I'm new to Maple Flow. As an exercise I'm replicating a calculation I did in Mathcad, building a blade element model of a hovering helicopter. The physics is well documented, but any specific design changes the results.
The lift and drag values of the airfoil of choice and the blade physical geometry are used to solve for the forces generated at any radial segment, these are integrated along the blade radius to compute the rotor thrust and torque. These integrals are taking an inordinate amount of time--one blade angle setting took fifteen minutes to compute rotor thrust and torque. Since the next step is to compute these values over a range of blade angles this poses a significant problem.
I'd post the file if I could figure out how!!