Streamflow and lift for Micro Aerial Vehicles?

AI Thread Summary
The discussion focuses on the challenges of analyzing streamflow and lift for Micro Aerial Vehicles (MAVs), highlighting that the flow around MAVs has low Reynolds Numbers, complicating the application of traditional aerodynamic equations. The complexities of the Navier-Stokes equations due to significant molecular viscosity make it difficult to simplify analyses for MAVs compared to larger aircraft. Engineers may rely on trial and error in design, as there are limited successful MAV models in operation. Additionally, the aerodynamics of MAVs do not scale well, presenting further design challenges. Overall, the conversation underscores the unique aerodynamic difficulties faced in the development of MAVs.
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What are the equations used to determine the streamflow and lift for Micro Aerial Vehicles?

What are the problems with MAVs?
 
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As far as I know analyzing flow over MAV's is more difficult than doing that in larger aircrafts. The flow around MAV's has Reynolds Numbers below 100.000 or so, which makes impossible simplify terms of N-S equations. Molecular viscosity forces might not be neglected.
 
So when engineers make MAVs, what do they rely on? Trial and Error?
 
I don't know, but I haven't seen too many MAV's flying over there.
 
Along the same lines, this just came out in one of the trade mags I get. It explains a bit of the issues of why aerodynamics don't scale well. We run into many of the same issues with our engines.

http://www.designnews.com/article/CA513570.html
 
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