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To Jim Solensky,

Sorry to hear about your cooling system woes.  You might want to take a
look at a page on the web that shows the typical pressure gradients around
the cowl on airplanes that look like ours... it shows that the location you
have chosen may actually be in a relatively stagnant area of pressure.  Go
to http://www.inforamp.net/~raac/CoolingSystems/Part4/CoolingSystems4.HTML
and check out the picture about 2/3 of the way down the page, you might
find it interesting.  That entire series of pages (just change the number
at the end of the .HTML tag, it goes from 1-4) is pretty interesting
reading, while it deals with liquid cooling systems primarily, there is
still a ton of info about where to find good flow and where to find the
other kind.  Anyway, that might be the problem you're facing, and maybe
you'll find a solution buried somewhere among those pages.  

There was a discussion over on AVSIG not long ago about this very thing
vis-a-vis a Glasair III, the solution was to install the NACA scoop well
forward on the cowl, and install a louvered exit aft of the oil cooler,
building the entire oil cooling system into its own little plenum, both
front and rear.  I understand the guy's temps dropped almost 30 degrees
throughout the entire flight regime.

How's your CG coming along... did the ring up front make a difference?
Stay in touch.

   <Marv>