參數名稱

數值

% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%

%

% Physical governing equations (EULER, NAVIER_STOKES,

%                                WAVE_EQUATION, HEAT_EQUATION, FEM_ELASTICITY,

%                                POISSON_EQUATION)

PHYSICAL_PROBLEM= NAVIER_STOKES          %不考慮粘性選EULER，考慮粘性選NAVIER_STOKES

%

% Specify turbulence model (NONE, SA, SA_NEG, SST)

KIND_TURB_MODEL= SA    %一般選一方程模型SA或兩方程模型SST

%

% Mathematical problem (DIRECT, CONTINUOUS_ADJOINT)

MATH_PROBLEM= DIRECT    %不做優化選DIRECT

%

% Restart solution (NO, YES)

RESTART_SOL= NO  %重啟動計算選YES，同時需要在后面設置重啟動文件% Restart flow  input file   SOLUTION_FLOW_FILENAME

% Regime type (COMPRESSIBLE, INCOMPRESSIBLE)

REGIME_TYPE= COMPRESSIBLE     %馬赫數為0.75，對應高速可壓縮流場

%

% System of measurements (SI, US)

% International system of units (SI): ( meters, kilograms, Kelvins,

%                                        Newtons = kg m/s^2, Pascals = N/m^2,

%                                        Density = kg/m^3, Speed = m/s,

%                                        Equiv. Area = m^2 )

% United States customary units (US): ( inches, slug, Rankines, lbf =  slug ft/s^2,

%                                        psf = lbf/ft^2, Density = slug/ft^3,

%                                        Speed = ft/s, Equiv. Area = ft^2 )

SYSTEM_MEASUREMENTS= SI    %采用標準單位

% -------------------- COMPRESSIBLE FREE-STREAM DEFINITION  --------------------%

%

% Mach number (non-dimensional, based on the free-stream values)

MACH_NUMBER= 0.75   %自由來流馬赫數

%

% Angle of attack (degrees, only for compressible flows)

AOA= 0.49   %來流攻角,注意SU2定義X+為流向（機頭指向機尾方向），Y+為側向（翼展方向），Z+為法向（垂直于翼面的方向）。

 %

% Side-slip angle (degrees, only for compressible flows)

SIDESLIP_ANGLE= 0.0  %側滑角，在本次算例中，SIDESLIP_ANGLE值實際為攻角

%

% Init option to choose between Reynolds (default) or thermodynamics  quantities

% for initializing the solution (REYNOLDS, TD_CONDITIONS)

INIT_OPTION= REYNOLDS   %  REYNOLDS，根據雷諾數計算自由來流參數；TD_CONDITIONS，根據溫度和密度參數計算自由來流參數

%

% Free-stream option to choose between density and temperature  (default) for

% initializing the solution (TEMPERATURE_FS, DENSITY_FS)

FREESTREAM_OPTION= TEMPERATURE_FS   %給定自由來流靜溫還是靜密度

%

% Free-stream temperature (288.15 K by default)

FREESTREAM_TEMPERATURE= 300  %自由來流靜溫值

%

% Reynolds number (non-dimensional, based on the free-stream values)

REYNOLDS_NUMBER= 3.0E6  %參考長度為REYNOLDS_LENGTH（單位米）的自由來流雷諾數（無量綱）

%

% Reynolds length (1 m by default)

REYNOLDS_LENGTH= 0.1412   %平均氣動弦長，單位：米

% ---- IDEAL GAS, POLYTROPIC, VAN DER WAALS AND PENG ROBINSON CONSTANTS  -------%

%

% Different gas model (STANDARD_AIR, IDEAL_GAS, VW_GAS, PR_GAS)

FLUID_MODEL= STANDARD_AIR

%

% Ratio of specific heats (1.4 default and the value is hardcoded

%                          for  the model STANDARD_AIR)

GAMMA_VALUE= 1.4

%

% Specific gas constant (287.058 J/kg*K default and this value is  hardcoded

%                        for the  model STANDARD_AIR)

GAS_CONSTANT= 287.058

% --------------------------- VISCOSITY MODEL  ---------------------------------%

%

% Viscosity model (SUTHERLAND, CONSTANT_VISCOSITY).

VISCOSITY_MODEL= SUTHERLAND

%

% Sutherland Viscosity Ref (1.716E-5 default value for AIR SI)

MU_REF= 1.716E-5

%

% Sutherland Temperature Ref (273.15 K default value for AIR SI)

MU_T_REF= 273.15

%

% Sutherland constant (110.4 default value for AIR SI)

SUTHERLAND_CONSTANT= 110.4

% --------------------------- THERMAL CONDUCTIVITY MODEL  ----------------------%

%

% Conductivity model (CONSTANT_CONDUCTIVITY, CONSTANT_PRANDTL).

