Supposed I do a cfd analysis. I've got the pressure and velocity near the airfoil surface. I do some numerical integration/differentiation to get the lift/drag. I've managed to get it w/o problems.

However what about the moment & its coefficient?

How is it calculated?

Also if the airfoil is pitching up & down in a sinusodial motion at e.g. 0.3 chord length, is there any modification required?

Thank you.

please the details about how to calculate moment and its coefficient. Also, list the variable which is related to the calculation. Please includes the plot of moment coefficient versus angle of attack.