1d colocated simple solution
TRANSCRIPT
1
METU Mechanical Engineering Department ME 485 Computational Fluid Dynamics using Finite Volume Method
Spring 2014 (Dr. Sert)
Demonstration of How SIMPLE Algorithm Works on 1D Co-located Meshes
Problem Definition
Simplify the incompressible flow in the following converging nozzle to be 1D and inviscid. Obtain the finite volume
solution using 5 cells of equal length. Density of the fluid is 1 kg/m3. As boundary conditions inlet velocity is given
1 m/s and exit pressure is specified as 0 Pa.
Cross sectional area of the nozzle decreases linearly
๐ด(๐ฅ) = 0.5 โ 0.2๐ฅ
Exit pressure is set to zero for simplicity. Actually the value of this reference pressure is not important for an
incompressible flow, because in INS only the pressure gradient (๐๐/๐๐ฅ) is important, not the actual pressure
values. If the actual exit pressure is ๐๐๐ก๐, pressure values that we will obtain by setting exit pressure to zero will
be gage pressures. To obtain absolute values we can add ๐๐๐ก๐ to all the pressure values.
Analytical Solution
Analytical solution of the problem is governed by the Bernoulli equation.
๐ +๐๐ข2
2= constant
Mass flow rate inside the nozzle is constant and its value is known due to the given inlet speed
๏ฟฝฬ๏ฟฝ = ๐ ๐ข๐๐ ๐ด๐๐ = 0.5 kg sโ
Using this value we can calculate the speed at any point inside the nozzle. Exit speed is
๐ข๐๐ฅ๐๐ก =๏ฟฝฬ๏ฟฝ
๐๐ด๐๐ฅ๐๐ก= 5m sโ
๐ฅ
๐ด๐๐ = 0.5 m2
๐ข๐๐ = 1 m/s
๐ด๐๐ฅ๐๐ก = 0.1 m2
๐๐๐ฅ๐๐ก = 0 Pa
๐ฟ = 2 m
๐ = 1 kg/m3
2
Using the known speed and pressure at the exit the constant of the Bernoulli equation can be calculated as
๐๐๐ฅ๐๐ก +๐๐ข๐๐ฅ๐๐ก
2
2= 0 +
(1)(5)2
2= 12.5 Pa
With the ๏ฟฝฬ๏ฟฝ = 0.5 equation and the above equation speed and pressure at any point inside the nozzle can be
determined.
Nodes and faces of the 5 cell mesh are shown below
Analytical solution at the faces and nodes is as follows
Face Node ๐ฅ [m] ๐ด [m2] ๐ข๐๐ฅ๐๐๐ก [m/s] ๐๐๐ฅ๐๐๐ก [Pa]
๐1 0.0 0.50 1.0000 12.0000
1 0.2 0.46 1.0870 11.9093
๐2 0.4 0.42 1.1905 11.7914
2 0.6 0.38 1.3158 11.6343
๐3 0.8 0.34 1.4706 11.4187
3 1.0 0.30 1.6667 11.1111
๐4 1.2 0.26 1.9231 10.6509
4 1.4 0.22 2.2727 9.9174
๐5 1.6 0.18 2.7778 8.6420
5 1.8 0.14 3.5714 6.1224
๐6 2.0 0.10 5.0000 0.0000
Discretization of the x-Momentum Equation
Consider the following cell P with W and E neighbors
For cell P, the discretized x-momentum equation without the viscous and source terms is
๐น๐๐ด๐๐ข๐ โ ๐น๐ค๐ด๐ค๐ข๐ค = โ๐๐
๐๐ฅ|๐โโ๐ (1)
where ๐น๐ = (๐๐ข)๐ , ๐น๐ค = (๐๐ข)๐ค are known, calculated using initial guesses or previous iteration values. ๐ข๐ and
๐ข๐ค of Eqn (1) can be expressed in terms of speeds at nodes using various schemes. Here upwind scheme is used
as follows
๐1 ๐2 ๐3 ๐4 ๐5 ๐6
1 2 3 4 5
๐ฅ
โ๐ฅ = 0.4 m
๐ค ๐
W P E
3
๐ข๐ = {
๐ข๐ ๐ข๐ธ if if ๐น๐ > 0
๐น๐ < 0 โ ๐ข๐ = ๐ข๐
max(๐น๐ , 0)
๐น๐+ ๐ข๐ธ
max(โ๐น๐ , 0)
โ๐น๐
๐ข๐ค = {
๐ข๐ ๐ข๐ if if ๐น๐ค > 0
๐น๐ค < 0 โ ๐ข๐ค = ๐ข๐
max(๐น๐ค , 0)
๐น๐ค+ ๐ข๐
max(โ๐น๐ค, 0)
โ๐น๐ค
Pressure derivative of Eqn (1) is discretized as
๐๐
๐๐ฅ|๐=๐๐ธ โ ๐๐2โ๐ฅ
Volume of cell P is
โโ๐= ๐ด๐โ๐ฅ
where ๐ด๐ is the cross sectional area at node P.
