Paul,

Here's my latest cooling version. I think it has all the changes you
recommended (see 2 & 1qtr inch horizontal fold radiators in parallel
(Large).jpg and 2 & 1qtr inch horizontal fold radiators in parallel
- Plumbing (Large).jpg attached)


Q1: I've used the same size hoses for water cooling that Mazda uses. Is
there any good purpose for a larger size?

Q2: We haven't talked about oil lines. Are 3/4" braided stainless steel
lines OK?

Q3: Is a diffuser wall necessary between the oil coolers and the water
HX, or just all open? (the blue colored wall in 2 & 1qtr inch horizontal
fold radiators in parallel - Diffuser (Large).jpg)


As usual, I appreciate all comments and concerns

If you like this, then I'm moving along to fabrication.

Thanks for your help.

Sandy McNabb
Renesis in a Glass Goose

That is looking good. You are getting good at 3D dwgs.

Q1: Thats fine. No significant advantage to larger hoses.
The water pump HP is below 3 HP.

Q2: 3/4 ID? If so that is OK.

Q3: A wall would give you the option of a minor adjustment
in the ratio of oil to water cooling. On the other hand
a slight loss of over all air flow would occur. I can't say exactly
how much without a good CFD.


Paul Lamar

There is one point I need to make about this drawing. It is
hard to say exactly that this configuration is 154% better than the RX8.
One cannot go on radiator volume alone.
The RX8 rad has larger radiator frontal area and  a thinner core
going for it. That is a more efficient core. It could cool better
at 100 MPH than this system as it is easier for the air to flow
through a thinner core. Properly ducted the RX8 core most certainly would
have lower cooling drag. However, the Glass Goose is not the lowest
drag airplane out there so a given amount of cooling drag may be less
important in the over all drag. Your options are limited here.
A thin four unit folded water core is not possible under the given cost and
manufacturing limitations. The bottom line is; the airplane must cool
on take off and climb out or it is not a viable airplane so cooling
drag is secondary. Never the less I think what you have here is going to
work OK.

Paul Lamar