why do the aerodynamic results not change after setting flap? they're same as no flap. and I found out that panels didn't change after setting flap. How can I set up new panels with flap?
Hi, how to adjust the trailing edge thickness ? I read online that you have to use the command TGAP from GDES. I wanted to change the thickness to 20% of the chordlength.
Yes, it is possible to export the airfoil geometry out of XFOIL as a set of points and then import the points into ICEM CFD. After step seven in this video (where you moved the finished airfoil from the buffer airfoil memory to the current airfoil memory), you will want to go from the GDES menu to the top level menu by hitting enter. At the top level menu, you will want to save away the x and y coordinate points into a .txt file using the PSAV command (PSAV filename.txt). Open the file in notepad, add to the file the first line that contains the number of points in each curve and the number of curves (335 1). Add a space and then a zero after every x/y coordinate pair (the airfoil will be imported onto a plane) and save the file. In ICEM CFD, import the saved file (File > Import Geometry > Formatted Data Point > Select file in folder browser). Now you have the airfoil shape imported into ICEM CFD.
It should. This command is not NACA specific so it should work on all airfoils. A good portion of UIUC airfoils need to be reformatted before being put into XFOIL (I made a video on how to do this called XFOIL Tutorial 3: Loading an Airfoil from a File. Its located here: ruclips.net/video/g-SnoYE4yYk/видео.html ) or they can cause issues. Which airfoil are you having trouble with and what are the flap parameters you are using? I will see if it gives me problems too.
I have finished watching all your videos and found it to be personally quite helpful! Keep up the good work!
Thank you! I'm glad they are helpful. We are just entering the intermediate level videos so stay tuned. Lots of good things to come.
Thanks a lot! This method of using XFOIL is way more easier & faster than using ANSYS Fluent!!!
Good to hear!
Thank you very much! Your tutorials are extremely helpful.
Glad to hear that!
That was a wonderful video. I wanna know can a tandem wing configuration be analysed with XFOIL ? TIA
why do the aerodynamic results not change after setting flap? they're same as no flap.
and I found out that panels didn't change after setting flap. How can I set up new panels with flap?
Hi, how to adjust the trailing edge thickness ? I read online that you have to use the command TGAP from GDES. I wanted to change the thickness to 20% of the chordlength.
When are the next vidoes coming?
Is it possible to export this geometry to icem cfd??
Yes, it is possible to export the airfoil geometry out of XFOIL as a set of points and then import the points into ICEM CFD. After step seven in this video (where you moved the finished airfoil from the buffer airfoil memory to the current airfoil memory), you will want to go from the GDES menu to the top level menu by hitting enter. At the top level menu, you will want to save away the x and y coordinate points into a .txt file using the PSAV command (PSAV filename.txt). Open the file in notepad, add to the file the first line that contains the number of points in each curve and the number of curves (335 1). Add a space and then a zero after every x/y coordinate pair (the airfoil will be imported onto a plane) and save the file. In ICEM CFD, import the saved file (File > Import Geometry > Formatted Data Point > Select file in folder browser). Now you have the airfoil shape imported into ICEM CFD.
Does this work for UIUC airfoils? when i try this xfoil crashes
It should. This command is not NACA specific so it should work on all airfoils. A good portion of UIUC airfoils need to be reformatted before being put into XFOIL (I made a video on how to do this called XFOIL Tutorial 3: Loading an Airfoil from a File. Its located here: ruclips.net/video/g-SnoYE4yYk/видео.html ) or they can cause issues. Which airfoil are you having trouble with and what are the flap parameters you are using? I will see if it gives me problems too.