30P30N多段翼流场计算报告

qiangsu5961

2019年4月2日 17:17

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来源：陆面体科技。

1. 30P30N多段翼

增升装置对于提高现代大型运输类飞机性能十分重要。高效的增升装置可以增加载重和航程、减轻飞机重量等。高升力机翼构型一般由翼身、前缘缝翼和后缘襟翼组成。在高速条件下，多段翼流场中可能存在转捩、分离、激波/边界层干扰等复杂流动现象。本文以30P30N多段翼为测试算例，检验SU2对于二维复杂外形的模拟能力。

30P30N多段翼流场计算报告的图1 图1：30P30N多段翼外形

30P30N多段翼流场计算报告的图2

图2：多段翼流动特征

2. 计算网格

表130P30N多段翼网格参数

网格构型	网格单元数
L1	63957
L2	112474
L3	260909
L4	583226
L5	1043636

网格采用JAXA提供的结构化网格(https://cfdws.chofu.jaxa. jp/apc/grids/3element_highlift_airfoil/30P30N_modified_slat_configF/plot3d/)。该网站提供了L1-L5等不同网格密度的五种结构化网格，这些网格具有相同的拓扑结构，都是由117块网格块构成，具体参数见表1。受计算资源限制，本文将对前4种网格进行网格无关性研究。该多段翼机翼弦长0.4572 m（18 inch），前缘逢翼和后缘襟翼均偏转30°。

30P30N多段翼流场计算报告的图3

30P30N多段翼流场计算报告的图4

图3：30P30N多段翼拓扑结构及网格

3.SU2求解器设置

下面以马赫数为0.20、攻角为16°、湍流模型为SA的计算工况为例，介绍30P30N算例的cfg文件参数设置。

（1）问题定义

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

% Physical governing equations (EULER, NAVIER_STOKES,

% WAVE_EQUATION, HEAT_EQUATION, FEM_ELASTICITY,

% POISSON_EQUATION)

PHYSICAL_PROBLEM= NAVIER_STOKES

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

KIND_TURB_MODEL= SST

% Mathematical problem (DIRECT, CONTINUOUS_ADJOINT)

MATH_PROBLEM= DIRECT

% Restart solution (NO, YES)

RESTART_SOL= NO

（2）自由来流参数设置

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

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

MACH_NUMBER= 0.2

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

AOA= 16.0

% Free-stream temperature (288.15 K by default)

FREESTREAM_TEMPERATURE= 300

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

REYNOLDS_NUMBER= 9.0E6

% Reynolds length (1 m by default)

REYNOLDS_LENGTH= 0.4572

（3）参考值设置

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

% Reference origin for moment computation

REF_ORIGIN_MOMENT_X = 0.25

REF_ORIGIN_MOMENT_Y = 0.00

REF_ORIGIN_MOMENT_Z = 0.00

% Reference length for pitching, rolling, and yawing non-dimensional moment

REF_LENGTH= 1.0

% Reference area for force coefficients (0 implies automatic calculation)

REF_AREA= 0.4572

（4）边界条件设置

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

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

MARKER_HEATFLUX= ( slat, 0.0, main, 0.0, flap, 0.0 )

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

MARKER_FAR= ( far )

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

MARKER_PLOTTING= ( slat, main, flap )

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

MARKER_MONITORING= ( slat, main, flap )

（5）数值求解通用参数

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

% Numerical method for spatial gradients (GREEN_GAUSS, WEIGHTED_LEAST_SQUARES)

NUM_METHOD_GRAD= WEIGHTED_LEAST_SQUARES

% Courant-Friedrichs-Lewy condition of the finest grid

CFL_NUMBER= 5

% Adaptive CFL number (NO, YES)

CFL_ADAPT= NO

% 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

EXT_ITER= 99999

% Linear solver for the implicit formulation (BCGSTAB, FGMRES)

LINEAR_SOLVER= BCGSTAB

% 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= 20

（6）多重网格参数

% -------------------------- MULTIGRID PARAMETERS -----------------------------%

% Multi-Grid Levels (0 = no multi-grid)

MGLEVEL= 0

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

MGCYCLE= W_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= 0.95

% Damping factor for the correction prolongation

MG_DAMP_PROLONGATION= 0.95

（7）流场计算数值格式

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

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

% TURKEL_PREC, MSW)

CONV_NUM_METHOD_FLOW= JST

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

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

MUSCL_FLOW= YES

% Slope limiter (VENKATAKRISHNAN, MINMOD)

SLOPE_LIMITER_FLOW= VENKATAKRISHNAN

% Coefficient for the limiter (smooth regions)

VENKAT_LIMITER_COEFF= 0.03

% 2nd and 4th order artificial dissipation coefficients

JST_SENSOR_COEFF= ( 0.5, 0.02 )

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

TIME_DISCRE_FLOW= EULER_IMPLICIT

（8）湍流计算数值格式

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

% Convective numerical method (SCALAR_UPWIND)

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)

MUSCL_TURB= NO

% Time discretization (EULER_IMPLICIT)

TIME_DISCRE_TURB= EULER_IMPLICIT

（9）收敛准则

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

% Convergence criteria (CAUCHY, RESIDUAL)

CONV_CRITERIA= RESIDUAL

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

RESIDUAL_REDUCTION= 10

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

RESIDUAL_MINVAL= -8

% 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-6

% Function to apply the criteria (LIFT, DRAG, NEARFIELD_PRESS, SENS_GEOMETRY,

% SENS_MACH, DELTA_LIFT, DELTA_DRAG)

CAUCHY_FUNC_FLOW= DRAG

（10）输入输出设置

% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%

% Mesh input file

MESH_FILENAME= L1-30P30N.su2

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

MESH_FORMAT= SU2

% Mesh output file

MESH_OUT_FILENAME= mesh_out.su2

% Restart flow input file

SOLUTION_FLOW_FILENAME= restart_flow.dat

% Restart adjoint input file

SOLUTION_ADJ_FILENAME= solution_adj.dat

% Output file format (PARAVIEW, TECPLOT, STL)

OUTPUT_FORMAT= TECPLOT

% Output file convergence history (w/o extension)

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= 250

% Writing convergence history frequency

WRT_CON_FREQ= 1

4.结果分析

4.1 湍流模型影响

30P30N多段翼流场计算报告的图5

图4：30P30N多段翼压力分布SA和SST计算结果对比

图4展示了SU2求解器分别采用SA模型和SST模型计算的30P30N多段翼表面压力分布（Ma=0.20 AoA=16° Rec=9.0×10⁶）。可以看到，SA、SST模型计算的压力分布在压力面（迎风面、正压区）与试验结果符合较好，而在吸力面（背风面、负压区）与试验结果存在一定差异。两种湍流模型相比，SA模型比SST模型更加接近试验结果。

4.2 网格密度影响

30P30N多段翼流场计算报告的图6

图5：30P30N多段翼压力分布不同网格密度计算结果对比

图5展示了SU2求解器分别采用不同网格密度计算的30P30N多段翼表面压力分布，湍流模型为SA模型。可以看到，随着网格密度的增加，背风面负压峰值不断升高，也越来越接近试验结果。该计算结果表明，30P30N多段翼算例对计算网格的密度较为敏感。采用L4网格和SA湍流模型计算的30P30N多段翼压力分布与试验结果基本符合。