Hi,

I ma trying to calculate the lift and drag coefficient for a NACA0012 at different angles of attack. I have run and post processed the results which look great. But I am unable to figure out what variables to use to calculate the lift and drag forces. Any help in this regards would be highly appreciated.

Hello,

Just take the function calculator and calculate the force in the direction you want.

Regards

you can get the lift and drag force in the solver, and then use the function to get the coefficient

Hi,

cl is propotional angle of attack ( up to stall) cl is propotional to shape and size of wings

cd is increasing very fast after stall.

cl is maximum at an angle just before stall. cd is minimum at an angle just before stall.

ratio of cl/cd is highest near stall. induced drag creats lift upto stall angle. induced drag becomes profile drag after stall angle.

J.B.Patel mechanical engineer.