CONDUCTIVITY_MODEL= CONSTANT_PRANDTL

%

% Laminar Prandtl number (0.72 (air), only for CONSTANT_PRANDTL)

PRANDTL_LAM= 0.72

%

% Turbulent Prandtl number (0.9 (air), only for CONSTANT_PRANDTL)

PRANDTL_TURB= 0.90

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

%

% Reference origin for moment computation 力矩參考點

REF_ORIGIN_MOMENT_X = 0.00

REF_ORIGIN_MOMENT_Y = 0.00

REF_ORIGIN_MOMENT_Z = 0.00

%

% Reference length for pitching, rolling, and yawing non-dimensional  moment用于力矩系數計算的參考長度

REF_LENGTH= 1.0

%

% Reference area for force coefficients (0 implies automatic  calculation) 用于升阻力系數計算的參考面積

REF_AREA= 0.0727   %采用半模計算，REF_AREA為全模飛機的一半參考面積

%

% Compressible flow non-dimensionalization (DIMENSIONAL,  FREESTREAM_PRESS_EQ_ONE,

%                              FREESTREAM_VEL_EQ_MACH,  FREESTREAM_VEL_EQ_ONE)

%流場計算結果的無量綱方式

REF_DIMENSIONALIZATION= FREESTREAM_VEL_EQ_ONE

% -------------------- BOUNDARY CONDITION DEFINITION  --------------------------%

%

% Navier-Stokes wall boundary marker(s) (NONE = no marker)

%物面邊界

MARKER_HEATFLUX= (body, 0.0, wing, 0.0 )

%遠場邊界

% Far-field boundary marker(s) (NONE = no marker)

MARKER_FAR= ( inlet, outlet, up, down, right )

%對稱邊界

% Symmetry boundary marker(s) (NONE = no marker)

MARKER_SYM= ( left )

%

% Marker(s) of the surface to be plotted or designed

%標記用于后處理或設計的邊界

MARKER_PLOTTING= (body,  wing )

%

% Marker(s) of the surface where the functional (Cd, Cl, etc.) will be  evaluated

%標記用于升阻力系數監測的邊界

MARKER_MONITORING= (body,  wing  )

% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD  ---------------%

%

% Numerical method for spatial gradients (GREEN_GAUSS,  WEIGHTED_LEAST_SQUARES)

%梯度計算方法

NUM_METHOD_GRAD= GREEN_GAUSS

%

% Courant-Friedrichs-Lewy condition of the finest grid

%最密層網格上的CFL數

CFL_NUMBER= 1.0

%

% Adaptive CFL number (NO, YES)

%是否采用自適應CFL

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 )

%

% Number of total iterations

%最大迭代步數

EXT_ITER= 50000

% ----------------------- SLOPE LIMITER DEFINITION  ----------------------------%

%

% Coefficient for the limiter

VENKAT_LIMITER_COEFF= 0.05

%

% Coefficient for the sharp edges limiter

ADJ_SHARP_LIMITER_COEFF= 3.0

%

% Reference coefficient (sensitivity) for detecting sharp edges.

REF_SHARP_EDGES= 3.0

%

% Remove sharp edges from the sensitivity evaluation (NO, YES)

SENS_REMOVE_SHARP= NO

% ------------------------ LINEAR SOLVER DEFINITION  ---------------------------%

%

% Linear solver for implicit formulations (BCGSTAB, FGMRES)

LINEAR_SOLVER= FGMRES

%

% Preconditioner of the Krylov linear solver (JACOBI, LINELET, LU_SGS)

LINEAR_SOLVER_PREC= ILU

%

% Linaer solver ILU preconditioner fill-in level (0 by default)

LINEAR_SOLVER_ILU_FILL_IN= 0

%

% Minimum error of the linear solver for implicit formulations

LINEAR_SOLVER_ERROR= 1E-10

%

% 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)

%采用幾重網格

MGLEVEL= 0

%

% Multi-grid cycle (V_CYCLE, W_CYCLE, FULLMG_CYCLE)

MGCYCLE= V_CYCLE

%

% Multi-grid pre-smoothing level

MG_PRE_SMOOTH= ( 1, 2, 3, 3 )

%

% Multi-grid post-smoothing 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= 0.75

