the result of cl and cd is not acceptable and i need to modify the file the result of the code which give not coverge
Writing the forces breakdown file (forces_breakdown.dat).
+-----------------------------------------------------------------------+
+----------------------------------------------------------------+
| Inner_Iter| Time(sec)| Time_Iter| CL| CD|
+----------------------------------------------------------------+
| 19510| 6.6939e-02| 0| 0.004081| 0.156430|
| 19520| 6.6938e-02| 0| 0.011526| 0.146708|
| 19530| 6.6936e-02| 0| 0.020145| 0.136572|
| 19540| 6.6936e-02| 0| 0.029911| 0.126056|
| 19550| 6.6936e-02| 0| 0.040790| 0.115191|
| 19560| 6.6937e-02| 0| 0.052748| 0.104011|
| 19570| 6.6936e-02| 0| 0.065747| 0.092552|
| 19580| 6.6937e-02| 0| 0.079750| 0.080846|
| 19590| 6.6937e-02| 0| 0.094710| 0.068930|
| 19600| 6.6937e-02| 0| 0.110578| 0.056842|
| 19610| 6.6936e-02| 0| 0.127301| 0.044617|
| 19620| 6.6936e-02| 0| 0.144820| 0.032294|
| 19630| 6.6936e-02| 0| 0.163072| 0.019912|
| 19640| 6.6936e-02| 0| 0.181996| 0.007507|
| 19650| 6.6938e-02| 0| 0.201529| -0.004880|
| 19660| 6.6938e-02| 0| 0.221605| -0.017212|
| 19670| 6.6939e-02| 0| 0.242152| -0.029450|
| 19680| 6.6939e-02| 0| 0.263099| -0.041557|
| 19690| 6.6939e-02| 0| 0.284374| -0.053493|
| 19700| 6.6938e-02| 0| 0.305902| -0.065223|
| 19710| 6.6939e-02| 0| 0.327610| -0.076709|
| 19720| 6.6939e-02| 0| 0.349426| -0.087915|
| 19730| 6.6940e-02| 0| 0.371270| -0.098806|
| 19740| 6.6939e-02| 0| 0.393065| -0.109348|
| 19750| 6.6938e-02| 0| 0.414740| -0.119507|
| 19760| 6.6937e-02| 0| 0.436215| -0.129251|
| 19770| 6.6936e-02| 0| 0.457421| -0.138551|
| 19780| 6.6935e-02| 0| 0.478285| -0.147374|
| 19790| 6.6936e-02| 0| 0.498731| -0.155695|
| 19800| 6.6935e-02| 0| 0.518687| -0.163486|
| 19810| 6.6934e-02| 0| 0.538085| -0.170724|
| 19820| 6.6933e-02| 0| 0.556863| -0.177383|
| 19830| 6.6933e-02| 0| 0.574961| -0.183444|
| 19840| 6.6933e-02| 0| 0.592319| -0.188885|
| 19850| 6.6933e-02| 0| 0.608878| -0.193688|
| 19860| 6.6932e-02| 0| 0.624578| -0.197837|
| 19870| 6.6934e-02| 0| 0.639369| -0.201318|
| 19880| 6.6934e-02| 0| 0.653203| -0.204118|
| 19890| 6.6933e-02| 0| 0.666041| -0.206226|
| 19900| 6.6932e-02| 0| 0.677843| -0.207635|
| 19910| 6.6932e-02| 0| 0.688573| -0.208341|
| 19920| 6.6932e-02| 0| 0.698202| -0.208341|
| 19930| 6.6932e-02| 0| 0.706704| -0.207633|
| 19940| 6.6932e-02| 0| 0.714061| -0.206219|
| 19950| 6.6932e-02| 0| 0.720254| -0.204105|
| 19960| 6.6932e-02| 0| 0.725271| -0.201298|
| 19970| 6.6932e-02| 0| 0.729098| -0.197808|
| 19980| 6.6931e-02| 0| 0.731734| -0.193645|
| 19990| 6.6930e-02| 0| 0.733176| -0.188822|
| 19999| 6.6930e-02| 0| 0.733451| -0.183929|
----------------------------- Solver Exit -------------------------------
Maximum number of iterations reached (ITER = 20000) before convergence.
