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.


  • 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.

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Analysis of 2D Compressible flow over airfoil using ANSYS Fluent
Skyfi Labs Last Updated: 2021-04-01

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