%

% Damping factor for the correction prolongation

MG_DAMP_PROLONGATION= 0.75

% -------------------- FLOW NUMERICAL METHOD DEFINITION  -----------------------%

%

% Convective numerical method (JST, LAX-FRIEDRICH, CUSP, ROE, AUSM,  HLLC,

%                               TURKEL_PREC, MSW)

%對流項格式

CONV_NUM_METHOD_FLOW= ROE

%

% Spatial numerical order integration (1ST_ORDER, 2ND_ORDER,  2ND_ORDER_LIMITER)

%重構格式

MUSCL_FLOW= YES

%

% Slope limiter (NONE, VENKATAKRISHNAN, VENKATAKRISHNAN_WANG,

%                 BARTH_JESPERSEN, VAN_ALBADA_EDGE)

%限制器

SLOPE_LIMITER_FLOW= VENKATAKRISHNAN

% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT,  EULER_EXPLICIT)

%時間推進格式

TIME_DISCRE_FLOW= EULER_IMPLICIT

%

% Relaxation coefficient

RELAXATION_FACTOR_FLOW= 0.9

% -------------------- TURBULENT NUMERICAL METHOD DEFINITION  ------------------%

%

% Convective numerical method (SCALAR_UPWIND)

%湍流對流項格式

CONV_NUM_METHOD_TURB= SCALAR_UPWIND

%

% Monotonic Upwind Scheme for Conservation Laws (TVD) in the  turbulence equations.

%           Required for 2nd  order upwind schemes (NO, YES)

%湍流重構格式

MUSCL_TURB= NO

%

% Slope limiter (VENKATAKRISHNAN, MINMOD)

%限制器

SLOPE_LIMITER_TURB= VENKATAKRISHNAN

%

% Time discretization (EULER_IMPLICIT)

%湍流項推進格式

TIME_DISCRE_TURB= EULER_IMPLICIT

%

% Relaxation coefficient

RELAXATION_FACTOR_TURB= 0.9

% --------------------------- CONVERGENCE PARAMETERS  --------------------------%

%

% Convergence criteria (CAUCHY, RESIDUAL)

CONV_CRITERIA= RESIDUAL

%

% Residual reduction (order of magnitude with respect to the initial  value)

RESIDUAL_REDUCTION= 6

%

% Min value of the residual (log10 of the residual)

RESIDUAL_MINVAL= -12

%

% Start convergence criteria at iteration number

STARTCONV_ITER= 10

%

% 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

%網格輸入文件

MESH_FILENAME= wb_coarse.su2

%

% Mesh input file format (SU2, CGNS, NETCDF_ASCII)

%網格格式

MESH_FORMAT= SU2

%

% Mesh output file

%網格輸出文件

MESH_OUT_FILENAME= mesh_out.su2

%

% Restart flow input file

%重啟動輸入文件

SOLUTION_FLOW_FILENAME= restart_flow.dat

%

% Restart adjoint input file

%重啟動伴隨輸入文件

SOLUTION_ADJ_FILENAME= solution_adj.dat

%

% Output file format (PARAVIEW, TECPLOT, STL)

%輸出文件格式

OUTPUT_FORMAT= TECPLOT_BINARY

%

% Output file convergence history (w/o extension)

%輸出的殘差歷史文件

CONV_FILENAME= history

%

% Output file restart flow

%輸出的重啟動文件

RESTART_FLOW_FILENAME= restart_flow.dat

%

% Output file restart adjoint

%輸出的重啟動伴隨文件

RESTART_ADJ_FILENAME= restart_adj.dat

%

% Output file flow (w/o extension) variables

%流場體數據輸出文件名

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)

%邊界數據輸出文件

SURFACE_FLOW_FILENAME= surface_flow

%

% Output file surface adjoint coefficient (w/o extension)

SURFACE_ADJ_FILENAME= surface_adjoint

%文件輸出頻率

% Writing solution file frequency

WRT_SOL_FREQ= 500

%殘差信息輸出頻率

% Writing convergence history frequency

WRT_CON_FREQ= 1

%

#!/bin/bash

#SBATCH -N 7                               #并行節點數

#SBATCH -n 168                            #并行cpu數，=24*節點數

#SBATCH --job-name=DLR-F6     #job的名稱

#SBATCH --ntasks-per-node=24    #每個節點用到的cpu數，無需修改

#SBATCH --output=%j.out              #算例運行過程中在屏幕上顯示的信息

#SBATCH --error=%j.err                 #報錯信息

mpirun  SU2_CFD  coarseAoA0.490.cfg         #流場求解

mpirun  SU2_SOL  coarseAoA0.490.cfg         #輸出tecplot結果文件