
#1
Apr1112, 10:56 AM

P: 12

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 



#2
Apr1112, 11:29 AM

P: 1,437

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. 



#3
Apr1512, 12:34 PM

P: 12

I have been told to use the following resource
http://books.google.co.uk/books?id=G...page&q&f=false 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 Thanks 


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