[Xianguu]

Hi ,

I have changed from SU2 3.20 to 4.0 recently, but I have some issues with the Euler adjoint simulation . It seems the simulation with 4.0 is hard to convergent on the cases which convergent well with 3.20.

I am wondering if there are any settings need to be changed? Here the config file for 4.0 is attached . Any suggestions will be appreciated !

%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% %
% SU2 configuration file %
% Case description: Adjoint inv. ONERA M6 wing in inviscid flow (regression) %
% Author: Francisco Palacios %
% Institution: Stanford University %
% Date: 06.16.2014 %
% File Version 3.2.9 "eagle" %
% %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%% %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
%
% Physical governing equations (EULER, NAVIER_STOKES,
% TNE2_EULER, TNE2_NAVIER_STOKES,
% WAVE_EQUATION, HEAT_EQUATION, LINEAR_ELASTICITY,
% POISSON_EQUATION)
PHYSICAL_PROBLEM= EULER
%
% Mathematical problem (DIRECT, ADJOINT)
MATH_PROBLEM= ADJOINT
%
% Restart solution (NO, YES)
RESTART_SOL= NO

% -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------%
%
% Mach number (non-dimensional, based on the free-stream values)
MACH_NUMBER= 0.85
%
% Angle of attack (degrees)
AoA= 5.31447
%
% Free-stream pressure (101325.0 N/m^2 by default, only for Euler equations)
FREESTREAM_PRESSURE= 101325.0
%
% Free-stream temperature (288.15 K by default)
FREESTREAM_TEMPERATURE= 288.15

% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
%

%
% Reference origin for moment computation
REF_ORIGIN_MOMENT_X = 0.2015
REF_ORIGIN_MOMENT_Y = 0.00
REF_ORIGIN_MOMENT_Z = 0.00
%
% Reference length for pitching, rolling, and yawing non-dimensional moment
REF_LENGTH_MOMENT= 0.64607
%
% Reference area for force coefficients (0 implies automatic calculation)
REF_AREA= 0
%
% Flow non-dimensionalization (DIMENSIONAL, FREESTEAM_PRESS_EQ_ONE,
% FREESTEAM_VEL_EQ_MACH, FREESTEAM_VEL_EQ_ONE)
%REF_DIMENSIONALIZATION= FREESTEAM_PRESS_EQ_ONE

% ----------------------- BOUNDARY CONDITION DEFINITION -----------------------%
%
% Marker of the Euler boundary (0 implies no marker)
MARKER_EULER= ( aircraft )
%
% Marker of the far field (0 implies no marker)
MARKER_FAR= ( farfield )
%
% Marker of symmetry boundary (0 implies no marker)
MARKER_SYM= ( symmetry )
%
% Marker of the surface which is going to be plotted or designed
MARKER_PLOTTING= ( aircraft )
%
% Marker of the surface where the functional (Cd, Cl, etc.) will be evaluated
MARKER_MONITORING= ( aircraft )

% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
%
% Numerical method for spatial gradients (GREEN_GAUSS, WEIGHTED_LEAST_SQUARES)
NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
%
% Objective function in optimization problem (DRAG, LIFT, SIDEFORCE, MOMENT_X,
% MOMENT_Y, MOMENT_Z, EFFICIENCY,
% EQUIVALENT_AREA, NEARFIELD_PRESSURE,
% FORCE_X, FORCE_Y, FORCE_Z, THRUST,
% TORQUE, FREE_SURFACE, TOTAL_HEATFLUX,
% MAXIMUM_HEATFLUX, INVERSE_DESIGN_PRESSURE,
% INVERSE_DESIGN_HEATFLUX)
OBJECTIVE_FUNCTION= DRAG
%
% Courant-Friedrichs-Lewy condition of the finest grid
CFL_NUMBER= 5.0
%
% Adaptive CFL number (NO, YES)
CFL_ADAPT= YES
%
% Parameters of the adaptive CFL number (factor down, factor up, CFL min value,
% CFL max value )
CFL_ADAPT_PARAM= ( 1.5, 0.5, 1.0, 100.0 )
%
% Runge-Kutta alpha coefficients
RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 )
%
% Number of total iterations
EXT_ITER= 600

