Berkcan Öztürk

Hello, I am trying to analyse NACA 2314 profile and my purpose is to find the Cm values over the chord line. But the problem is I cannot do a direct analysis. Here is a list what I do in order: 1- I select the Direct Foil Design and enter 4-digits as 2314. 2- I repanel the airfoil (I use 100-150 panels). 3-I define an analysis with Re=500,000+ 4- I click the 'XFoil Direct Analysis' and do an analysis with changing AoA values from -5 to 20 (sometimes narrowing it down.) The problem is I cannot see...

Oh, thank you very very much! I changed that setting earlier but nothing changed. I did not know I had to re analysis the airfoil. Now, it is fine thank you again. Happy new year!

Hello, I am trying to use XFLR5 for my class project. I need to do a simple airfoil analysis. I watched some tutorial videos and read the manuals there is no problem there. But when I do the Batch Analysis with different Re#, the program shows me every curve in only one color. Like I do an analysis with Re# from 500,000 to 1,000,000 but I can't distinguish which one is which. I have added a screenshot of my result graphs. There may be a simple option but I couldn't find it. Any help will be appreciated....