Substituting these details into Eqn (1) we get
๐น๐๐ด๐ [๐ข๐max(๐น๐ , 0)
๐น๐+ ๐ข๐ธ
max(โ๐น๐, 0)
โ๐น๐] โ ๐น๐ค๐ด๐ค [๐ข๐
max(๐น๐ค, 0)
๐น๐ค+ ๐ข๐
max(โ๐น๐ค, 0)
โ๐น๐ค] = ๐๐
๐ข โ ๐ด๐๐๐ธ โ ๐๐
2 (2)
which can be arranged as
๐๐๐ข ๐ข๐ + ๐๐
๐ข๐ข๐ + ๐๐ธ๐ข๐ข๐ธ = ๐๐
๐ข โ ๐ด๐๐๐ธ โ ๐๐
2 (3)
where
๐๐๐ข = โ๐ด๐คmax (๐น๐ค , 0)
๐๐ธ๐ข = โ๐ด๐max(โ๐น๐ , 0)
๐๐๐ข = ๐ด๐คmax(โ๐น๐ค , 0) + ๐ด๐max(๐น๐ , 0)
๐๐๐ข = 0
Eqn (3) can also be written as
๐ข๐ = ๏ฟฝฬ๏ฟฝ๐ โ ๐๐๐ข๐๐ธ โ ๐๐
2 (4)
where
๏ฟฝฬ๏ฟฝ๐ =1
๐๐๐ข (๐๐
๐ข โโ๐๐๐๐ข ๐ข๐๐
๐๐
) and ๐๐๐ข =
๐ด๐๐๐๐ข (5)
Although the source term is zero, it is kept in the equations because for boundary cells there may be nonzero
contributions to it.
4
Modification of the x-Momentum Equation for Boundary Cells
Cell 1:
At the west face inlet velocity is known, i.e. in the x-momentum equation flux at the west face is known
๐น๐ค๐ด๐ค๐ข๐ค = ๐๐ข๐๐2 ๐ด๐๐ = known
This can be taken to the right hand side of the equation to act as a source term.
For the pressure derivative one-sided difference can be used instead of central differencing
๐๐
๐๐ฅ|๐=๐2 โ ๐1โ๐ฅ
With these, Eqn (3) for cell 1 becomes (modified terms are shown in red)
๐๐๐ข ๐ข๐ + ๐๐
๐ข๐ข๐ + ๐๐ธ๐ข๐ข๐ธ = ๐๐
๐ข โ ๐ด๐(๐๐ธ โ ๐๐)
where
๐๐๐ข = 0
๐๐ธ๐ข = โ๐ด๐max(โ๐น๐ , 0)
๐๐๐ข = ๐ด๐max(๐น๐ , 0)
๐๐๐ข = ๐๐ข๐๐
2 ๐ด๐๐
Therefore at an inlet boundary where velocity is given, following changes occur in the x-momentum equation
Coefficient of the ghost neighbor is set to zero.
๐๐๐ข coefficient changes because there is no contribution from the ghost neighbor.
Momentum flux created by the known inlet velocity acts as a source term.
Pressure discretization becomes one-sided (not central).
Cell 5:
Considering that the right end of the domain is an exit boundary we can use
๐ข๐ = ๐ข๐
Pressure gradient term can be discretized to make use of the given ๐๐๐ฅ๐๐ก value.
