Drag Force on Axisymmetric Cone in Mach 5 Flow
 

Hello all, I'm very new to Fluent, and for my thesis I am trying to calculate the drag force on a flared axisymmetric cone at zero AoA in hypersonic flow. I am unsure as to how to go about doing this. I have tried to compute a surface integral report of pressure coefficient, but I can't figure out how to get it to provide me with the axial force. I'm hoping somebody can help me with this. Thanks.