[puck1]

I need to perform calculations of the forces and moments acting on a wing using the computational package OpenFOAM. The wing moves with a sideslip angle and is vertically oriented. The inclination is carried out along a line rotated 30 degrees to the vector of the oncoming flow. The angle of attack of the wing is given in the figure. The inclination angle in the vertical plane varies from -10 to +20 degrees. It is necessary to find the longitudinal and transverse components of force and moment, relative to the vertical axis passing through the lower point of rotation of the wing. Two variants should be considered in the calculation: a flat plate and a curved wing, bent according to the NACA0010 profile.

Could you help me with her solution? I will be very grateful for your help.