EP-705 Fluent Quad & Airfoil Setup

Wikis > EP-705 Fluent Quad & Airfoil Setup



2. Geometry & Meshing PROCEDURE (without explicit inflation layer definition)

NOTE: These instructions match the steps taken in SimCafe’s tutorial on airfoil ( https://goo.gl/OLIX5g) and the tutorial regarding importing points (http://pjotr.ru/ansys_dm_01/)

  • Find online the coordinates for the desired airfoil.
    • You need to write the points into a .txt file with the following format:705-01
    • Any lines beginning with #’s are simply comments and do not have to be included.
    • There can be spaces and tabs between the numbers so do not worry too much about delimiting using only one space.
    • The first number is the group number and the second is the order within the group. The remaining three numbers are the XYZ coordinates of each point. You only need 1 group, however, for this procedure.
  • Follow the first 5 steps in the tutorial about point importing. Because this is a 2D procedure, you will only have one surface (one group of points) to create.
    • Before creating the surface of the Make sure to zoom into the trailing edge and connect the open points after creating the curve from the points.
  • After
    Use the same geometry made with the instructions from SimCafe but without the line projections.

    • The geometry should look similar to this:705-02
  • Open Meshing and change the settings of Mesh to match the settings below (except for Statistics):

705-03 705-04

  • The statistics should be checked, as mentioned, each time the mesh generated.
  • For 2D mesh, an orthogonal quality above 0.4 is preferred, but using inflation will most likely result in lower OQ, which is acceptable.
  • RCLK on Mesh > Insert > Sizing
Scoping Scoping Method Geometry Selection
Geometry Select the main edge of the airfoil. (excluding the trailing edge)
Definition Type Number of Divisions

You can also use Element Size.

Number of Divisions 900

Adjust number of divisions as needed.

Behavior Soft
Bias Type _____  ___  _  ___  _____

This is to have smaller sizing near the trailing edge in order to improve orthogonal quality. Adjust according to the geometry.

Bias Option Bias Factor
Bias Factor 35

Adjust bias factor as needed.

  • RCLK on Mesh > Insert > Sizing
Scoping Scoping Method Geometry Selection
Geometry Select the trailing edge of the airfoil.
Definition Type Number of Divisions

Or you can use Element Size and use a size that is about half the height of the trailing edge.

Number of Divisions 2
Behavior Hard
Bias Type No Bias
  • RCLK on Mesh > Insert > Inflation
Scoping Scoping Method Geometry Selection
Geometry Select the main surface (do not select it as a body)
Definition Boundary Scoping Method Geometry Selection
Boundary Select the main edge (excluding the trailing edge) of the airfoil
Inflation Option First Layer Thickness

Choose appropriate option depending on the situation.

First Layer Height .1 mm

This was the desired first cell height calculated for an Re of 3000000. Calculate and use an appropriate height, or use another method.

Maximum Layers 20
  • (Optional)
    • RCLK on Coordinate Systems > Insert > Coordinate System
Origin Define By Global Coordinates
Origin X 1500 mm

Select appropriate coordinates so that the sphere of influence is slightly to the right of the trailing edge.

Origin Y 0
Origin Z 0


  • Mesh > Insert > Body Sizing
Scoping Scoping Method Geometry Selection
Geometry Select the main body (do not select it as a surface)
Definition Type Sphere of Influence
Sphere Center Coordinate System

Or select the coordinate system created in the step above.

Sphere Radius 2000 mm

This can be altered as needed.

Element Size 40 mm

This can be altered as needed. You can change this to do mesh independence study as well.

  • Creating Named Selections
    • Select the edges that form the airfoil
      • RCLK on the graphics window > Create Named Selections
      • Name it “wing”
    • Do the same for the edges for the inlet and outlet as shown:

Example of how it should look: