|Apr11-12, 10:56 AM||#1|
Circulation around a plane wing.
After looking into the lift force i hve been able to calculate most of the things i know. I have however been told that i need to use circulation and vorticity to show that the air flows faster over the wing than below it. I need to show this mathematically by derviving an equation but i am unsure where to start.
Would anbody be able to help without making things too complicated
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|Apr11-12, 11:29 AM||#2|
There isn't some magic equation to use. There is basically no simple way to do it. For a slow (M<0.3) airfoil, the easiest way to determine circulation is probably using a simple inviscid panel method code and enforcing the Kutta condition. That will give you a circulation value.
For faster flows, compressibility becomes important and the problem becomes more difficult. Once you reach the point of having a supersonic leading edge, circulation is no longer the important factor and you can determine lift from the series of shocks and expansions and the resulting pressure fields.
|Apr15-12, 12:34 PM||#3|
I have been told to use the following resource
I was able to show that for a faster speed the pressure is less using bernoulli principle. I now need to show that the speed is greater above the wing. WOuld anyone be able to explain how the link shows this in more simpler terms
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