+-----------------------------------------------------------------------+
| Convergence Field | Value | Criterion | Converged |
+-----------------------------------------------------------------------+
| rms[P]| -4.74136| < -12| No|
+-----------------------------------------------------------------------+
-------------------------------------------------------------------------
+-----------------------------------------------------------------------+
| File Writing Summary | Filename |
+-----------------------------------------------------------------------+
|SU2 binary restart |restart_flow.dat |
| | (3796.74 MB/s)|
Writing the forces breakdown file (forces_breakdown.dat).
|Paraview surface |surface_flow.vtu |
| | (385.216 MB/s)|
Writing the forces breakdown file (forces_breakdown.dat).
+-----------------------------------------------------------------------+
--------------------------- Finalizing Solver ---------------------------
Deleted CNumerics container.
Deleted CIntegration container.
Deleted CSolver container.
Deleted CIteration container.
Deleted CInterface container.
Deleted CGeometry container.
Deleted CFreeFormDefBox class.
Deleted CSurfaceMovement class.
Deleted CVolumetricMovement class.
Deleted CConfig container.
Deleted nInst container.
Deleted COutput class.
-------------------------------------------------------------------------
-------------------------- Performance Summary --------------------------
Simulation totals:
Wall-clock time (hrs): 0.371884 | Core-hrs: 0.371884
Cores: 1 | DOFs/point: 6
Points/core: 38442 | Ghost points/core: 0
Ghost/Owned Point Ratio: 0 |
Preprocessing phase:
Preproc. Time (s): 0.156802 | Preproc. Time (%): 0.0117123
Compute phase:
Compute Time (s): 1338.6 | Compute Time (%): 99.9867
Iteration count: 20000 | Avg. s/iter: 0.0669302
Core-s/iter/Mpoints: 1.74107 | Mpoints/s: 0.574359
Output phase:
Output Time (s): 0.021299 | Output Time (%): 0.00159092
Output count: 1 | Avg. s/output: 0.021299
Restart Aggr. BW (MB/s): 142429 | MB/s/core: 142429
-------------------------------------------------------------------------
------------------------- Exit Success (SU2_CFD) ------------------------
the code i use it as foolowing
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% %
% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
%
SOLVER= INC_RANS
%
KIND_TURB_MODEL= SST
KIND_TRANS_MODEL= LM
%FREESTREAM_TURBULENCEINTENSITY= 0.001
%FREESTREAM_TURB2LAMVISCRATIO = 2.0
%HROUGHNESS = 3.3E-6
%
MATH_PROBLEM= DIRECT
%
RESTART_SOL= NO
%
OBJECTIVE_FUNCTION=DRAG
% -------------------- INCOMPRESSIBLE FREE-STREAM DEFINITION ------------------%
%
INC_DENSITY_INIT= 1.225
INC_TEMPERATURE_INIT= 288.15
% -------------- COMPRESSIBLE AND INCOMPRESSIBLE FLUID CONSTANTS --------------%
%
%GAMMA_VALUE= 1.4
%GAS_CONSTANT= 287.87
%
% AoA 0.0 deg
INC_VELOCITY_INIT= ( 14.60799973614140 , 0.00277648930504, 0.0 )
%
INC_NONDIM= INITIAL_VALUES
% --------------------------- VISCOSITY MODEL ---------------------------------%
%
VISCOSITY_MODEL= CONSTANT_VISCOSITY
%
MU_CONSTANT= 1.789e-05
% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
%
REF_ORIGIN_MOMENT_X= 0.25
REF_ORIGIN_MOMENT_Y = 0.00
REF_ORIGIN_MOMENT_Z = 0.00
%
REF_LENGTH= 1.0
%
REF_AREA= 1.0
% -------------------------- CL DRIVER DEFINITION -----------------------------%
%
% Activate fixed lift mode (specify a CL instead of AoA, NO/YES)
FIXED_CL_MODE= NO
%
% Target coefficient of lift for fixed lift mode (0.80 by default)
TARGET_CL= 0.724
%
% Estimation of dCL/dAlpha (0.2 per degree by default)
DCL_DALPHA= 0.2
%
% Maximum number of iterations between AoA updates
UPDATE_AOA_ITER_LIMIT= 100
%
% Number of iterations to evaluate dCL/dAlpha at the end of the simulation
ITER_DCL_DALPHA= 500
%
% Evaluate dObjFunc/dCL during runtime (YES) or use the value stored in the
% direct solution file (NO).
