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-   -   Hicks_Henne bump functions :) (https://www.cfd-online.com/Forums/su2/141911-hicks_henne-bump-functions.html)

Bachduong September 19, 2014 03:51
Hicks_Henne bump functions :)
 
Dear guys!
I'm trying to run optimization case steady_rae2822 (SU2 v 3.2.1)
I have some questions about Hicks_Henne bump functions:
1) I have seen in file grid_movement_structure.cpp some code about Hicks_Henne bump functions, lines 3623-3670 as we seen below

Quote:
double Ampl = config->GetDV_Value(iDV);
double xk = config->GetParamDV(iDV, 1);
const double t2 = 3.0;

if (config->GetParamDV(iDV, 0) == NO) { upper = false; double_surface = true; }
if (config->GetParamDV(iDV, 0) == YES) { upper = true; double_surface = true; }

for (iMarker = 0; iMarker < config->GetnMarker_All(); iMarker++) {

for (iVertex = 0; iVertex < boundary->nVertex[iMarker]; iVertex++) {
VarCoord[0] = 0.0; VarCoord[1] = 0.0; VarCoord[2] = 0.0;


if (config->GetMarker_All_DV(iMarker) == YES) {
Point = boundary->vertex[iMarker][iVertex]->GetNode();

Coord_ = boundary->vertex[iMarker][iVertex]->GetCoord();
Normal_ = boundary->vertex[iMarker][iVertex]->GetNormal();

/*--- The Hicks Henne bump functions should be applied to a basic airfoil without AoA,
and unitary chord, a tranformation is required ---*/
ValCos = cos(AoA*PI_NUMBER/180.0);
ValSin = sin(AoA*PI_NUMBER/180.0);

Coord[0] = Coord_[0]*ValCos - Coord_[1]*ValSin;
Coord[0] = max(0.0, Coord[0]); // Coord x should be always positive
Coord[1] = Coord_[1]*ValCos + Coord_[0]*ValSin;

Normal[0] = Normal_[0]*ValCos - Normal_[1]*ValSin;
Normal[1] = Normal_[1]*ValCos + Normal_[0]*ValSin;

/*--- Bump computation ---*/
if (double_surface) {
ek = log10(0.5)/log10(xk);
fk = pow( sin( PI_NUMBER * pow(Coord[0],ek) ) , t2);
/*--- Upper and lower surface ---*/
if (( upper) && (Normal[1] > 0)) { VarCoord[1] = Ampl*fk; }
if ((!upper) && (Normal[1] < 0)) { VarCoord[1] = -Ampl*fk; }
}
else {
xCoord = Coord[0] - BumpLoc;
ek = log10(0.5)/log10(xk/BumpSize);
fk = pow( sin( PI_NUMBER * pow(xCoord/BumpSize,ek)),t2);

/*--- Only one surface ---*/
if ((xCoord <= 0.0) || (xCoord >= BumpSize)) VarCoord[1] = 0.0;
else VarCoord[1] = Ampl*fk;
}
}
Hicks_Henne functions(x) = Ampl*(sin(Pi*x^(log5/logxk)))^3
y(x)=y(x) baseline + Sum (Ampl*(sin(Pi*x^(log5/logxk)))^3)

Perhaps, Ampl = 0.01 (i have seen in config file, that DV_VALUE = 0.01)and xk = 0.05 .. 0.95 (for k = 1..19) respectively, right?
Any suggestion?
Thank you!

fpalacios September 21, 2014 20:30
I think you have understood the code, but... Could you please reformulate the question? It is not clear for me.

Thanks,
Francisco

Bachduong September 22, 2014 01:07
Sorry!
I have seen in config file for shape optimization case for RAE2822 airfoil

Quote:
% ------------------------ GRID DEFORMATION PARAMETERS ------------------------%
%
% Kind of deformation (FFD_SETTING, FFD_CONTROL_POINT_2D, FFD_CAMBER_2D, FFD_THICKNESS_2D,
% HICKS_HENNE, COSINE_BUMP, PARABOLIC,
% NACA_4DIGITS, DISPLACEMENT, ROTATION, FFD_CONTROL_POINT,
% FFD_DIHEDRAL_ANGLE, FFD_TWIST_ANGLE, FFD_ROTATION,
% FFD_CAMBER, FFD_THICKNESS, SURFACE_FILE)
DV_KIND= FFD_SETTING
%
% Marker of the surface to which we are going apply the shape deformation
DV_MARKER= ( AIRFOIL )
%
% Parameters of the shape deformation
% - HICKS_HENNE ( Lower Surface (0)/Upper Surface (1)/Only one Surface (2), x_Loc )
% - NACA_4DIGITS ( 1st digit, 2nd digit, 3rd and 4th digit )
% - PARABOLIC ( Center, Thickness )
% - DISPLACEMENT ( x_Disp, y_Disp, z_Disp )
% - ROTATION ( x_Orig, y_Orig, z_Orig, x_End, y_End, z_End )
% - OBSTACLE ( Center, Bump size )
% - FFD_CONTROL_POINT ( Chunk ID, i_Ind, j_Ind, k_Ind, x_Disp, y_Disp, z_Disp )
% - FFD_DIHEDRAL_ANGLE ( Chunk ID, x_Orig, y_Orig, z_Orig, x_End, y_End, z_End )
% - FFD_TWIST_ANGLE ( Chunk ID, x_Orig, y_Orig, z_Orig, x_End, y_End, z_End )
% - FFD_ROTATION ( Chunk ID, x_Orig, y_Orig, z_Orig, x_End, y_End, z_End )
% - FFD_CAMBER ( Chunk ID, i_Ind, j_Ind )
% - FFD_THICKNESS ( Chunk ID, i_Ind, j_Ind )
% - FFD_VOLUME ( Chunk ID, i_Ind, j_Ind )
DV_PARAM= ( 1, 0.5 )
%
% New value of the shape deformation
DV_VALUE= 0.01
%
% Visualize the deformation (NO, YES)
VISUALIZE_DEFORMATION= NO

