Airfoil Modification in SpaceClaim
 

I'm fairly new to ANSYS Fluent and am using the 2021 Student version.

I am trying to put a rounded edge on the trailing edge of an airfoil (attached picture). Here's what I've tried so far:

1. Used the equation for the airfoil (attached image of the equation) (https://nasa.fandom.com/wiki/NACA_airfoil) to generate x y coordinates in Excel. Output those to AutoCAD and created a polyline. Added a fillet to the end and then imported a .dxf file from AutoCAD to SpaceClaim. Used the Fill command on the .dxf file. I now have a modified airfoil like I want, but when I got to mesh, all of the individual plot points have created separate edges. When I go to select the airfoil geometry, it registers 801 edges. How can I join these edges together so that they're all one?

2. SpaceClaim>Design>Sketch>Equation>Custom I am trying to define a curve for the airfoil using the custom function. I used the following function and it displays a straight line (attached picture).

5*[chord]*[thickness](0.2969Sqrt([t]/[chord])-0.126([t]/[chord])-0.3516*Pow([t]/[chord],2)+0.2843*Pow([t]/[chord],3)-0.1036*Pow([t]/[chord],4))

This corresponds to the equation from NASA's website linked above.

Any help is appreciated.

If you have already created the x,y coordinates in Excel, simply create a *.txt file containing the x,y values and import this directly into SpaceClaim. Look up Point curve text in the file import area of the SC Help documentation, which describes the data format and optional commands to be included in the file. You can then view and edit the curve in the Design tab, with Sketch mode, using the Pull and Move tools to modify the trailing edge.

Thanks, I will try this.

In the meantime, I was able to find a workaround. I created the airfoil in SolidWorks and saved it as a .STEP file. I then imported it into DesignModeler. I created my fluid domain and created a Boolean>Subtract where I was able to subtract the 3D airfoil from my fluid domain. I was left with the desired result, although the method mentioned above is probably the right way to do this.