EVAL_DOF_DCX= NO
% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
%
MARKER_HEATFLUX= ( AIRFOIL, 0.0 )
%
MARKER_FAR= ( FARFIELD )
%
MARKER_PLOTTING= ( AIRFOIL )
%
MARKER_MONITORING= ( AIRFOIL )
% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
%
NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES
%
CFL_NUMBER= 1.0
%
%MAX_DELTA_TIME= 1E10
%
CFL_ADAPT= NO
%
CFL_ADAPT_PARAM= ( 0.1, 2.0, 40.0, 1e10, 0.001 )
%CFL_ADAPT_PARAM= ( 0.5, 1.0, 0.5, 1000, 0.001 ) % Less aggressive adaptation
%
ITER= 20000
% ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
%
LINEAR_SOLVER= FGMRES
%
LINEAR_SOLVER_PREC= LU_SGS
%
LINEAR_SOLVER_ERROR= 1E-6
%
LINEAR_SOLVER_ITER= 5
% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
%
%
CONV_NUM_METHOD_FLOW= FDS
%
MUSCL_FLOW= YES
%
SLOPE_LIMITER_FLOW= VENKATAKRISHNAN
%
JST_SENSOR_COEFF= ( 0.5, 0.02 )
%
TIME_DISCRE_FLOW= EULER_IMPLICIT
% ----------------------- SLOPE LIMITER DEFINITION ----------------------------%
%
VENKAT_LIMITER_COEFF= 0.05
%
LIMITER_ITER= 99999
% -------------------- TURBULENT NUMERICAL METHOD DEFINITION ------------------%
%
CONV_NUM_METHOD_TURB= SCALAR_UPWIND
%
MUSCL_TURB= NO
%
SLOPE_LIMITER_TURB= NONE
%
TIME_DISCRE_TURB= EULER_IMPLICIT
%
CFL_REDUCTION_TURB= 1.0
% --------------------------- CONVERGENCE PARAMETERS --------------------------%
%
%
%CONV_CRITERIA= CAUCHY
%
CONV_RESIDUAL_MINVAL= -12
%
CONV_FIELD= ( RMS_PRESSURE )
%
% Start convergence criteria at iteration number
CONV_STARTITER= 500
% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
%
%HISTORY_WRT_FREQ_INNER=0
MESH_FILENAME= mesh_211_ffd.su2
%
MESH_FORMAT= SU2
%
SOLUTION_FILENAME= restart_flow.dat
%
OUTPUT_FILES= (RESTART, SURFACE_PARAVIEW)
WRT_FORCES_BREAKDOWN= YES
VOLUME_OUTPUT= (COORDINATES, SOLUTION, PRIMITIVE, RESIDUAL)
HISTORY_OUTPUT= (ITER, LINSOL, RMS_RES, MAX_RES, AERO_COEFF, CFL_NUMBER)
%
CONV_FILENAME= history
%
RESTART_FILENAME= restart_flow.dat
%
SOLUTION_ADJ_FILENAME = solution_adj.dat
TABULAR_FORMAT= CSV
VOLUME_FILENAME= flow
%
SURFACE_FILENAME= surface_flow
%
OUTPUT_WRT_FREQ= 500
%
SCREEN_WRT_FREQ_INNER= 10
%
