I need help with my airfoil simulation

Francesco_C
Francesco_C Altair Community Member
in Community Q&A

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

cmesh.5.Log
volume.png
runmesh.png
refinement.png
boundary.png
run.png
time hystory.png
pressure.png
force.png
Cp.png
Cl Cd.png

Tagged:

Answers

  • acupro
    acupro
    Altair Employee

    In the image with the acuLiftDrag commands - both issuances are pointing to Run number 5. You indicated that run was for AOA = 0. If you want to get a value for AOA = 15, you'll need to make another run with the free stream velocity components set such that the resultant is at AOA = 15.0. Then you could run acuLiftDrag on that result/run. Note you also need to make sure you're using the correct/consistent density in acuLiftDrag, as the default is 1.225.

  • Francesco_C
    Francesco_C Altair Community Member
    https://community.altair.com/discussion/comment/187131#Comment_187131

    i solved my problem thanks to your comment

Categories