fanbox2.inp

/Batch
!             The name of this file is "fanbox2"
/prep7
!
!  Heated Solid contained in an enclosed region.
!             Fan model drive the flow
!             Two heated slabs
!  File contains information on the geometry and the meshing.
!
et,1,141                           ! The FLOTRAN Element type
eshape,2                           ! Use all quad elements
!!!!!!!!!!!!!!!!!!!  -  Mesh Density Controls
!
!                    Shape of the Problem Domain
!   These lines outline the areas chosen. Below are given the mesh
!   parameters used.
!
!                  I         II   III  IIa   E  F     G
!       __________________________________________________
!       |\_________________|_____|____|____|__|_|_________/|
!       ||\________________|_____|____|____|__|_|_________|_ IV
!       || |               |\ __/|    |\__/|  | |         ||
!       || |               ||   ||    ||  ||  | |         ||
!       || |               ||   ||    ||  ||  | |         ||
!       || |               ||   ||    ||  ||  | |         || V
!       || |               ||   ||    ||  ||  | |         ||
!       || |               ||___||    ||__||  | |         ||
!       ||_|_______________|/____\____|/__\|__|_|_________||
!       || |               |     |    |    |  | |         ||
!       || |               |     |    |    |  | |         || VI
!       || |               |     |    |    |  | |         ||
!       ||_|_______________|_____|____|____|__|_|_________||
!       |/_|_______________|_____|____|____|__|_|_________\|
!
!                     This is a Schematic - Check dimensions below
!
!   delb is the outer layer area thickness - extends all around
!   dels is the thickness of the boundary area that surrounds the heated solid.
!           These may be changed by the user
!           The origin is at the lower left corner.
!   The fluid is air. SI units are used, so dimensions are meters.
!
dxls = 1.7    ! Open space to the left of the box
dxrs = 1.7    ! Distance between first heat slab and the fan
dxf  = .20    ! Thickness of the Fan (F)
dxg  = 1.2    ! Open space to the right of the fan (G)
bxw  = .20    ! Width of the box
bxh  = 1.00   ! Height of the box
dyb  = .75    ! Distance below the box
dyt  = 0.8    ! Distance above the box
dxds = dxrs/2. - bxw ! Distance between heat slabs
xf1  = dxls+bxw+dxrs           ! x position of the fan
xrt = dxls+bxw+dxrs+dxf+dxg
ytp = dyb +bxh+dyt
!!!!!!!!!!!!!!!! Boundary layer size specifications
delb=.2
dels=.05
!
!    The Roman Numerals outside the figure designate regions.  The
!    designations are referenced below to determine the mesh region
!    parameters (enables mesh parameterization)
!
!  The parameters for the lesize commands
!
nb=5    ! Elements in outside boundary layer (thickness of region is delb)
rb=3.5    ! Mesh ratio in the outside boundary layer
no1=7   ! Elements in Region IV (top is in y direction, left side is x)
ro1=1.5
nx1=13    ! Elements in x direction - Region I
rx1=.4
nx2=5   ! Elements in x direction - Region II
rx2= -1.5
nx3= 12    ! Elements in x direction - Region III
rx3=-2.
rx3a= -1.5
nxe = 14
rxe = -2.5
nx4 = 3  ! Elements in the fan - Region F
rx4 = -2
nx5 = 14  ! Elements in x direction - Region G
rx5 = -2
ny1 = 6  ! Elements in y direction - Region VI
ry1 =1.5
ny2= 10   ! Elements in y direction - Region V
ry2 = -2
ns=4     ! Elements in the boundary layer around the solid
rs =5
!!!!!!!!!!!!!!!!!!! Aluminum-Silicon alloy
mp,kxx,2,2.2E-3           ! Thermal conductivity of solid in the heated box
mp,c,2,2.496              ! Specific heat of solid in heated solid
mp,dens,2,8.00E-3         ! Density of the heated solid
mp,kxx,3,2.0E-3
mp,c,3,2.0
mp,dens,3,8.00E-3         ! fan solid
mp,kxx,3,2.0E-3
qinsolid=9.4778E-4/(bxh*bxw)! Volumetric heat source/slab (1 watt)
!!!!!!!!!!!!!!!!!!!!!!  Geometry calculations are based on established
do1=dyt-delb-dels
k,1,0,0
k,2,do1+delb,0
dx1=dxls-dels
k,3,dx1,0
dx2=dxls+bxw+dels
k,4,dx2,0
dx3=xrt - 1.5*delb
k,5,xrt,0
k,6,delb,delb
k,7,do1+delb,delb
k,8,dx1,delb
k,9,dx2,delb
k,10,dx3,delb
dy1=dyb-dels
k,11,0,dy1
k,12,delb,dy1
k,13,do1+delb,dy1
k,14,dx1,dy1
k,15,dx2,dy1
k,16,dx3,dy1
k,17,xrt,dy1
k,18,dxls,dyb
k,19,dxls+bxw,dyb
k,20,dxls,dyb+bxh
k,21,dxls+bxw,dyb+bxh
dy2=dyb+bxh+dels
k,22,do1+delb,dy2
k,23,dx1,dy2
k,24,dx2,dy2
k,25,dx3,dy2
k,26,xrt,dy2
dy3=ytp-delb
k,27,delb,dy3
k,28,dx1,dy3
k,29,dx2,dy3
k,30,dx3,dy3
k,31,0,ytp
k,32,dx1,ytp
k,33,dx2,ytp
k,34,xrt,ytp
!  Outer boundary layer thickness delb lines1-12
l,1,6
l,2,7
l,3,8
l,4,9
l,5,10
l,17,16
l,26,25
l,34,30
l,33,29
l,32,28
l,31,27
l,11,12
lesize,all,,,nb,rb
!
