Step 1: Create Geometry in GAMBIT Since the nozzle has a circular cross-section, it's reasonable to assume that the flow is axisymmetric. So the geometry to be created is two-dimensional. Start GAMBIT Create a new folder called nozzle and select this as the working directory. Add -id nozzle to the startup options. Create Axis Edge We'll create the bottom edge corresponding to the nozzle axis by creating vertices A and B shown in the problem specification and joining them by a straight line. Operation Toolpad > Geometry Command Button > Vertex Command Button > Create Vertex Create the following two vertices: Vertex 1: (-0.5,0,0) Vertex 2: (0.5,0,0) Operation Toolpad > Geometry Command Button > Edge Command Button > Create Edge Select vertex 1 by holding down the Shift button and clicking on it. Next, select vertex 2. Click Apply in the Create Straight Edge window. Create Wall Edge We'll next create the bottom edge corresponding to the nozzle wall. This edge is curved. Since A=pi r 2
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# Fluent Nozzle Tutorial

Mar 04, 2015

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Step 1: Create Geometry in GAMBIT

Since the nozzle has a circular cross-section, it's reasonable to assume that the flow is axisymmetric. So the geometry to be created is two-dimensional.

Start GAMBIT

Create a new folder called nozzle and select this as the working directory. Add -id nozzle to the startup options.

Create Axis Edge

We'll create the bottom edge corresponding to the nozzle axis by creating vertices A and B shown in the problem specification and joining them by a straight line.

Operation Toolpad > Geometry Command Button   > Vertex Command Button   >

Create Vertex

Create the following two vertices:

Vertex 1: (-0.5,0,0)Vertex 2: (0.5,0,0)

Operation Toolpad > Geometry Command Button   > Edge Command Button   >

Create Edge

Select vertex 1 by holding down the Shift button and clicking on it. Next, select vertex 2. Click Apply in the Create Straight Edge window.

Create Wall Edge

We'll next create the bottom edge corresponding to the nozzle wall. This edge is curved. Since

A=pi r2

where r(x) is the radius of the cross-section at x and

A = 0.1 + x2

for the given nozzle geometry, we get

r(x) = [(0.1 + x2)/pi]0.5; -0.5 < x < 0.5

This is the equation of the curved wall. Life would have been easier if GAMBIT allowed for this equation to be entered directly to create the curved edge. Instead, one has to create a file containing the coordinates of a series of points along the curved line and read in the file. The more number of points used along the curved edge, the smoother the resultant edge.

The file vert.dat contains the point definitions for the nozzle wall. Take a look at this file. The first line is

21 1

which says that there are 21 points along the edge and we are defining only 1 edge. This is followed by x,r and zcoordinates for each point along the edge. The r-value for each x was generated from the above equation for r(x). Thez-coordinate is 0 for all points since we have a 2D geometry.

Main Menu > File > Import > ICEM Input ...

Next to File Name:, enter the path to the vert.dat file that you downloaded or browse to it by clicking on theBrowse button.

Then, check the Verticesand Edges boxes under Geometry to Create as we want to create the vertices as well as the curved edge.

Click Accept.

This should create the curved edge. Here it is in relation to the vertices we created above:

(Click picture for larger image)

Create Inlet and Outlet Edges

Create the vertical edge for the inlet:

Operation Toolpad > Geometry Command Button   > Edge Command Button   >

Create Edge

Shift-click on vertex 1 and then the vertex above it to create the inlet edge.

Similarly, create the vertical edge for the outlet.

(Click picture for larger image)

Create Face

Form a face out of the area enclosed by the four edges:

Operation Toolpad > Geometry Command Button   > Face Command Button   >

Form Face

Recall that we have to shift-click on each of the edges enclosing the face and then click Apply to create the face.

Main Menu > File > Save

This will create the nozzle.dbs file in your working directory. Check that it has been created so that you will able to resume from here if necessary.

Step 2: Mesh Geometry in GAMBIT

Now that we have the basic geometry of the nozzle created, we need to mesh it. We would like to create a 50x20 grid for this geometry.