๐๐
๐๐ฅ|๐=๐๐ โ ๐๐คโ๐ฅ
=๐๐๐ฅ๐๐ก โ
๐๐ + ๐๐2
โ๐ฅ=2๐๐๐ฅ๐๐ก โ ๐๐ โ ๐๐
2โ๐ฅ
๐ค ๐
1 2
๐ข๐ค = ๐ข๐๐
P E
๐ค ๐
4 5
๐๐ = ๐๐๐ฅ๐๐ก
W P
5
With these, Eqn (3) for cell 1 becomes (modified terms are shown in red)
๐๐๐ข ๐ข๐ + ๐๐
๐ข๐ข๐ + ๐๐ธ๐ข๐ข๐ธ = โ๐ด๐
2๐๐๐ฅ๐๐ก โ ๐๐ โ ๐๐2โ๐ฅ
where
๐๐๐ข = โ๐ด๐คmax(๐น๐ค , 0)
๐๐ธ๐ข = 0
๐๐๐ข = ๐ด๐คmax(โ๐น๐ค , 0) + ๐ด๐max(๐น๐ , 0)
Therefore at an exit boundary where pressure is given, following changes occur in the x-momentum equation
Coefficient of the ghost neighbor is set to zero.
Pressure discretization uses the known exit pressure.
Face Velocity Calculation using Rhie-Chow (Momentum) Interpolation and Relaxation
In total, there are 6 faces in the mesh. Consider the following face ๐ with neighboring cells L (left) and R (right).
Using Rhie-Chow interpolation and velocity under-relaxation, velocity at face ๐ is calculated as
๐ข๐ = ๐ผ๐ข[๏ฟฝฬ๏ฟฝ๐ โ ๐๐๐ข(๐๐ โ ๐๐ฟ)] + (1 โ ๐ผ๐ข)๐ข๐
๐๐ฟ๐ท (6)
where
๏ฟฝฬ๏ฟฝ๐ =๏ฟฝฬ๏ฟฝ๐ฟ + ๏ฟฝฬ๏ฟฝ๐
2 , ๐๐
๐ข =๐๐ฟ๐ข + ๐๐
๐ข
2
๐ผ๐ข is the velocity under-relaxation factor and ๐ข๐๐๐ฟ๐ท is the face velocity of the previous iteration.
Eqn (6) and the above expressions for ๏ฟฝฬ๏ฟฝ๐ and ๐๐๐ข need to be modified at the boundary faces.
Modification at face 1:
Face 1 at the left boundary has a specified inlet velocity, so we do not use Eqn (6) at face 1, i.e. we do not need
๏ฟฝฬ๏ฟฝ๐1 or ๐๐1๐ข .
๐
L R
๐1
๐ข๐1 = ๐ข๐๐
6
Modification at face 6:
There is no cell on the right of face 6. Instead of central interpolation, one-sided interpolation can be used to
calculate ๏ฟฝฬ๏ฟฝ๐6 and ๐๐6๐ข . With the assumption of constant cell size
๏ฟฝฬ๏ฟฝ๐6 = ๏ฟฝฬ๏ฟฝ5 +๏ฟฝฬ๏ฟฝ5 โ ๏ฟฝฬ๏ฟฝ42
, ๐๐6๐ข = ๐5
๐ข +๐5๐ข โ ๐4
๐ข
2
Also (๐๐ โ ๐๐ฟ) term of Eqn (6) can be expressed in terms of the known exit pressure as
(๐๐๐ฅ๐๐ก โ ๐5)
1/2
which comes from ๐๐
๐๐ฅ|๐6โ
๐๐๐ฅ๐๐กโ๐5
โ๐ฅ/2
Pressure Correction (PC) Equation
PC equation is
๐น๐โฒ๐ด๐ โ ๐น๐ค
โฒ๐ด๐ค = โ๐ด๐๐น๐โ + ๐ด๐ค๐น๐ค
โ
Relating velocity corrections to pressure corrections as follows
๐น๐โฒ = ๐๐ข๐
โฒ = โ๐๐๐๐ข(๐๐ธ
โฒ โ ๐๐โฒ ) and ๐น๐ค
โฒ = ๐๐ข๐คโฒ = โ๐๐๐ค
๐ข (๐๐โฒ โ ๐๐
โฒ )
PC equation becomes
๐๐๐๐ถ๐๐
โฒ + ๐๐๐๐ถ๐๐
โฒ + ๐๐ธ๐๐ถ๐๐ธ
โฒ = โ๐ด๐๐น๐โ + ๐ด๐ค๐น๐ค
โ (7)
๐๐๐๐ถ = โ๐๐๐ค๐ด๐ค
๐๐๐๐ถ = ๐๐๐ค๐ด๐ค + ๐๐๐๐ด๐
๐๐ธ๐๐ถ = โ๐๐๐๐ด๐
Eqn (7) is modified as follows for boundary cells.