% ----------------------- SLOPE LIMITER DEFINITION ----------------------------%
%
% Reference element length for computing the slope and sharp edges limiters.
REF_ELEM_LENGTH= 0.1
%
% Coefficient for the limiter
LIMITER_COEFF= 0.3
%
% Coefficient for the sharp edges limiter
SHARP_EDGES_COEFF= 1.0
%
% Reference coefficient (sensitivity) for detecting sharp edges.
REF_SHARP_EDGES= 3.0
%
% Remove sharp edges from the sensitivity evaluation (NO, YES)
SENS_REMOVE_SHARP= YES

% ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
%
% Linear solver for the implicit formulation (BCGSTAB, FGMRES)
LINEAR_SOLVER= FGMRES
%
% Preconditioner of the Krylov linear solver (JACOBI, LINELET, LU_SGS)
LINEAR_SOLVER_PREC= LU_SGS
%
% Min error of the linear solver for the implicit formulation
LINEAR_SOLVER_ERROR= 1E-6
%
% Max number of iterations of the linear solver for the implicit formulation
LINEAR_SOLVER_ITER= 5

% -------------------------- MULTIGRID PARAMETERS -----------------------------%
%
% Multi-Grid Levels (0 = no multi-grid)
MGLEVEL= 2
%
% Multi-grid cycle (V_CYCLE, W_CYCLE, FULLMG_CYCLE)
MGCYCLE= V_CYCLE
%
% Multi-Grid PreSmoothing Level
MG_PRE_SMOOTH= ( 1, 2, 3, 3 )
%
% Multi-Grid PostSmoothing Level
MG_POST_SMOOTH= ( 0, 0, 0, 0 )
%
% Jacobi implicit smoothing of the correction
MG_CORRECTION_SMOOTH= ( 0, 0, 0, 0 )
%
% Damping factor for the residual restriction
MG_DAMP_RESTRICTION= 0.9
%
% Damping factor for the correction prolongation
MG_DAMP_PROLONGATION= 0.9

% --------------------- FLOW NUMERICAL METHOD DEFINITION ----------------------%
% Convective numerical method: (JST, LAX-FRIEDRICH, ROE-1ST_ORDER,
% ROE-2ND_ORDER)
CONV_NUM_METHOD_FLOW= JST
%
% Slope limiter: (VENKATAKRISHNAN)
SLOPE_LIMITER_FLOW= VENKATAKRISHNAN
%
% 1st, 2nd and 4th order artificial dissipation coefficients
AD_COEFF_FLOW= ( 0.15, 0.5, 0.04 )
%
% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT)
TIME_DISCRE_FLOW= EULER_IMPLICIT

% ----------------- ADJOINT-FLOW NUMERICAL METHOD DEFINITION ------------------%
%
% Convective numerical method: (JST, LAX-FRIEDRICH, ROE-1ST_ORDER,
% ROE-2ND_ORDER)
CONV_NUM_METHOD_ADJFLOW= JST
%
% Slope limiter: (VENKATAKRISHNAN, SHARP_EDGES)
SLOPE_LIMITER_ADJFLOW= VENKATAKRISHNAN
%
% 1st, 2nd, and 4th order artificial dissipation coefficients
AD_COEFF_ADJFLOW= ( 0.15, 0.2, 0.02)
%
% Reduction factor of the CFL coefficient in the adjoint problem
CFL_REDUCTION_ADJFLOW= 0.01
%
% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT)
TIME_DISCRE_ADJFLOW= EULER_IMPLICIT

% ----------------------- GEOMETRY EVALUATION PARAMETERS ----------------------%
%
% Geometrical evaluation mode (FUNCTION, GRADIENT)
GEO_MODE= FUNCTION
%
% Marker(s) of the surface where geometrical based func. will be evaluated
GEO_MARKER= ( aircraft )
%
% Number of airfoil sections
GEO_NUMBER_SECTIONS= 5
%
% Orientation of airfoil sections (X_AXIS, Y_AXIS, Z_AXIS)
GEO_ORIENTATION_SECTIONS= Y_AXIS
%
% Location (coordinate) of the airfoil sections (MinValue, MaxValue)
GEO_LOCATION_SECTIONS= (0.0806, 1.1284)
%
% Plot loads and Cp distributions on each airfoil section
GEO_PLOT_SECTIONS= NO
%
% Number of section cuts to make when calculating internal volume
GEO_VOLUME_SECTIONS= 101