Mesh Edges

As in the previous tutorials, we will first start by meshing the edges.

Operation Toolpad > Mesh Command Button   > Edge Command Button   > Mesh

Edges

Like the Laminar Pipe Flow Tutorial, we are going to use even spacing between each of the mesh points. We won't be using the Grading this time, so deselect the box next to Grading that says Apply.

Then, change Interval Count to 20 for the side edges and Interval Count to 50 for the top and bottom edges.

(Click picture for larger image)

Mesh Face

Now that we have the edges meshed, we need to mesh the face.

Operation Toolpad > Mesh Command Button   > Face Command Button   > Mesh

Faces

As before, select the face and click the Apply button.

Figure

Main Menu > File > Save

Step 3: Specify Boundary Types in GAMBIT

Specify Boundary Types

Now that we have the mesh, we would like to specify the boundary conditions here in GAMBIT.

Operation Toolpad > Zones Command Button   > Specify Boundary Types Command

Button

This will bring up the Specify Boundary Types window on the Operation Panel. We will first specify that the left edge is the inlet. Under Entity:, pick Edges so that GAMBIT knows we want to pick an edge (face is default).

Now select the left edge by Shift-clicking on it. The selected edge should appear in the yellow box next to the Edgesbox you just worked with as well as the Label/Type list right under the Edges box.

Next to Name:, enter inlet.

For Type:, select WALL.

Click Apply. You should see the new entry appear under Name/Type box near the top of the window.

Repeat for the outlet, centerline, and wall edges.

You should have the following edges in the Name/Type list when finished:

Save and Export

Main Menu > File > Save

Main Menu > File > Export > Mesh...

Type in nozzle.msh for the File Name:. Select Export 2d Mesh since this is a 2 dimensional mesh. Click Accept.

Check nozzle.msh has been created in your working directory.

Step 4: Set Up Problem in FLUENT

If you have skipped the previous mesh generation steps 1-3, you can download the mesh by right-clicking on this link. Save the file as nozzle.msh in your working directory. You can then proceed with the flow solution steps below.

Launch FLUENT

Start > Programs > Fluent Inc > FLUENT 6.3.26 > FLUENT 6.3.26

Select 2ddp from the list of options and click Run.

Import File

Navigate to your working directory and select the nozzle.msh file. Click OK.

The following should appear in the FLUENT window:

Check that the displayed information is consistent with our expectations of the nozzle grid.

Check and Display Grid

First, we check the grid to make sure that there are no errors.

Main Menu > Grid > Check

Any errors in the grid would be reported at this time. Check the output and make sure that there are no errors reported.

Grid > Info > Size

How many cells and nodes does the grid have?

Main Menu > Display > Grid

Make sure all items under Surfaces is selected. Then click Display. The graphics window opens and the grid is displayed in it.

Some of the operations available in the graphics window are:

Translation: The grid can be translated in any direction by holding down the Left Mouse Button and then moving the mouse in the desired direction.

Zoom In: Hold down the Middle Mouse Button and drag a box from the Upper Left Hand Corner to the Lower Right Hand Corner over the area you want to zoom in on.

Zoom Out: Hold down the Middle Mouse Button and drag a box anywhere from the Lower Right Hand Corner to theUpper Left Hand Corner.

The grid has 50 divisions in the axial direction and 20 divisions in the radial direction. The total number of cells is 50x20=1000. Since we are assuming inviscid flow, we won't be resolving the viscous boundary layer adjacent to the wall. (The effect of the boundary layer is small in our case and can be neglected.) Thus, we don't need to cluster nodes towards the wall. So the grid has uniform spacing in the radial direction. We also use uniform spacing in the axial direction.

Look at specific parts of the grid by choosing each boundary (centerline, inlet, etc) listed under Surfaces in the Grid Display menu. Click to select and click again to deselect a specific boundary. Click Display after you have selected your boundaries.

Define Solver Properties

Define > Models > Solver...

