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Clarification on Reference Frames for Blade Forces
Hi,
I have a couple of questions regarding the reference frames used to compute the forces acting on the blade:
Are the tangential and normal forces output by the simulation assumed to act at the quarter-chord point or at the aerodynamic centre of the blade section?
Are the lift and drag coefficients reported along the blade aligned with the aero coord system defined for each panel/spanwise station?
Thank you in advance!