% --------------------------- CONVERGENCE PARAMETERS --------------------------&
%
% Convergence criteria (CAUCHY, RESIDUAL)
CONV_CRITERIA= RESIDUAL
%
% Residual reduction (order of magnitude with respect to the initial value)
RESIDUAL_REDUCTION= 5
%
% Min value of the residual (log10 of the residual)
RESIDUAL_MINVAL= -6.5
%
% Start convergence criteria at iteration number
STARTCONV_ITER= 100
%
% Number of elements to apply the criteria
CAUCHY_ELEMS= 100
%
% Epsilon to control the series convergence
CAUCHY_EPS= 1E-10
%
% Direct function to apply the convergence criteria (LIFT, DRAG, NEARFIELD_PRESS)
CAUCHY_FUNC_FLOW= DRAG
%
% Adjoint function to apply the convergence criteria (SENS_GEOMETRY, SENS_MACH)
CAUCHY_FUNC_ADJFLOW= SENS_GEOMETRY

% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
%
% Mesh input file
MESH_FILENAME= BWB450_FrEACs_1mil.su2
%
% Mesh output file
MESH_OUT_FILENAME= mesh_out.su2
%
% Restart flow input file
SOLUTION_FLOW_FILENAME= solution_flow.dat
%
% Restart adjoint input file
SOLUTION_ADJ_FILENAME= solution_adj.dat
%
% Mesh input file format (SU2)
MESH_FORMAT= SU2
%
% Output file format (PARAVIEW, TECPLOT)
OUTPUT_FORMAT= TECPLOT
%
% Output file convergence history
CONV_FILENAME= history
%
% Output file restart flow
RESTART_FLOW_FILENAME= restart_flow.dat
%
% Output file restart adjoint
RESTART_ADJ_FILENAME= restart_adj.dat
%
% Output file flow (w/o extension) variables
VOLUME_FLOW_FILENAME= flow
%
% Output file adjoint (w/o extension) variables
VOLUME_ADJ_FILENAME= adjoint
%
% Output Objective function gradient (using continuous adjoint)
GRAD_OBJFUNC_FILENAME= of_grad.dat
%
% Output file surface flow coefficient (w/o extension)
SURFACE_FLOW_FILENAME= surface_flow
%
% Output file surface adjoint coefficient (w/o extension)
SURFACE_ADJ_FILENAME= surface_adjoint
%
% Writing solution file frequency
WRT_SOL_FREQ= 500
%
% Writing solution file frequency for physical time steps (dual time)
WRT_SOL_FREQ_DUALTIME= 1
%
% Writing convergence history frequency
WRT_CON_FREQ= 1
%
% Writing convergence history frequency (dual time, only written to screen)
WRT_CON_FREQ_DUALTIME= 10
%
% Output rind layers in the solution files
WRT_HALO= NO

% ----------------------- DESIGN VARIABLE 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, FFD_CONTROL_SURFACE, SURFACE_FILE, AIRFOIL)
DV_KIND= FFD_CONTROL_POINT
%
% Marker of the surface in which we are going apply the shape deformation
DV_MARKER= ( UPPER_SIDE, LOWER_SIDE, TIP )
%
% Parameters of the shape deformation
% - FFD_CONTROL_POINT ( FFD_BoxTag, i_Ind, j_Ind, k_Ind, x_Disp, y_Disp, z_Disp )
% - FFD_DIHEDRAL_ANGLE ( FFD_BoxTag, x_Orig, y_Orig, z_Orig, x_End, y_End, z_End )
% - FFD_TWIST_ANGLE ( FFD_BoxTag, x_Orig, y_Orig, z_Orig, x_End, y_End, z_End )
% - FFD_ROTATION ( FFD_BoxTag, x_Orig, y_Orig, z_Orig, x_End, y_End, z_End )
% - FFD_CAMBER ( FFD_BoxTag, i_Ind, j_Ind )
% - FFD_THICKNESS ( FFD_BoxTag, i_Ind, j_Ind )
% - FFD_VOLUME ( FFD_BoxTag, i_Ind, j_Ind )
DV_PARAM= ( WING, 1, 0, 0, 0.0, 0.0, 1.0 )
%
% New value of the shape deformation
DV_VALUE= 0.0

% ------------------------ GRID DEFORMATION PARAMETERS ------------------------%
% Visualize the deformation (NO, YES)
VISUALIZE_DEFORMATION= NO

