negative drag coeffient
hello every one
I am studying a supercritical airfoil with fluent. and for mach 0.5 flow I obtained a negative drag coefficient, this ic completely wrong. I used the same way of meshing and defining boundary conditions as in the tutorial. I only change the airfoil. do you know how can I face this problem?
|All times are GMT -4. The time now is 04:40.|