!   Lower vertical lines 13-19 (ny1)
l,1,11
l,6,12
l,7,13
l,8,14
l,9,15
l,10,16
l,5,17
lsel,s,,,13,19
lesize,all,,,ny1,ry1
!
!   Second vertical lines 20-28 (ny2)
l,11,31
l,12,27
l,13,22
l,14,23
l,18,20
l,19,21
l,15,24
l,16,25
l,17,26
lsel,s,,,20,28
lesize,all,,,ny2,ry2
lesize,24,,,ny2,ry2*1.5
lesize,25,,,ny2,ry2*1.5
!
!  Wrap around  lines 29-36 (no1)
l,1,2
l,6,7
l,12,13
l,27,22
l,28,23
l,29,24
l,30,25
l,34,26
lsel,s,,,29,36
lesize,all,,,no1,ro1
!
!  First horizontal batch lines 37-42 (nx1)
l,2,3
l,7,8
l,13,14
l,22,23
l,27,28
l,31,32
lsel,s,,,37,42
lesize,all,,,nx1,rx1
!
! Second horizontal batch lines 43-50 (nx2)
l,3,4
l,8,9
l,14,15
l,18,19
l,20,21
l,23,24
l,28,29
l,32,33
lsel,s,,,43,50
lesize,all,,,nx2,rx2
!
! Third horizontal batch lines 51-56 (nx3)
l,4,5
l,9,10
l,15,16
l,24,25
l,29,30
l,33,34
lsel,s,,,52,55
lesize,all,,,nx3,rx3
lsel,s,,,51,56,5
lesize,all,,,nx3,-1.5
!
! Boundary layer around the solid 57-60 (ns)
l,18,14
l,19,15
l,21,24
l,20,23
lsel,s,,,57,60
lesize,all,,,ns,rs
alls
!!!!!!!!!        Create the heated solid first
a,18,19,21,20           ! Area 1 is the first heat slab
mat,1
asel,u,,,1
a,1,2,7,6
a,2,3,8,7
a,3,4,9,8
a,4,5,10,9
a,1,6,12,11
a,6,7,13,12
a,7,8,14,13
a,8,9,15,14
a,9,10,16,15
a,10,5,17,16
a,11,12,27,31
a,12,13,22,27
a,13,14,23,22
a,14,18,20,23
a,14,15,19,18
a,19,15,24,21
a,20,21,24,23
a,15,16,25,24
a,16,17,26,25
a,22,23,28,27
a,23,24,29,28
a,24,25,30,29
a,25,26,34,30
a,27,28,32,31
a,28,29,33,32
a,29,30,34,33
!
