关于错误“BMXAA4195E - The Default Value field requires a value”

本文探讨了在迁移TableObjectPackage过程中遇到的BMXAA4195E错误及其解决方案。该错误通常发生在字段标记为Required但未设置默认值的情况下。文章提供了详细的步骤来修正此问题。

我在两种情况下碰到过这个信息。

1. 移植Table Object Package 到另一个Server,由于原Server上某个新建的表有字段设为"Required",而目标server上也手工建立了这个表,但是相同的字段没有设为"Required",这样,Table Object Package在目标server上部署失败,并报出“BMXAA4195E - The Default Value field requires a value”

2. 为了解决上面那个问题,我把原server上的那些字段"Required"全部取消,然后再重建Table Object Package, Migrate到目标server,部署成功,只是想将原server上字段改回"Required"的时候,报出“BMXAA4195E - The Default Value field requires a value”。

经过试验,发现这个问题的原因是,没有给字段设置默认值。因此可以用以下方式将字段改回"Required".

  a. 将字段加上"Required", 并加上默认值。

  b. Apply DB change

  c. 取消默认值

   d. Apply DB change.


这里产生另外一个疑问,对于Migrate来说,如果目标Server上已存在一个相同名称,完全不同字段的表,结果会如何?  下回再试验。

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
08-27
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