Analysis of 2D Compressible flow over airfoil using ANSYS Fluent

An airfoil-shaped body moving through a fluid produces an aerodynamic force. Some important constraints to describe an airfoil's shape are its camber and its thickness. For example, an airfoil of the NACA 4-digit series such as the NACA 2415 describes an airfoil with a camber of 0.02 chord located at 0.40 chord, with 0.15 chord of maximum thickness.

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ANSYS Workbench is a software environment for the execution of structural, thermal, and electromagnetic analyses. Focuses on geometry creation and optimization, attaching existing geometry, setting up the finite element model, resolving, and revising results.

Procedure:

• Run ANSYS workbench.
• Go to geometry-change to 2D properties.
• In the tree, outline select XY Plane.
• Select and import the formatted data points of the NACA series airfoil.
• Go to the concept and select lines from point option
• Start joining all the points of upper and lower airfoil separately
• Now click on generate after selecting point segment as 50.
• Click on the concept and select surface from edges and select all the points simultaneously
• In detail, view-select edges-click apply then select generate option.
• Go to sketch –select rectangle- select the airfoil and measure the distance by scaling the constraints.
• Go to the constraints-select inlet of the nozzle and select vertical lines.
• Now select all the edges of the rectangle and click on base objects -then click on apply- generate
• Now go to create -surface body-click target bodies -click apply and then generate.
• Now go to mesh option
• Select the project-select the edges-inlet, outlet, upper airfoil, and lower airfoil, and give the names by clicking on right click of the mouse and then create named selection.
• Now check whether the named selection is proper by cross verifying the selected names.
• Go to mesh option-create option-select the geometry and then apply
• Now generate the mesh by giving the iteration as 150
• Now select all the named surface and update the mesh.
• Go to setup option- select double precision-select 2D.
• In-tree page- Select solver as Pressure based.
• Select velocity formulation as Absolute.
• Select time- Steady.
• Select 2D space- Axisymmetric (only for 0degree).
• Click on the model- Select viscous as K epsilon (2 eq) & press.
• Click on materials-Select Air as fluid and Aluminium as solid.


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• Click on cell zone conditions- Select operating conditions and see that operating pressure is 101325Pa.
• Click on boundary conditions-Select inlet-velocity inlet- 100m/s.
• Select outlet- outlet pressure (gauge pressure as 0 itself) and click done.
• Click on reference value- Compute from the inlet.
• Click on initialization- Select standard initialization and compute from the inlet and initialize.
• Click on run calculation and calculate for 1000 iterations (till when the curve converges) and calculate.
• Go to results- Insert contour
• Go to geometry – For domain select all domains.
• For location select periodic 1.
• For variable select Velocity.
• For Range select global and apply.
• The result is displayed.
• Go to Function calculator- In function select MassflowAve.
• For location select outlet and calculate.
• Now to calculate pressure, mass flow average of pressure on the outlet, velocity, force- Go to function and select respective functions.
• The results will be displayed below.

• ANSYS

• Analysis

Analysis of 2D Compressible flow over airfoil using ANSYS Fluent