We see that FLUENT offers two methods ("solvers") for solving the governing equations: Pressure-Based and Density-Based. To figure out the basic difference between these two solvers, let's turn to the documentation.

Main Menu > Help > User's Guide Contents ...

This should bring up FLUENT 6.3 User's Guide in your web browser. If not, access the User's Guide from the Start menu: Start > Programs > Fluent Inc Products > Fluent 6.3

Documentation > Fluent 6.3 Documentation. This will bring up the FLUENT documentation in your browser. Click on the link to the user's guide.

Go to chapter 25 in the user's guide; it discusses the Pressure-Based and Density-Based solvers. Section 25.1 introduces the two solvers:

"Historically speaking, the pressure-based approach was developed for low-speed incompressible flows, while the density-based approach was mainly used for high-speed compressible flows. However, recently both methods have been extended and reformulated to solve and operate for a wide range of flow conditions beyond their traditional or original intent."

"In both methods the velocity field is obtained from the momentum equations. In the density-based approach, the continuity equation is used to obtain the density field while the pressure field is determined from the equation of state."

"On the other hand, in the pressure-based approach, the pressure field is extracted by solving a pressure or pressure correction equation which is obtained by manipulating continuity and momentum equations."

Mull over this and the rest of this section. So which solver do we use for our nozzle problem? Turn to section 25.7.1 in chapter 25:

"The pressure-based solver traditionally has been used for incompressible and mildly compressible flows. The density-based approach, on the other hand, was originally designed for high-speed compressible flows. Both approaches are now applicable to a broad range of flows (from incompressible to highly compressible), but the origins of the density-based formulation may give it an accuracy (i.e. shock resolution) advantage over the pressure-based solver for high-speed compressible flows."

Since we are solving a high-speed compressible flow, let's pick the density-based solver.

In the Solver menu, select Density Based.

Under Space, choose Axisymmetric. This will solve the axisymmetric form of the governing equations.

Click OK.

Define > Models > Viscous

Select Inviscid under Model.

Click OK. This means the solver will neglect the viscous terms in the governing equations.

Define > Models > Energy

The energy equation needs to be turned on since this is a compressible flow where the energy equation is coupled to the continuity and momentum equations.

Make sure there is a check box next to Energy Equation and click OK.

Define > Materials

Select air under Fluid materials. Under Properties, choose Ideal Gas next to Density. You should see the window expand. This means FLUENT uses the ideal gas equation of state to relate density to the static pressure and temperature.

Click Change/Create. Close the window.

Define > Operating Conditions

We'll work in terms of absolute rather than gauge pressures in this example. So set Operating Pressure in thePressure box to 0.

Click OK.

It is important that you set the operating pressure correctly in compressible flow calculations since FLUENT uses it to compute absolute pressure to use in the ideal gas law.

Define > Boundary Conditions

Set boundary conditions for the following surfaces: inlet, outlet, centerline, wall.

Select inlet under Zone and pick pressure-inlet under Type as its boundary condition. Click Set.... The Pressure Inletwindow should come up.

Set the total pressure (noted as Gauge Total Pressure in FLUENT) at the inlet to 101,325 Pa as specified in the problem statement. For a subsonic inlet, Supersonic/Initial Gauge Pressure is the initial guess value for the static pressure. This initial guess value can be calculated from the 1D analysis since we know the area ratio at the inlet. This value is 99,348 Pa. Note that this value will be updated by the code. After you have entered the values, click OKto close the window.

Check that under the Thermal tab, the Total Temperature is 300 K. Click OK.

Using the same steps as above, pick pressure-outlet as the boundary condition for the outlet surface. Then, when the Pressure Outlet window comes up, set the pressure to 3738.9 as specified in the problem statement. Click OK.

Set the centerline zone to axis boundary type.

Make sure that wall zone is set to wall boundary type.

Step 5: Solve!

Now we will set the solve settings for this problem and then iterate through and actually solve it.

Solve > Control > Solution

We'll just use the defaults. Note that a second-order discretization scheme will be used. Click OK.