Modification for cell 1:
At west face inlet velocity is specified and ๐ข๐คโฒ = 0. Due to this following changes happen
๐๐๐๐ถ = 0 , ๐๐
๐๐ถ = ๐๐๐๐ด๐
๐6
๐๐ = ๐๐๐ฅ๐๐ก
4 5
๐ค ๐
1 2
๐ข๐ค = ๐ข๐๐
P E
7
Modification for cell 5:
๐ข๐โฒ expression need to be modified because there is no ๐๐ธ
โฒ . Instead of using (๐๐ธโฒ โ ๐๐
โฒ ) we can use half cell as
๐ข๐โฒ =
๐๐๐ข(๐๐๐ฅ๐๐ก
โฒ โ ๐๐โฒ )
1/2
where ๐๐๐ฅ๐๐กโฒ = 0 because exit pressure is fixed. Due to this coefficients of the PC change as follows
๐๐ธ๐๐ถ = 0 , ๐๐
๐๐ถ = 2๐๐๐๐ด๐ + ๐๐๐ค๐ด๐ค
Face Velocity Corrections
For the above face ๐, velocity correction is done as follows
๐ข๐ = ๐ข๐โ โ ๐๐
๐ข(๐๐ โฒ โ ๐๐ฟ
โฒ ) (8)
where ๐ข๐โ is the velocity calculated previously using Rhie-Chow interpolation. For the boundary faces Eqn (8) is
used as follows
Modification for face 1: Inlet velocity is given and no correction is done.
Modification for face 6: Similar to the previous step we use
๐ข๐6 = ๐ข๐6โ โ ๐๐6
๐ข(๐๐๐ฅ๐๐กโฒ โ ๐5
โฒ )
1/2 where ๐๐๐ฅ๐๐ก
โฒ = 0
Correct Cell Center Velocities
๐ข๐ = ๐ข๐โ โ ๐๐
๐ข(๐๐ธโฒ โ ๐๐
โฒ )
2 (9)
Eqn (9) will be modified for the boundary cells.
๐ค ๐
4 5
๐๐ = ๐๐๐ฅ๐๐ก
W P
๐
L R
๐ค ๐
W P E
8
Modification for cell 1: West cell does not exist. Pressure correction difference can be done in a one-sided way.
๐ข1 = ๐ข1โ โ ๐1
๐ข(๐2โฒ โ ๐1
โฒ )
1
Modification for cell 5: East cell does not exist. Pressure correction difference can be done in a one-sided way
using the fact that exit pressure is fixed.
๐ข5 = ๐ข5โ โ ๐5
๐ข(๐๐๐ฅ๐๐กโฒ โ ๐5
โฒ )
1/2 where ๐๐๐ฅ๐๐ก
โฒ = 0
Correct Pressures
๐๐ = ๐๐โ + ๐ผ๐๐1
โฒ (10)
where ๐๐โ is the pressure of the previous iteration (or the initial guess) and ๐ผ๐ is the pressure relaxation factor.
SIMPLE Iterations
STEP 1:
As initial guess we can use the inlet velocity and exit pressure at all nodes and faces.
๐ข1 = ๐ข2 = ๐ข3 = ๐ข4 = ๐ข5 = 1.0
๐ข๐1 = ๐ข๐2 = ๐ข๐3 = ๐ข๐4 = ๐ข๐5 = ๐ข๐6 = 1.0
๐1 = ๐2 = ๐3 = ๐4 = ๐5 = 0.0
ITERATION 1:
STEP 2: Setup x-momentum equation set to solve for ๐ขโ.
