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
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Paul,

Thank you very much for putting up with all of my questions and offering all
of your advice. I certainly couldn't have done it without you.

Now, I'm going to mock it up and then it's off to the welder.

Thanks, Sandy