I need help with my airfoil simulation
Hi guys, so im trying to simulate the diffeences between the same profile (intact vs impacted but not with a hole) at different Angles of attack
I'll attach all the pictures of mesh and run parameters +log.
Some ppl before told me to get a even finer mesh so i runned this imulation that took me 8 hours (i think is too much considering my i9-14900K + 64gb ram)
anyway my results are strange u can see a pressure/x plot obtained from the intersection curve that gives anything like a Cp plot.
I put my log in acusolve prompt for the aculiftdrag do you think that those values are correct? why if i modify the "-aoa" parameter to 15 deg my Cl gets lower than before, shouldent it be higher?
Anyway guys can you take a look at the log/setup and give me some advice to have less running time but also accurate results.
Thank you all for your time.
This log is at zero degrees with freestream vel of 108.611 m/s