Cell 1:
Knowns: ๐น๐ = (๐๐ข)๐ = 1.0 , ๐น๐ค = (๐๐ข)๐ค = 1.0 , ๐ด๐ค = 0.5 , ๐ด๐ = 0.42 , ๐๐ = ๐๐ธ = 0.0
๐๐๐ข = 0.0 , ๐๐
๐ข = 0.42 , ๐๐ธ๐ข = 0.0 , ๐๐
๐ข = 0.5
๏ฟฝฬ๏ฟฝ1 =0.5 โ 0.0
0.42= 1.1905 , ๐1
๐ข =0.46
0.42= 1.0952
Cell 1 eqn is : 0.42๐ข1โ = 0.5 โ 0.46(0.0 โ 0.0)
9
Cell 2:
Knowns: ๐น๐ = (๐๐ข)๐ = 1.0 , ๐น๐ค = (๐๐ข)๐ค = 1.0 , ๐ด๐ค = 0.42 , ๐ด๐ = 0.34 , ๐๐ = ๐๐ธ = 0.0
๐๐๐ข = โ0.42 , ๐๐
๐ข = 0.34 , ๐๐ธ๐ข = 0.0 , ๐๐
๐ข = 0.0
๏ฟฝฬ๏ฟฝ2 =0.0 โ ((โ0.42)(1.0))
0.34= 1.1905 , ๐2
๐ข =0.38
0.34= 1.0952
Cell 2 eqn is : โ0.42๐ข1โ + 0.34๐ข2
โ = โ0.38(0.0 โ 0.0)/2
Cell 3:
Knowns: ๐น๐ = (๐๐ข)๐ = 1.0 , ๐น๐ค = (๐๐ข)๐ค = 1.0 , ๐ด๐ค = 0.34 , ๐ด๐ = 0.26 , ๐๐ = ๐๐ธ = 0.0
๐๐๐ข = โ0.34 , ๐๐
๐ข = 0.26 , ๐๐ธ๐ข = 0.0 , ๐๐
๐ข = 0.0
๏ฟฝฬ๏ฟฝ3 =0.0 โ ((โ0.34)(1.0))
0.26= 1.3077 , ๐3
๐ข =0.30
0.26= 1.1538
Cell 3 eqn is : โ0.34๐ข2โ + 0.26๐ข3
โ = โ0.30(0.0 โ 0.0)/2
Cell 4:
Knowns: ๐น๐ = (๐๐ข)๐ = 1.0 , ๐น๐ค = (๐๐ข)๐ค = 1.0 , ๐ด๐ค = 0.26 , ๐ด๐ = 0.18 , ๐๐ = ๐๐ธ = 0.0
๐๐๐ข = โ0.26 , ๐๐
๐ข = 0.18 , ๐๐ธ๐ข = 0.0 , ๐๐
๐ข = 0.0
๏ฟฝฬ๏ฟฝ4 =0.0 โ ((โ0.26)(1.0))
0.18= 1.4444 , ๐4
๐ข =0.22
0.18= 1.2222
Cell 4 eqn is : โ0.26๐ข3โ + 0.18๐ข4
โ = โ0.22(0.0 โ 0.0)/2
Cell 5:
Knowns: ๐น๐ = (๐๐ข)๐ = 1.0 , ๐น๐ค = (๐๐ข)๐ค = 1.0 , ๐ด๐ค = 0.18 , ๐ด๐ = 0.1 , ๐๐ = ๐๐ = ๐๐๐ฅ๐๐ก = 0.0
๐๐๐ข = โ0.18 , ๐๐
๐ข = 0.1 , ๐๐ธ๐ข = 0.0 , ๐๐
๐ข = 0.0
๏ฟฝฬ๏ฟฝ5 =0.0 โ ((โ0.18)(1.0))
0.1= 1.8000 , ๐5
๐ข =0.14
0.1= 1.4000
Cell 5 eqn is : โ0.18๐ข4โ + 0.1๐ข5
โ = โ0.14(2(0.0) โ 0.0 โ 0.0)/2
Discretized x-momentum equation system and the solution for ๐ขโ is
[ 0.42 0 0 0 0โ0.42 0.34 0 0 00 โ0.34 0.26 0 00 0 โ0.26 0.18 00 0 0 โ0.18 0.1]
{
๐ข1โ
๐ข2โ
๐ข3โ
๐ข4โ
๐ข5โ}
=
{
0.50000 }
โ
{
๐ข1โ
๐ข2โ
๐ข3โ
๐ข4โ
๐ข5โ}
=
{
1.19051.47061.92312.77780.5000}
10
STEP 3: Calculate face velocities using Rhie-Chow interpolation and ๐ผ๐ข = 0.6. These velocities will be used as
โstarโ velocities in Step 5.
