Problem in giving condition for Coefficient of Lift/Drag for a airfoil.
 

Dear all,

I am facing issues while simulating a airfoil for angle of attack of 10 degrees. To achieve that i have made the airfoil geometry horizontal and am giving different component values (x,y,z) for velocity to achieve the desired angle of attack. Now in Star CCM reports for the direction of Coefficient of Lift/Drag should i gave the Sin/Cos of the angle or just simply 1. I have tried both but i am not getting acceptable results. Please guide me through the situation. Thanks in advance