## 1. Create Case

From this tutorial, you will learn how to perform a 2D analysis of a supersonic flow past a 15 degrees inclined wedge in a tunnel.

After opening SimFlow, we will create a new case named *oblique_shock*

Go to

**New**panelProvide name

*oblique_shock*Click

**Create Case**

## 2. Import Geometry

Firstly, we need to Download Geometry: Oblique_shock and save it to the hard drive. Then:

Click

**Import Geometry**Select already downloaded geometry file

*oblique_shock.stl*Click

**Open**

## 3. Imported Geometry Units

The STL format does not contain the unit information which are defined during the geometry export. If we do not know the exported unit, we can estimate it based on the total size of the model. It is displayed next to *Geometry size* label. In our case, the default unit meter is correct.

To confirm default unit

*meter*, press**OK**

## 4. Geometry

After import, the tunnel geometry will be displayed in the graphics window.

Click

**Fit View**to zoom the geometry

## 5. Creating Face Group - Inlet

We are dealing with an internal flow problem. The imported geometry determines the bounds of the fluid domain. To inform the program where different boundaries should be created, we will create appropriate face groups.

Select the inlet face by holding

`CTRL`key and clicking on the geometry face in a 3D view. The selection should be marked in redClick on the

*Face Group*button in the graphics context toolbarPress

`Esc`key to clear the selection

## 6. Creating Face Group - Outlet

Rotate the view in a way you will be able to see the second end of the tunnel.

Select the outlet face by holding

`CTRL`key and clicking on the geometry faceClick on the

*Face Group*button in the graphics context toolbarPress

`Esc`key to clear the selection

## 7. Creating Face Group - Top

Now, select the top face of the tunnel.

Select the top face by holding

`CTRL`key and clicking on the geometry faceClick on the

*Face Group*button in the graphics context toolbar

## 8. Rename Face Groups

In the *Geometry Panel* , under the *oblique_shock* geometry we can find four face groups. The first group, named *default* , contains all non-selected surfaces. These surfaces will form the bottom walls of the tunnel. The next two groups represent the inlet and outlet of the fluid domain respectively. The last one represents the top wall of the tunnel. We will rename these groups to make the resulting boundary names more readable.

Select

*oblique_shock*geometryExpand

*Geometry Faces*Change face groups names accordingly (double click on its name and start editing)

*group_1*\(\rightarrow\)*inlet*

*group_2*\(\rightarrow\)*outlet*

*group_3*\(\rightarrow\)*top*

## 9. Meshing Parameters - Geometry

When geometry is ready we can move to the meshing step. We will define the boundary layer on the bottom and top wall of the tunnel.

Go to

*Hex Meshing*panelSelect the

*oblique_shock*componentEnable

*Mesh Geometry*Enable

*Create Boundary Layer Mesh*Mark

*top*face group to be inflated with a boundary layer

## 10. Base Mesh - Domain

In order to create a 2D mesh, we will use a *Plate* base mesh type.

Go to

*Base*tabSelect

*Plate*as a*Base Mesh Type*Click on

**Autosize**Define the number of divisions

*Division**320**100*

## 11. Solid Mesh - Material Point

Material Point tells the meshing algorithm on which side of the geometry the mesh is to be retained. Since we are considering flow inside the tunnel we need to place the material point inside the geometry.

Go to

*Point*tabSpecify location inside the tunnel

*Material Point**0**0.6**0*

## 12. Start Meshing

Everything is now ready for meshing.

Switch to

*Mesh*tabStart the meshing process with

**Mesh**button

## 13. Mesh

After the meshing process is finished the mesh should appear on the screen.

Set the XY orientation

*View XZ*Click

*Fit View*

## 14. Boundaries

To be able to assign inlet and outlet boundary conditions we have to adjust the mesh boundary types.

Define boundary types accordingly

*empty**Empty*

*oblique_shock**Wall*

*oblique_shock_inlet**Patch*

*oblique_shock_outlet**Patch*

*oblique_shock_top**Wall*

## 15. Select Solver

We want to analyze high-speed compressible flow inside the tunnel. For this purpose, we will use the Rho Central (rhoCentralFoam) solver.

Go to

*SETUP*panelSelect

**Transient**typeSelect

**Compressible**flow filterSelect

*Rho Central*solver**Select**solver

## 16. Parameters - Velocity

SimFlow allows users to create parameters that can be used instead of numbers. This allows to easily change a single property without the need to edit all inputs where a given property is used. In this tutorial, we will create a velocity parameter equal to 3 times the Mach number. The speed of sound for \(0^{\circ}C \; (273.15K)\) is \(331.5\; m/s\). To compute its value for temperature 300K we will use the following formula:

\(c_{air}=331.5 \cdot \sqrt{300/273.15}\)

Go to

*Parameters*panelDefine the new parameter name and formula and press

`Enter`

*Name**u**Formula*, 3*331.5*sqrt(300/273.15)]The newly created parameter will be shown in the parameters list.

