], true);
        ObjectiveFunc[4*nPlane+iPlane]  = boundary->Compute_Thickness(Plane_P0[iPlane], Plane_Normal[iPlane], iPlane, 0.666666, Xcoord_Airfoil[iPlane], Ycoord_Airfoil[iPlane], Zcoord_Airfoil[iPlane], true);
        ObjectiveFunc[5*nPlane+iPlane]  = boundary->Compute_Thickness(Plane_P0[iPlane], Plane_Normal[iPlane], iPlane, 0.750000, Xcoord_Airfoil[iPlane], Ycoord_Airfoil[iPlane], Zcoord_Airfoil[iPlane], true);
//.........这里部分代码省略.........
开发者ID:dengxbskla，项目名称:SU2，代码行数:101，代码来源:SU2_GDC.cpp


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