Learning Forum

[MTayyab]

Hi,

i am trying to do a flow over an airfoil simulation at different angles of attack.

I have created the mesh, and for the inlet velocity at different angles of attack i input the correct velocity components my domain is c type domain but when i calculate the lift and drag coefficients i get very small values.

My free stream velocity is 210m/s and at 4 deg angle of attack i get the following values:

cd:

[Rob]

Have a look in help as there's a video going through the NACA airfoil set up. Errors in the lift and drag are often caused by poor mesh, incorrect reference values or Force monitor vectors. n

[Federico2594]

Try to use the K-W SST model that is better for Airfoil Study.nIs important to keep the correct value of y+ to solve correctly the bundary layer.nRegards,nnFedericon