C Grid Mesh for Aerofoil Analysis
 

Hey guys,


I'm attempting to analyse a NACA0009 aerofoil, my end goal is to determine lift and drag coefficients for a range of AOA.


So far I have made a 2d unstructured c-grid mesh (using ICEM) and have imported it into Fluent. However, when attempting to solve I get the following error.




https://www.cfd-online.com/Forums/da...BJRU5ErkJgggA="pressure-far-field boundary conditions can only be used with ideal gases"
https://www.cfd-online.com/Forums/da...BJRU5ErkJgggA=

Attempting to fix the error, all I can find on google is setting the working fluid to an ideal gas, which I have done without any luck.


I'd appreciate any assistance.