% --------------------- OPTIMAL SHAPE DESIGN DEFINITION -----------------------%
% Available flow based objective functions or constraint functions
% DRAG, LIFT, SIDEFORCE, EFFICIENCY,
% FORCE_X, FORCE_Y, FORCE_Z,
% MOMENT_X, MOMENT_Y, MOMENT_Z,
% THRUST, TORQUE, FIGURE_OF_MERIT,
% EQUIVALENT_AREA, NEARFIELD_PRESSURE,
% FREE_SURFACE
%
% Available geometrical based objective functions or constraint functions
% MAX_THICKNESS, 1/4_THICKNESS, 1/2_THICKNESS, 3/4_THICKNESS, AREA, AOA, CHORD,
% MAX_THICKNESS_SEC1, MAX_THICKNESS_SEC2, MAX_THICKNESS_SEC3, MAX_THICKNESS_SEC4, MAX_THICKNESS_SEC5,
% 1/4_THICKNESS_SEC1, 1/4_THICKNESS_SEC2, 1/4_THICKNESS_SEC3, 1/4_THICKNESS_SEC4, 1/4_THICKNESS_SEC5,
% 1/2_THICKNESS_SEC1, 1/2_THICKNESS_SEC2, 1/2_THICKNESS_SEC3, 1/2_THICKNESS_SEC4, 1/2_THICKNESS_SEC5,
% 3/4_THICKNESS_SEC1, 3/4_THICKNESS_SEC2, 3/4_THICKNESS_SEC3, 3/4_THICKNESS_SEC4, 3/4_THICKNESS_SEC5,
% AREA_SEC1, AREA_SEC2, AREA_SEC3, AREA_SEC4, AREA_SEC5,
% AOA_SEC1, AOA_SEC2, AOA_SEC3, AOA_SEC4, AOA_SEC5,
% CHORD_SEC1, CHORD_SEC2, CHORD_SEC3, CHORD_SEC4, CHORD_SEC5
%
% Available design variables
% HICKS_HENNE ( 1, Scale | Mark. List | Lower(0)/Upper(1) side, x_Loc )
% COSINE_BUMP ( 2, Scale | Mark. List | Lower(0)/Upper(1) side, x_Loc, x_Size )
% SPHERICAL ( 3, Scale | Mark. List | ControlPoint_Index, Theta_Disp, R_Disp )
% 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 | FFD_BoxTag, i_Ind, j_Ind, k_Ind, x_Mov, y_Mov, z_Mov )
% FFD_DIHEDRAL_ANGLE ( 8, Scale | Mark. List | FFD_BoxTag, x_Orig, y_Orig, z_Orig, x_End, y_End, z_End )
% FFD_TWIST_ANGLE ( 9, Scale | Mark. List | FFD_BoxTag, x_Orig, y_Orig, z_Orig, x_End, y_End, z_End )
% FFD_ROTATION ( 10, Scale | Mark. List | FFD_BoxTag, x_Orig, y_Orig, z_Orig, x_End, y_End, z_End )
% FFD_CAMBER ( 11, Scale | Mark. List | FFD_BoxTag, i_Ind, j_Ind )
% FFD_THICKNESS ( 12, Scale | Mark. List | FFD_BoxTag, i_Ind, j_Ind )
% FFD_VOLUME ( 13, Scale | Mark. List | FFD_BoxTag, i_Ind, j_Ind )
% FOURIER ( 14, Scale | Mark. List | Lower(0)/Upper(1) side, index, cos(0)/sin(1) )
%
% Optimization objective function with scaling factor
% ex= Objective * Scale
OPT_OBJECTIVE= DRAG * 0.1
%
% Optimization constraint functions with scaling factors, separated by semicolons
% ex= (Objective = Value ) * Scale, use '>','<','='
OPT_CONSTRAINT= (LIFT > 0.2864) * 0.1; (MAX_THICKNESS_SEC1 > 0.0570) * 0.1; (MAX_THICKNESS_SEC2 > 0.0513) * 0.1; (MAX_THICKNESS_SEC3 > 0.0457) * 0.1; (MAX_THICKNESS_SEC4 > 0.0399) * 0.1; (MAX_THICKNESS_SEC5 > 0.0343) * 0.1
%

[economon]

Hi,

Thanks for your comment. Indeed, with v4.0 we did change a number of things (that should be helpful!), so it is likely that your original config files may need to be modified a bit in order to recover the performance.

First, were you able to get the adjoint test cases for v4.0 working with v4.0 of the code? These should be working quite well, and you can use them as a template.

Additionally, one important thing to note is that the non-dimensionalization schemes for both the flow and adjoint problems changed with v4.0. This has an impact on the numerics, so this could be a likely reason that the convergence properties have changed with your old configuration. I would recommend that you explore the various options related to non-dim. and the numerical methods, and you should recover your performance.

Hope this helps,
Tom