k,35,xf1,-.2
k,36,xf1,.2+ytp
l,35,36                ! Line 61
k,37,xf1+dxf,-.2
k,38,xf1+dxf,.2+ytp
l,37,38                ! Line 62
lsel,s,,,61,62
asel,s,,,5,10,5
asel,a,,,19,27,4
asbl,all,all
alls
*get,ode,kp,,num,max
xsel = dx2+dxds+dels
xser = xsel + bxw
k,ode+1,dx2+dxds,-.2
k,ode+2,dx2+dxds,.2+ytp
l,ode+1,ode+2                ! Line 51
k,ode+3,dx2+dxds+2*dels+bxw,-.2
k,ode+4,dx2+dxds+2*dels+bxw,.2+ytp
l,ode+3,ode+4                ! Line 52
asel,s,,,28,31,3
asel,a,,,32,36,2
lsel,s,,,51,52
asbl,all,all
k,51,xsel,dyb
k,52,xser,dyb
k,53,xser,dyb+bxh
k,54,xsel,dyb+bxh
lsel,none
!!!!!!!!! boundary layer lines for second slab
l,51,55
l,52,61
l,53,62
l,54,56
l,51,52
l,54,53
l,51,54
l,52,53
lsel,a,,,111,112
lsel,a,,,94,105,11
asel,s,,,51
asbl,all,all
llist
alls
!!!!!!!!! Redo horizontal lesizes on the right side
lsel,s,,,88,90
lsel,a,,,85
lesize,all,,,nx4
lsel,s,,,86,87
lesize,all,,,nx4,rx4
lsel,s,,,66,67
lsel,a,,,77,81,4
lsel,a,,,69,70
lesize,all,,,nx5,rx5
!!!!!!!!!!!!!!  Take into account the second slab
lsel,s,,,53,54
lsel,a,,,91,93,2
lsel,a,,,56,61,5
lesize,all,,,nx3,rx3
lsel,s,,,111,112
lsel,a,,,72,73
lesize,all,,,nx2,rx2
lsel,s,,,107,110
lesize,all,,,nx2
lsel,s,,,96,97
lsel,a,,,99,100
lsel,a,,,102,104,2
lesize,all,,,nxe,rxe
!!!!!!!!!   Slab Vertical lines
lsel,all
lesize,75,,,ny2,ry2*1.5
lesize,79,,,ny2,ry2*1.5
lesize,94,,,ny2,ry2
lesize,105,,,ny2,ry2
!!!!!!!!  Boundary layer vertical lines
lsel,s,,,55,65,10
lsel,a,,,68
lsel,a,,,98
lesize,all,,,nb,rb
lsel,s,,,71,74,3
lsel,a,,,62
lsel,a,,,101
lesize,all,,,nb,1./rb
mat,2
asel,s,,,1,36,35   ! Mesh heated solids first
amesh,all
alls
asel,u,,,38,40      ! Unselect non-fluid areas (fan boundary)
asel,u,,,1,36,35    ! Unselected heated solids
mat,1
amesh,all           ! Mesh the fluid regions
!!!!!!!!!!!         ! Mesh the fan
asel,s,,,39
real,2           ! Activate and define real constant set 2.
r,2,4,1,-.00125,-1.E-6      ! The Fan Constants
amesh,all
!!!!!!!!!!!!!!! Solid materials around the fan
real,1
mat,3
asel,s,,,38,40,2
amesh,all
!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!  Boundary conditions
! Right wall boundary condition
lsel,s,,,28,36,8
lsel,a,,,19
nsll,,1
d,all,vx,0
d,all,vy,0
sf,all,CONV,1.0,80.
! Upper wall condition
lsel,s,,,42,50,8
lsel,a,,,70,90,20
lsel,a,,,61
lsel,a,,,100,110,10
nsll,,1
d,all,vy,0
d,all,vx,0
!  Left wall boundary condition
lsel,s,,,13,20,7
nsll,,1
d,all,vx,0
d,all,vy,0
sf,all,CONV,1.0,80.
!!!!  Bottom boundary is Adiabatic
lsel,s,,,29,37,8
lsel,a,,,43,53,10
lsel,a,,,96,107,11
lsel,a,,,66,85,19
nsll,,1
d,all,vx,0
d,all,vy,0
!!!!!!!!!!!!!!!!!!!!!!!!!! Apply the volumetric heat source
asel,s,,,1
asel,a,,,36
esel,s,mat,,2
nsle
bfe,all,hgen,1,qinsolid
!!!!!!!!!!!!!!!!!!!!!!!!!! Apply 0 pressure at upper left corner
nsel,s,loc,x,0
nsel,r,loc,y,ytp
d,all,pres,0
!            The origin is at the lower left corner
TOFF,460
alls
save
finish
/solu
FLDA,SOLU,FLOW,1         ! Select flow option
FLDA,SOLU,TURB,1         ! Turn on turbulence
FLDA,OUTP,SUMF,10,       ! Summary frequency, every 10 global iterations
FLDA,PROT,DENS,AIR-IN    ! Choose AIR-IN, but use a constant reference
FLDA,PROT,VISC,AIR-IN
FLDA,PROT,COND,AIR-IN
FLDA,PROT,SPHT,AIR-IN
FLDA,PRES,REFE,14.7
FLDA,TEMP,NOMI,80
FLDA,TEMP,BULK,80
FLDA,MAXI,TEMP,1000
FLDA,TURB,WALL,EQLB
FLDA,TURB,RATI,100.
FLDA,METH,PRES,3
FLDA,CONV,PRES,1e-10
ACEL,0.,386.4             ! Gravity acts downward
FLDA,ITER,EXEC,20         ! Do all this for 20 global iterations
FLDA,STAB,MOME,1
FLDA,STAB,VISC,1.E-6
solve
FLDA,STAB,VISC,0
FLDA,ITER,EXEC,80        ! Get the solution out to 100 iterations
solve
flda,meth,temp,5        ! Invoke direct solve
flda,srch,temp,20
flda,conv,temp,1e-16
flda,relx,temp,1.0
flda,iter,exec,40
flda,outp,sumf,1
flda,solu,temp,1
flda,solu,flow,0
solve
save

finish

/exit