Bulent Aliev wrote:

Paul wrote:

Bulent Aliev wrote:

The radiator is 6"x21" Griffin. Engine GM 4.3 litter V6 200 hp. There is
a long article on it in Contact magazine issue 48

I think this is the same one I saw at OSH a couple of years ago.
It is a Canadian aircraft as I recall. the owner said he thought
it had a lot of drag. Do you recall how thick the rad is?

You are right again: it's the same plane.
The first radiator was a 18"x 19" frontal cooling area and had double one
inch core, but had excess of cooling capacity. The second one was 6"x21" with
two rows of 1 1/2" cores  and 2" tanks at both ends. The coolant inlet and
outlets are 1 1/2" and 1 3/4" in diam. respectively.
The front of the scoop is angled at 35-35 degrees.
Bulent

On additional thought from the looks of the front picture not enough 
attention was payed to the contours of the internal diffuser. The 
outside of the scoop looks great however.

Here is a picture of the exit flap. This too is also very well done
but the over all result is one of the reasons I tried to get thin 
angled rads inside cowls to work to reduce the drag penality from 
this kind of installation.

Paul Lamar
 
The Aircraft Rotary Engine Newsletter.              Powered by Linux.

http://home.earthlink.net/~rotaryeng/            http://www.linux.org