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pacgcrosss

I am involved in a research project regarding electric aircraft. I've done a fair bit of research into this but am having trouble keeping all the different parameters and how they affect each other straight in my head.

Fundamentally I am putting together a model whose parameters I can tweak and iterate through to optimize range, etc. For me, my problem boils down to how much power I need the battery to provide to maintain the thrust required for steady state (cruise) flight.

I've used actuator disk theory to relate thrust to power using this formula (second to last formula of 11.7.3): http://web.mit.edu/16.unified/www/FALL/thermodynamics/notes/node86.html

However (and please correct me if I'm wrong) the power in that equation is not exactly the power provided by the battery. To get that I'd need the propulsive efficiency, which includes many variables that aren't relevant to my model (blade pitch, etc.).

Would I be better off using blade element theory? I tried this, and was able to determine thrust in terms of RPM. How can I relate power required from the battery to RPM within the framework of this theory? I know this must depend on many factors such as air density, blade geometry.

Thank you in advance for helping me clear this up in my head.

Pac