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I want to compare different blade shapes and rotor designs in their lift force and torque by a specific rpm. For a calculation, I would need the lift coefficient, which i don't have for a self designed blade shape. How can I calculate this coefficient or have I to simulate this? And which software is recommended to simulate such kind of problem (the blades are designed in a CAD software)?

BTW: Is there any good source (books, online source,...) for aerodynamic formulas referring to rotors (helicopters), I didn't find something so far?

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The lift coefficient for a body, rotor blade in your case, must be measured in a wind tunnel. It will be a function of airspeed, angle of attack and the gas used (usually air). The mathematics required isn't particularly advanced (Newton's laws of interaction of the air molecules with the surface and with each other), but it is of little use because it requires following the history of the molecules of the gas. There are of the order of Avogadro's number of molecules. The fluid approximation is not warranted so normal fluid dynamics is of little help. This paper may help: arXiv:nlin/0507032.

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  • $\begingroup$ Another factor influencing lift is the wing shape itself. $\endgroup$ – Charles Crummer Sep 17 '16 at 7:31

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