Face 1: ๐ข๐1 = 1.0
Face 2: ๏ฟฝฬ๏ฟฝ๐2 =๏ฟฝฬ๏ฟฝ1+๏ฟฝฬ๏ฟฝ2
2= 1.2129 , ๐๐2
๐ข =๐1๐ข+๐2
๐ข
2= 1.1064 โ
๐ข๐2 = (0.6)[1.2129 โ 1.1064(0.0 โ 0.0)] + (1 โ 0.6)(1.0) = 1.1277
Face 3: ๏ฟฝฬ๏ฟฝ๐3 =๏ฟฝฬ๏ฟฝ2+๏ฟฝฬ๏ฟฝ3
2= 1.2715 , ๐๐3
๐ข =๐2๐ข+๐3
๐ข
2= 1.1357 โ
๐ข๐3 = (0.6)[1.2715 โ 1.1357(0.0 โ 0.0)] + (1 โ 0.6)(1.0) = 1.1629
Face 4: ๏ฟฝฬ๏ฟฝ๐4 =๏ฟฝฬ๏ฟฝ3+๏ฟฝฬ๏ฟฝ4
2= 1.3761 , ๐๐4
๐ข =๐3๐ข+๐4
๐ข
2= 1.1880 โ
๐ข๐4 = (0.6)[1.3761 โ 1.1880(0.0 โ 0.0)] + (1 โ 0.6)(1.0) = 1.2256
Face 5: ๏ฟฝฬ๏ฟฝ๐5 =๏ฟฝฬ๏ฟฝ4+๏ฟฝฬ๏ฟฝ5
2= 1.6222 , ๐๐5
๐ข =๐4๐ข+๐5
๐ข
2= 1.3111 โ
๐ข๐5 = (0.6)[1.6222 โ 1.3111(0.0 โ 0.0)] + (1 โ 0.6)(1.0) = 1.3733
Face 6: ๏ฟฝฬ๏ฟฝ๐6 = ๏ฟฝฬ๏ฟฝ5 +๏ฟฝฬ๏ฟฝ5โ๏ฟฝฬ๏ฟฝ4
2= 1.9778 , ๐๐6
๐ข = ๐5๐ข +
๐5๐ขโ๐4
๐ข
2= 1.4889 โ
๐ข๐5 = (0.6)[1.9778 โ 1.4889(0.0 โ 0.0)] + (1 โ 0.6)(1.0) = 1.5867
STEP 4: Calculate the coefficients of the pressure correction equation system solve for ๐โฒ values.
Cell 1: ๐๐๐๐ถ = 0.0
๐๐ธ๐๐ถ = โ๐๐๐
๐ข๐ด๐ = โ(1)(1.1064)(0.42) = โ0.4647
๐๐๐๐ถ = ๐๐๐
๐ข๐ด๐ = 0.4647
RHS value: โ๐ด๐๐น๐โ + ๐ด๐ค๐น๐ค
โ = โ(0.42)(1.1277) + (0.5)(1.0) = 0.0264
Cell 2: ๐๐๐๐ถ = โ๐๐๐ค
๐ข๐ด๐ค = โ(1)(1.1064)(0.42) = โ0.4647
๐๐ธ๐๐ถ = โ๐๐๐
๐ข๐ด๐ = โ(1)(1.1357)(0.34) = โ0.3862
๐๐๐๐ถ = ๐๐๐ค
๐ข๐ด๐ค + ๐๐๐๐ข๐ด๐ = 0.8509
RHS value: โ๐ด๐๐น๐โ + ๐ด๐ค๐น๐ค
โ = โ(0.34)(1.1629) + (0.42)(1.1277) = 0.0783
Cell 3: ๐๐๐๐ถ = โ๐๐๐ค
๐ข๐ด๐ค = โ(1)(1.1357)(0.34) = โ0.3862
๐๐ธ๐๐ถ = โ๐๐๐
๐ข๐ด๐ = โ(1)(1.1880)(0.26) = โ0.3089
๐๐๐๐ถ = ๐๐๐ค
๐ข๐ด๐ค + ๐๐๐๐ข๐ด๐ = 0.6950
RHS value: โ๐ด๐๐น๐โ + ๐ด๐ค๐น๐ค
โ = โ(0.26)(1.2256) + (0.34)(1.1629) = 0.0767
Cell 4: ๐๐๐๐ถ = โ๐๐๐ค
๐ข๐ด๐ค = โ(1)(1.1880)(0.26) = โ0.3089
๐๐ธ๐๐ถ = โ๐๐๐
๐ข๐ด๐ = โ(1)(1.3111)(0.18) = โ0.2360
๐๐๐๐ถ = ๐๐๐ค
๐ข๐ด๐ค + ๐๐๐๐ข๐ด๐ = 0.5449
RHS value: โ๐ด๐๐น๐โ + ๐ด๐ค๐น๐ค
โ = โ(0.18)(1.3733) + (0.26)(1.2256) = 0.0715
11
Cell 5: ๐๐๐๐ถ = โ๐๐๐ค
๐ข๐ด๐ค = โ(1)(1.3111)(0.18) = โ0.2360
๐๐ธ๐๐ถ = 0.0
๐๐๐๐ถ = ๐๐๐ค
๐ข๐ด๐ค + 2๐๐๐๐ข๐ด๐ = 0.5338
RHS value: โ๐ด๐๐น๐โ + ๐ด๐ค๐น๐ค
โ = โ(0.1)(1.5867) + (0.18)(1.3733) = 0.0885
Discretized PC equation system and the solution for ๐โฒ is
[ 0.4647 โ0.4647 0 0 0โ0.0467 0.8509 โ0.3862 0 0
0 โ0.3862 0.6950 โ0.3089 00 0 โ0.3089 0.5449 โ0.23600 0 0 โ0.2360 0.5338 ]
{
๐1โฒ
๐2โฒ
๐3โฒ
๐4โฒ
๐5โฒ}
=
{
0.02640.07830.07670.07150.0885}
โ
{
๐1โฒ
๐2โฒ
๐3โฒ
๐4โฒ
๐5โฒ}
=
{
3.13213.07542.80452.21751.1463}
STEP 5: Correct face velocities using Eqn (8).