% --------------------- OPTIMAL SHAPE DESIGN DEFINITION -----------------------%
% Available Objective functions
% DRAG, LIFT, SIDEFORCE, PRESSURE, FORCE_X, FORCE_Y,
% FORCE_Z, MOMENT_X, MOMENT_Y, MOMENT_Z, EFFICIENCY,
% EQUIVALENT_AREA, THRUST, TORQUE, FREESURFACE

% Optimization objective function with optional scaling factor
% ex= Objective * Scale
OPT_OBJECTIVE= DRAG * 0.001

% Optimization constraint functions with scaling factors, separated by semicolons
% ex= (Objective = Value ) * Scale, use '>','<','='
OPT_CONSTRAINT= ( LIFT > 0.71 ) * 0.001

% List of design variables (Design variables are separated by semicolons)
% - HICKS_HENNE ( 1, Scale | Mark. List | Lower(0)/Upper(1) side, x_Loc )
% - NACA_4DIGITS ( 4, Scale | Mark. List | 1st digit, 2nd digit, 3rd and 4th digit )
% - DISPLACEMENT ( 5, Scale | Mark. List | x_Disp, y_Disp, z_Disp )
% - ROTATION ( 6, Scale | Mark. List | x_Axis, y_Axis, z_Axis, x_Turn, y_Turn, z_Turn )
% - FFD_CONTROL_POINT ( 7, Scale | Mark. List | Chunk, i_Ind, j_Ind, k_Ind, x_Mov, y_Mov, z_Mov )
% - FFD_DIHEDRAL_ANGLE ( 8, Scale | Mark. List | Chunk, x_Orig, y_Orig, z_Orig, x_End, y_End, z_End )
% - FFD_TWIST_ANGLE ( 9, Scale | Mark. List | Chunk, x_Orig, y_Orig, z_Orig, x_End, y_End, z_End )
% - FFD_ROTATION ( 10, Scale | Mark. List | Chunk, x_Orig, y_Orig, z_Orig, x_End, y_End, z_End )
% - FFD_CAMBER ( 11, Scale | Mark. List | Chunk, i_Ind, j_Ind )
% - FFD_THICKNESS ( 12, Scale | Mark. List | Chunk, i_Ind, j_Ind )
% - FFD_VOLUME ( 13, Scale | Mark. List | Chunk, i_Ind, j_Ind )
DEFINITION_DV= ( 1, 1.0 | AIRFOIL | 0, 0.05 ); ( 1, 1.0 | AIRFOIL | 0, 0.10 ); ( 1, 1.0 | AIRFOIL | 0, 0.15 ); ( 1, 1.0 | AIRFOIL | 0, 0.20 ); ( 1, 1.0 | AIRFOIL | 0, 0.25 ); ( 1, 1.0 | AIRFOIL | 0, 0.30 ); ( 1, 1.0 | AIRFOIL | 0, 0.35 ); ( 1, 1.0 | AIRFOIL | 0, 0.40 ); ( 1, 1.0 | AIRFOIL | 0, 0.45 ); ( 1, 1.0 | AIRFOIL | 0, 0.50 ); ( 1, 1.0 | AIRFOIL | 0, 0.55 ); ( 1, 1.0 | AIRFOIL | 0, 0.60 ); ( 1, 1.0 | AIRFOIL | 0, 0.65 ); ( 1, 1.0 | AIRFOIL | 0, 0.70 ); ( 1, 1.0 | AIRFOIL | 0, 0.75 ); ( 1, 1.0 | AIRFOIL | 0, 0.80 ); ( 1, 1.0 | AIRFOIL | 0, 0.85 ); ( 1, 1.0 | AIRFOIL | 0, 0.90 ); ( 1, 1.0 | AIRFOIL | 0, 0.95 ); ( 1, 1.0 | AIRFOIL | 1, 0.05 ); ( 1, 1.0 | AIRFOIL | 1, 0.10 ); ( 1, 1.0 | AIRFOIL | 1, 0.15 ); ( 1, 1.0 | AIRFOIL | 1, 0.20 ); ( 1, 1.0 | AIRFOIL | 1, 0.25 ); ( 1, 1.0 | AIRFOIL | 1, 0.30 ); ( 1, 1.0 | AIRFOIL | 1, 0.35 ); ( 1, 1.0 | AIRFOIL | 1, 0.40 ); ( 1, 1.0 | AIRFOIL | 1, 0.45 ); ( 1, 1.0 | AIRFOIL | 1, 0.50 ); ( 1, 1.0 | AIRFOIL | 1, 0.55 ); ( 1, 1.0 | AIRFOIL | 1, 0.60 ); ( 1, 1.0 | AIRFOIL | 1, 0.65 ); ( 1, 1.0 | AIRFOIL | 1, 0.70 ); ( 1, 1.0 | AIRFOIL | 1, 0.75 ); ( 1, 1.0 | AIRFOIL | 1, 0.80 ); ( 1, 1.0 | AIRFOIL | 1, 0.85 ); ( 1, 1.0 | AIRFOIL | 1, 0.90 ); ( 1, 1.0 | AIRFOIL | 1, 0.95 )
I mean, Ampl = 0.01 and xk = 0.05 ... 0.95 respectively (for k= 1..19) ? or they get another value?
Thank you!


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