I need some information and guidance on how to calculate net lift and thrust produced by wings of an MAV(micro air vehicle) which are flapping and active pitching.(adsbygoogle = window.adsbygoogle || []).push({});

I know only about one method which is the Blade Element Analysis, but it is just an approximation and doesn't accounts for pitching. Other methods are experimental testing but I don't want to go for it. I want to create a formulation of the design first and then make a prototype and for that I need to know about the lift and thrust generated by wings of 15cm span and inverse zimmerman planform.

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# Aerospace Calculation of lift and thrust

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