## 17. Boundary Conditions - Inlet - Flow

Now, we will define the inlet and outlet boundary conditions. At the inlet, we will set constant fluid velocity using parameter *u* .

Go to

*Boundary Conditions*panelSelect

*oblique_shock_inlet*boundarySet the

*Velocity Inlet*characterSet the inlet velocity

*U**Reference Value \({\sf [m/s]}\)**u*

## 18. Boundary Conditions - Inlet - Thermal

Switch to

*Thermal*tabSet constant temperature at the inlet

*T**Type**Fixed Value*

*T**Value \({\sf [K]}\)**300*

## 19. Boundary Conditions - Outlet

At the outlet, we are going to apply the *Wave Transmissive* boundary condition. This type allows the pressure waves to freely escape the domain and prevents reflecting them from the outlet boundary.

Select

*oblique_shock_outlet*Set the pressure type

*p**Type**Wave Transmissive*

## 20. Monitors – Sampling

During calculation, we can observe intermediate results on a section plane. To add sampling data on a plane we need to define the plane and also select fields that will be sampled. Note that runtime post-processing can only be defined before starting calculations and can not be changed later on.

Go to

*Monitors*panelSwitch to

*Sampling*tabSelect

*Create Slice*Expand

*Fields*listSelect pressure

*p*, velocity*U*and Temperature*T*

## 21. Run - Time Control

For any simulation, it is very convenient to let the solver automatically determine the proper time step value. To use this option we need to define time step constraints by providing the initial time step (adjusted by the solver during computations), maximal time step value and the Courant number.

Go to

*RUN*panelSet the

*Simulation Time [s]*to*0.1*Change

*Time Stepping*to*Automatic*Set initial time step, maximum time step and the Courant number accordingly

*Initial \(\Delta t\) \({\sf [s]}\)**1e-05*

(solver will start computation with this value and adjust it in the next iterations)

*Max \(\Delta t\) \({\sf [s]}\)**1e-04*

*Max Co \({\sf [-]}\)**0.5*

## 22. Run - Output

We can control how often results should be saved on the hard drive. Only this data will be available for postprocessing.

Switch to

*Output*tabSet the

*Interval [s]*to*1e-03*

## 23. Run - CPU

To speed up calculation process increase the number of CPUs basing on your PC capability. We recommend using 4 cores for this tutorial. If you are using a free version you can use the contact form to Request 30-day Trial

Estimated computation time for the free version (2 processors): 20 minutes

Switch to

*CPU*tabChange the solver to

*parallel*Define the number of processors

Click

**Run Simulation**button

## 24. Residuals

When the calculation is finished you should see a similar residual plot.

## 25. Slice - Velocity Field

During computation *Slices* tab will appear next to the *Residuals*. Under this tab, we can preview results on the section plane.

Change tab to

*Slices*Select the pressure

*p*Click

*Adjust range to data*

## 26. Calculate Vorticity

The Mach number is not being computed by default during solver computations. In order to visualize it, we will compute the Mach number using the existing data.

Go to

*Calculate*panelSet the

*Time Rnge*to*Full Time Range*Set the

*Field*to*Mach Number*Click on

**Calculate**

## 27. Postprocessing – ParaView

Start ParaView to visualize the shock wave.

Go to

*POSTPROCESSING*panelClick on

**Run ParaView**

## 28. ParaView - Load Results

Load the results into the program.

Select

*oblique_shock*Uncheck

*Skip Zero Time*Click

**Apply**to load results into ParaViewClick

**Refresh**Select Mach number

*Ma*from the list

## 29. ParaView - Vorticity

The Mach number contour plot will be displayed in the graphic window.

Play with animation buttons to track the flow history

## 30. ParaView - Pressure Gradient (I)

In order to see shock waves more clearly we will display gradients of pressure p which will indicate the discontinuity region.

While holding the

`Ctrl`key push the`Spacebar`Start typing

*Gradient of Unstructured DataSet*and press`Enter`to select this command

## 31. ParaView - Pressure Gradient (II)

Now we will display the magnitude of the pressure gradient in the 3d view. We can adjust the coloring scheme to see the shock waves more clearly.

Click

**Apply**to display Pressure GradientSelect

*Gradients*from the Coloring listClick

*Choose preset*

## 32. ParaView - Coloring

We would like to have similar plots to the *Schlieren photography* which is often used in experiments to visualize density variation. For this purpose we will use *X Ray* preset.

Select

*X Ray*preset.**Apply**changes**Close**window

## 33. Paraview - Shock Wave - Results

Shock waves can be identified at the locations of the largest pressure gradient, which corresponds to the dark color in the image. The shock wave angle depends on the wedge angle and Mach Number.

In our case, the shock wave angle equals 31 degrees and is very close to the theoretical value. The analytical solution of this problem is well known and for instance, it can be found in:

Anderson J. Modern Compressible Flow: With Historical Perspective. McGraw-Hill Series in Aeronautical and Aerospace Engineering. McGraw-Hill, 2004. ISBN 9780071241366