%SCREEN_OUTPUT=(INNER_ITER, WALL_TIME, RMS_PRESSURE, RMS_NU_TILDE, RMS_RE_THETA_T, LIFT, DRAG, LINSOL_ITER_TRANS, LINSOL_RESIDUAL_TRANS, TAVG_DRAG)
SCREEN_OUTPUT=(INNER_ITER,WALL_TIME, TIME_ITER, RMS_ADJ_DENSITY, RMS_DENSITY, , REL_RMS_DENSITY,REL_RMS_ADJ_DENSITY, LIFT,DRAG)
%
WRT_PERFORMANCE = YES
% ----------------------- DESIGN VARIABLE PARAMETERS --------------------------%
%
DV_KIND= FFD_CONTROL_POINT_2D
DV_MARKER= ( AIRFOIL )
DV_PARAM= ( AIRFOIL_BOX, 0.0, 0.0, 1.0, 0.0)
DV_VALUE= 0.01
%DV_FILENAME= mesh_motion.dat
%
% ------------------------ GRID DEFORMATION PARAMETERS ------------------------%
%
DEFORM_LINEAR_SOLVER_ITER= 1000
DEFORM_NONLINEAR_ITER= 1
DEFORM_CONSOLE_OUTPUT= YES
DEFORM_LINEAR_SOLVER_ERROR = 1E-6
DEFORM_STIFFNESS_TYPE= INVERSE_VOLUME
OPT_ITERATIONS= 100
OPT_OBJECTIVE= DRAG * 1.0
OPT_GRADIENT_FACTOR= 0.1
OPT_RELAX_FACTOR= 1
OPT_BOUND_UPPER= 0.01
OPT_BOUND_LOWER= -0.01
%OPT_CONSTRAINT= ( AIRFOIL_THICKNESS > 0.21 ) * 1.0
OPT_CONSTRAINT= ( LIFT > 0.724 ) * 1.0; ( AIRFOIL_THICKNESS > 0.21 ) * 1.0
DEFINITION_DV= ( 19, 1.0 | AIRFOIL | AIRFOIL_BOX, 0, 0, 0.0, 1.0 ); ( 19, 1.0 | AIRFOIL | AIRFOIL_BOX, 1, 0, 0.0, 1.0 ); ( 19, 1.0 | AIRFOIL | AIRFOIL_BOX, 2, 0, 0.0, 1.0 ); ( 19, 1.0 | AIRFOIL | AIRFOIL_BOX, 3, 0, 0.0, 1.0 ); ( 19, 1.0 | AIRFOIL | AIRFOIL_BOX, 4, 0, 0.0, 1.0 ); ( 19, 1.0 | AIRFOIL | AIRFOIL_BOX, 5, 0, 0.0, 1.0 ); ( 19, 1.0 | AIRFOIL | AIRFOIL_BOX, 6, 0, 0.0, 1.0 ); ( 19, 1.0 | AIRFOIL | AIRFOIL_BOX, 7, 0, 0.0, 1.0 ); ( 19, 1.0 | AIRFOIL | AIRFOIL_BOX, 8, 0, 0.0, 1.0 ); ( 19, 1.0 | AIRFOIL | AIRFOIL_BOX, 9, 0, 0.0, 1.0 ); ( 19, 1.0 | AIRFOIL | AIRFOIL_BOX, 10, 0, 0.0, 1.0 ); ( 19, 1.0 | AIRFOIL | AIRFOIL_BOX, 0, 1, 0.0, 1.0 ); ( 19, 1.0 | AIRFOIL | AIRFOIL_BOX, 1, 1, 0.0, 1.0 ); ( 19, 1.0 | AIRFOIL | AIRFOIL_BOX, 2, 1, 0.0, 1.0 ); ( 19, 1.0 | AIRFOIL | AIRFOIL_BOX, 3, 1, 0.0, 1.0 ); ( 19, 1.0 | AIRFOIL | AIRFOIL_BOX, 4, 1, 0.0, 1.0 ); ( 19, 1.0 | AIRFOIL | AIRFOIL_BOX, 5, 1, 0.0, 1.0 ); ( 19, 1.0 | AIRFOIL | AIRFOIL_BOX, 6, 1, 0.0, 1.0 ); ( 19, 1.0 | AIRFOIL | AIRFOIL_BOX, 7, 1, 0.0, 1.0 ); ( 19, 1.0 | AIRFOIL | AIRFOIL_BOX, 8, 1, 0.0, 1.0 ); ( 19, 1.0 | AIRFOIL | AIRFOIL_BOX, 9, 1, 0.0, 1.0 ); ( 19, 1.0 | AIRFOIL | AIRFOIL_BOX, 10, 1, 0.0, 1.0 )
最新发布