Set Initial Guess

Main Menu > Solve > Initialize > Initialize...

As you may recall from the previous tutorials, this is where we set the initial guess values for the iterative solution. We'll set these values to be the ones at the inlet. Select inlet under Compute From.

Click Init. The above values of pressure, velocity and temperature are now assigned to each cell in the grid. This completes the initialization. Close the window.

Set Convergence Criteria

FLUENT reports a residual for each governing equation being solved. The residual is a measure of how well the current solution satisfies the discrete form of each governing equation. We'll iterate the solution until the residual for each equation falls below 1e-6.

Main Menu > Solve > Monitors > Residual...

Change the residual under Convergence Criterion for continuity, x-velocity, y-velocity and energy to 1e-6.

Also, under Options, select Plot. This will plot the residuals in the graphics window as they are calculated.

Click OK.

Iterate Until Convergence

Main Menu > Solve > Iterate...

In the Iterate Window that comes up, change the Number of Iterations to 500. Click Iterate.

The residuals for each iteration is printed out as well as plotted in the graphics window as they are calculated.

Save case and data after you have obtained a converged solution.

Step 6: Analyze Results

Mach Number Plot

As in the previous tutorials, we are going to plot the velocity along the centerline. However, this time, we are going to use the dimensionless Mach quantity.

Plot > XY Plot

We are going plot the variation of the Mach number in the axial direction at the axis and wall. In addition, we will plot the corresponding variation from 1D theory.

Do everything as we would do for plotting the centerline velocity. However, instead of selecting Axial Velocity as theY Axis Function, select Mach Number.

Also, since we are going to plot this number at both the wall and axis, select centerline and wall under Surfaces.

Click Plot.

Figure

How does the FLUENT solution compare with the 1D solution?

Is the comparison better at the wall or at the axis? Can you explain this?

Save this plot as machplot.xy by checking Write to File and clicking Write....

Pressure Contour Plot

Sometimes, it is very useful to see how the pressure and temperature changes throughout the object. This can be done via contour plots.

Display > Contours...

First, we are going to plot the pressure contours of the nozzle. Therefore, make sure that under Contours Of,Pressure... and Static Pressure is selected.

We want this at a fine enough granularity so that we can see the pressure changes clearly. Under Levels, change the default 20 to 40. This increases the number of lines in the contour plot so that we can get a more accurate result.

Click Display.

Figure

Notice that the pressure on the fluid gets smaller as it flows to the right, as is consistent with fluid going through a nozzle.

Temperature Contour Plot

Now we will plot the temperature contours and see how the temperature varies throughout the nozzle.

Back in the Contours window, under Contours Of, select Temperature... and Static Temperature.

Click Display.

Figure

As we can see, the temperature decreases towards the right side of the nozzle, indicating a change of internal energy to kinetic energy as the fluid speeds up.

Step 7: Refine Mesh

Solve the nozzle flow for the same conditions as used in class on a 80x30 grid. Recall that the static pressure p at the exit is 3,738.9 Pa.

(a) Plot the variation of Mach number at the axis and the wall as a function of the axial distance x. Also, plot the corresponding results obtained on the 50x20 grid used in class and from the quasi-1D assumption. Recall that the quasi-1D result for the Mach number variation was given to you in the M_1D.xy file. Note all five curves should be plotted on the same graph so that you can compare them. You can make the plots in FLUENT, MATLAB or EXCEL.

(b) Plot the variation of static pressure at the axis and the wall as a function of the axial distance x. Also, plot the corresponding results obtained on the 50x20 grid used in class and from the quasi-1D assumption. Calculate the static pressure variation for the quasi-1D case from the Mach number variation given in M_1D.xy.

(c) Plot the variation of static temperature at the axis and the wall as a function of the axial distance x. Also, plot the corresponding results obtained on the 50x20 grid used in class and from the quasi-1D assumption. Calculate the static temperature variation for the quasi-1D case from the Mach number variation given in M_1D.xy.

Comment very briefly on the grid dependence of your results and the comparison with the quasi-1D results.