Face 1: ๐ข๐1 = 1.0 (No correction for the inlet velocity)
Face 2: ๐ข๐2 = ๐ข๐2โ + ๐๐2
๐ข (๐2โฒ โ ๐1
โฒ ) = 1.1277 โ 1.1064(3.0754 โ 3.1321) = 1.1905
Face 3: ๐ข๐3 = ๐ข๐3โ + ๐๐3
๐ข (๐3โฒ โ ๐2
โฒ ) = 1.1629 โ 1.1357(2.8045 โ 3.0754) = 1.4706
Face 4: ๐ข๐4 = ๐ข๐4โ + ๐๐4
๐ข (๐4โฒ โ ๐3
โฒ ) = 1.2256 โ 1.1880(2.2175 โ 2.8045) = 1.9231
Face 5: ๐ข๐5 = ๐ข๐5โ + ๐๐5
๐ข (๐5โฒ โ ๐4
โฒ ) = 1.3733 โ 1.3111(1.1463 โ 2.2175) = 2.7778
Face 6: ๐ข๐6 = ๐ข๐6โ + ๐๐6
๐ข (๐๐๐ฅ๐๐กโฒ โ๐5
โฒ)
0.5= 1.5867 โ 1.4889
(0.0โ1.1463)
0.5= 5.0000
Important note: As seen, corrected face velocities satisfy the continuity equation exactly, i.e. mass is
conserved exactly in each cell with the corrected face velocities. For example consider cell 3.
Mass balance for cell 3: ๐๐ข๐ค๐ด๐ค โ ๐๐ข๐๐ด๐ = (1)(0.26)(1.9231) โ (1)(0.34)(1.4706) = 0.0000
This is true for all cells. For this 1D problem with specified inlet velocity, these corrected face velocities are
the same as the analytical values. For a 2D or 3D problem mass balance in each cell will again be exact, but
the face velocities cannot be equal to the analytical values, which are probably not known anyway. This
โexact mass balanceโ at each iteration is an important power of the SIMPLE algorithm. Although in this
problem face velocities are exact, cell center velocities and pressures will require a number of iterations to
converge and the converged values will not be equal to the analytical values. Accuracy will depend on the
used mesh and the selected convergence tolerance.
5 plus/minus typos. Results are correct.
12
STEP 6: Correct cell center velocities using Eqn (9).
Cell 1: ๐ข1 = ๐ข1โ + ๐1
๐ข (๐2โฒ โ ๐1
โฒ ) (1)โ = 1.1905 + 1.0952(3.0754 โ 3.1321) = 1.2526
Cell 2: ๐ข2 = ๐ข2โ + ๐2
๐ข (๐3โฒ โ ๐1
โฒ ) (2)โ = 1.4706 + 1.1176(2.8045 โ 3.0754) = 1.6537
Cell 3: ๐ข3 = ๐ข3โ + ๐3
๐ข (๐4โฒ โ ๐2
โฒ ) (2)โ = 1.9231 + 1.1538(2.2175 โ 2.8045) = 2.4181
Cell 4: ๐ข4 = ๐ข4โ + ๐4
๐ข (๐5โฒ โ ๐3
โฒ ) (2)โ = 2.7778 + 1.2222(1.1463 โ 2.2175) = 3.7911
Cell 5: ๐ข5 = ๐ข5โ + ๐5
๐ข (๐๐๐ฅ๐๐กโฒ โ ๐5
โฒ ) (1)โ = 5.0000 + 1.2222(1.1463 โ 2.2175) = 8.2096
STEP 7: Correct pressures using Eqn (10). Use a pressure relaxation value of ๐ผ๐ = 0.4.
