okay, i'm going to try to convey my thoughts via pictures, not that any of you folks have got the wrong idea, just for clairification:
the top one is supposed to represent circulation theory.
The purple lines are supposed to represent a body flow away from the fuselage that my be negligible but still happens.
the next two are my guesses at ground effect; which depends, i do not know about the inboard induced flow, does it actually bother to travel all the way to the end or does just the difference in pressure nearest to the tip bother to spill over?
In the mid pix, would that not represent a path of skewed circulation? Now that I look at it more, it looks like it could have a heck of a lot of sidewash
, like if you were standing there it would knock you right down.
In the last pix, would that not represent a downwash reflection of the circulation?
In terms of zero vortex, image that the tip flow was cut off, wouldn't that mean that the circulation would simply go straight down by then? Again, if and only if a zero vortex occured there.
: >> "Q1: No finite wing could eliminate trailing vorticity.
I could prove you absolutely wrong with a simple phrase: "sonic waverider and compression lift". consider that the shock wave closes in on the leading edge and prevents the induce flow from spilling over -- hence elliminating the trailing vortex -- providing lots of lift that would normally be lost due to vortices.
[Edited 2004-04-05 22:55:22]
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