cm vs alpha graph of an airplane on ansys fluent
 

Hey everyone.
I have to find the cm (pitching moment coefficent) vs alpha graph of an airplane using ansys fluent. What is the aproach ı have to take to solve this problem.
Thanks already.

1. Build a grid of said aircraft
2. Set the angle of attacjk along with boundary conditions, freestream parameters and whatever else your flow solver needs.
3. Run the flow solver to generate a solution and compute the moment coefficient using the flow solution.
4. Plot the coefficient against that value of AOA.
5. Repeat steps 2-4 until you have generated a desired curve.


Now if you are looking for fluent specific knowledge, you might want to try the fluent specific forum.

Hey
I see. I thought there woulld be a faster way than making a new mesh every time but that can work too.
Thanks for your suggestion.

You do not have to make a new mesh for each AoA. Just make a suitable mesh and change the freestream velocity components for each simulation.

In Fluent there is the far-field boundary condition for this type of simulation. It's efficient to make a spherical (full-aircraft) or hemispherical (half-aircraft due to symmetry) computational domain.