Cell 1: ๐1 = ๐1โ + ๐ผ๐๐1
โฒ = 0.0 + 0.6 โ 3.1321 = 1.2529
Cell 2: ๐2 = ๐2โ + ๐ผ๐๐2
โฒ = 0.0 + 0.6 โ 3.0754 = 1.2302
Cell 3: ๐3 = ๐3โ + ๐ผ๐๐3
โฒ = 0.0 + 0.6 โ 2.8045 = 1.1218
Cell 4: ๐4 = ๐4โ + ๐ผ๐๐4
โฒ = 0.0 + 0.6 โ 2.2175 = 0.8870
Cell 5: ๐5 = ๐5โ + ๐ผ๐๐5
โฒ = 0.0 + 0.6 โ 1.1463 = 0.4585
STEP 8: Check for convergence. There are many possibilities here. One simple way is to compare velocity and
pressure differences of two consecutive iterations. Convergence is declared if the maximum of such
differences is less than a certain user specified tolerance value. It is preferred to use not just differences but
normalize them in a logical way, e.g. normalize the velocity differences with respect to the given inlet velocity.
It is always a good idea to select couple of critical monitoring points in the flow field and watch how variables
change at those points before declaring convergence.
If the convergence check fails go to Step 2 and perform one more iteration. Face and cell center velocities and
cell center pressures calculated in this iteration will be used in the next iteration.
The solution may also divergence, depending on how far the initial guess is from the exact solution, mesh
density and relaxation factors.
ITERATION 2:
You can use the MATLAB code NS_1D_Colocated.m available at the course web site to perform a full solution.
You can try different meshes, initial guesses, boundary condition implementations, relaxation factors, etc.
Results of the second iteration are given below for you to check the correctness of your hand calculations.
STEP 2:
๐1๐ข = 0.9200 ๏ฟฝฬ๏ฟฝ1 = 1.0000 ๐ข1
โ = 1.0209
๐2๐ข = 0.7600 ๏ฟฝฬ๏ฟฝ2 = 1.2526 ๐ข2
โ = 1.0707
๐3๐ข = 0.6000 ๏ฟฝฬ๏ฟฝ3 = 1.6537 ๐ข3
โ = 1.1736
๐4๐ข = 0.4400 ๏ฟฝฬ๏ฟฝ4 = 2.4181 ๐ข4
โ = 1.3195
๐5๐ข = 0.2800 ๏ฟฝฬ๏ฟฝ5 = 3.7911 ๐ข5
โ = 1.5079
13
STEP 3:
๐๐1๐ข = 1.0000 ๏ฟฝฬ๏ฟฝ๐1 = 0.8737 ๐ข๐1
โ = 1.0000
๐๐2๐ข = 0.8400 ๏ฟฝฬ๏ฟฝ๐2 = 1.1263 ๐ข๐2
โ = 1.1634
๐๐3๐ข = 0.6800 ๏ฟฝฬ๏ฟฝ๐3 = 1.5043 ๐ข๐3
โ = 1.5043
๐๐4๐ข = 0.5200 ๏ฟฝฬ๏ฟฝ๐4 = 2.0640 ๐ข๐4
โ = 2.0640
๐๐5๐ข = 0.3600 ๏ฟฝฬ๏ฟฝ๐5 = 3.0664 ๐ข๐5
โ = 3.0664
๐๐6๐ข = 0.2000 ๏ฟฝฬ๏ฟฝ๐6 = 4.7967 ๐ข๐6
โ = 4.7957
STEP 4: STEP 5: STEP 6: STEP 7:
๐1โฒ = โ0.5818 ๐ข๐1 = 1.0000 ๐ข1 = 1.0505 ๐1 = 1.0201
๐2โฒ = โ0.6141 ๐ข๐2 = 1.1905 ๐ข2 = 1.0641 ๐2 = 0.9845
๐3โฒ = โ0.5645 ๐ข๐3 = 1.4706 ๐ข3 = 1.0774 ๐3 = 0.8960
๐4โฒ = โ0.2934 ๐ข๐4 = 1.9231 ๐ข4 = 1.0835 ๐4 = 0.7996
๐5โฒ = โ0.5084 ๐ข๐5 = 2.7778 ๐ข5 = 1.7926 ๐5 = 0.6619
๐ข๐6 = 5.0000
Converged Solution with 5 cells
14
Converged Solution with 100 cells