飞机机翼的流场分析 - 副本

/FILNAME,Flow field analysis of aircraft,0
/PREP7
!定义流体单元
ET,1,141
!设置单元关键字
KEYOPT,1,4,1
!建立模型
K,1,0,0,0 !定义关键点
K,2,0.4,0,0
K,3,0.46,0.04,0
K,4,0.38,0.09,0
K,5,0.2,0.05,0
!定义直线
LSTR, 1, 2
LSTR, 5, 1
!建立机翼模型
FLST,3,4,3
FITEM,3,2
FITEM,3,3

FITEM,3,4
FITEM,3,5
BSPLIN, ,P51X, , , , ,-1,0,0,-1,-0.25,0,
FLST,2,3,4
FITEM,2,1

FITEM,2,3

FITEM,2,2
AL,P51X
RECTNG,-2,13,-0.8,1.6,
ASBA,2,1 !进行布尔减运算
!划分网格
LESIZE,1,,,15
LESIZE,2,,,15
LESIZE,3,,,15
ESIZE,0.12
mshape,1,2d !设置单元形状为三角形
AMESH,ALL
!进入求解
/SOL
!定义边界条件
DL,7, ,UY,0,1
DL,7, ,UX,0,1

DL,7, ,VX,0,0
DL,7, ,VY,0,0

DL,7, ,PRES,0,1

DL,5, ,UY,0,1
DL,5, ,UX,0 ,1
DL,5, ,PRES,0,1
!定义函数
*DEL,_FNCNAME
*DEL,_FNCMTID
*DEL,_FNCCSYS
*SET,_FNCNAME,'S'
*SET,_FNCCSYS,0
! /INPUT,SS.func,,,1
*DIM,%_FNCNAME%,TABLE,6,5,1,,,,%_FNCCSYS%
!
! Begin of equation: 280*{TIME}^2
*SET,%_FNCNAME%(0,0,1), 0.0, -999
*SET,%_FNCNAME%(2,0,1), 0.0
*SET,%_FNCNAME%(3,0,1), 0.0
*SET,%_FNCNAME%(4,0,1), 0.0
*SET,%_FNCNAME%(5,0,1), 0.0
*SET,%_FNCNAME%(6,0,1), 0.0
*SET,%_FNCNAME%(0,1,1), 1.0, -1, 0, 2, 0, 0, 1
*SET,%_FNCNAME%(0,2,1), 0.0, -2, 0, 1, 1, 17, -1
*SET,%_FNCNAME%(0,3,1), 0, -1, 0, 280, 0, 0, -2
*SET,%_FNCNAME%(0,4,1), 0.0, -3, 0, 1, -1, 3, -2
*SET,%_FNCNAME%(0,5,1), 0.0, 99, 0, 1, -3, 0, 0
! End of equation: 280*{TIME}^2
!-->
*DEL,_FNCNAME
*DEL,_FNCMTID
*DEL,_FNCCSYS
*SET,_FNCNAME,'V'
*SET,_FNCCSYS,0
! /INPUT,VV.func,,,1
*DIM,%_FNCNAME%,TABLE,6,3,1,,,,%_FNCCSYS%
!
! Begin of equation: 560*{TIME}
*SET,%_FNCNAME%(0,0,1), 0.0, -999
*SET,%_FNCNAME%(2,0,1), 0.0
*SET,%_FNCNAME%(3,0,1), 0.0
*SET,%_FNCNAME%(4,0,1), 0.0
*SET,%_FNCNAME%(5,0,1), 0.0
*SET,%_FNCNAME%(6,0,1), 0.0
*SET,%_FNCNAME%(0,1,1), 1.0, -1, 0, 560, 0, 0, 1
*SET,%_FNCNAME%(0,2,1), 0.0, -2, 0, 1, -1, 3, 1
*SET,%_FNCNAME%(0,3,1), 0, 99, 0, 1, -2, 0, 0
! End of equation: 560*{TIME}
!定义动壁面的位移边界条件
DL,2, ,UY,0,1
DL,2, ,UX,%S% ,1
DL,3, ,UY,0,1
DL,3, ,UX,%S% ,1
DL,1, ,UY,0,1
DL,1, ,UX,%S% ,1
!定义动壁面上的无滑移边界条件
DL,1, ,VX,%V%,0
DL,1, ,VY,0,0
DL,2, ,VX,%V%,0
DL,2, ,VY,0,0
DL,3, ,VX,%V%,0
DL,3, ,VY,0,0
DL,4, ,VX,0,0
DL,4, ,VY,0,0
DL,4, ,UY,0,1
DL,4, ,UX,0,1
DL,6, ,UY,0,1
DL,6, ,UX,0,1
DL,6, ,VY,0,0
!设置流体求解选项
FLDATA1,SOLU,TRAN,1
FLDATA1,SOLU,FLOW,1
FLDATA1,SOLU,TURB,1
FLDATA1,SOLU,ALE,1
!设置求解控制
FLDATA4,TIME,STEP,0.005,
FLDATA4,TIME,NUMB,34
FLDATA4,TIME,TEND,0.17,
FLDATA4,TIME,APPE,0.005,
!设置计算结果输出
FLDATA5,OUTP,PTOT,1
FLDATA5,OUTP,TTOT,1
FLDATA5,OUTP,HFLU,1
FLDATA5,OUTP,HFLM,1
FLDATA5,OUTP,STRM,1
FLDATA5,OUTP,PCOE,1
FLDATA5,OUTP,MACH,1
FLDATA5,OUTP,YPLU,1
FLDATA5

,OUTP,TAUW,1
FLDATA5,OUTP,RDFL,1
!设置流体属性参数
FLDATA7,PROT,DENS,CONSTANT
FLDATA8,NOMI,DENS,1.0
FLDATA7,PROT,VISC,CONSTANT
FLDATA8,NOMI,VISC,0.00002
!考虑流体重力
ACEL,0,9.81,0,
!设置流体求解稳定参数
FLDATA26,STAB,VISC,0.25,
!设置压力方程求解器
FLDATA18,METH,PRES,1
FLDATA19,TDMA,PRES,200,
!设置流体瞬态求解算法
FLDATA,OUTP,TAUW,T
FLDATA,TIME,METH,NEWM
FLDATA,TIME,DELT,0.5
!设置网格重分
FLDATA,REMESH,ELEM,ALL ! 设置重分单元的范围
!设置重分单元尺寸
FLDATA39,REME,REXP,1.4,
!设置重分单元的质量
FLDATA,REMESH,ARMA,40.0
FLDATA,REMESH,VOCH,8.0
FLDATA,REMESH,ARCH,40.0
!设置重分单元的频率
FLDATA39,REME,TIME,0.005,
!开始求解
SOLVE