I'd like to know the right formula to calculate torque of a quadrotor propeller (propeller pitch is constant) due to aerodynamic drag in terms of angular velocity ω. For the sake of my simulation I'm assuming `APC 10x4,7` propellers. I'd like to refer to UIUC Propeller Data Site, so please assume only the set of data given there is available while answering. I know really little of aerodynamics, I'm planning to design a control system in Simulink later on, but would like to derive a non-linear mathematical model first.(adsbygoogle = window.adsbygoogle || []).push({});

Please note I need to use data from UIUC Propeller Data Site for APC 10x4,7, which means the propeller below. I'm guessing all is there to derive a formula τ(ω), I just don't understand how to do it.

http://img19.imageshack.us/img19/7838/apcsf10x47side.jpg [Broken]

http://img853.imageshack.us/img853/7319/apcsf10x47front.jpg [Broken]

http://img850.imageshack.us/img850/8931/apcsf10x47geom.png [Broken]

Static data from UIUC:

RPM CT CP

2377 0.1039 0.0431

2676 0.1058 0.0437

2947 0.1059 0.0437

3234 0.1083 0.0444

3494 0.1096 0.0450

3762 0.1121 0.0460

4029 0.1136 0.0466

4319 0.1155 0.0474

4590 0.1177 0.0484

4880 0.1199 0.0494

5147 0.1213 0.0500

5417 0.1228 0.0508

5715 0.1239 0.0513

5960 0.1253 0.0520

6226 0.1261 0.0524

6528 0.1274 0.0531

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# How to calculate quadrotor propeller torque due to aerodynamic drag

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