X-Mozilla-Keys:                                                                                 
Jeff Spitzer wrote:

Ed Anderson wrote:

 Jeff,
     I use -16 Stainless steel braided hose on the water pump.  At least on
the 88 NA model the inside of the intake nozzel of the water pump will take
a -16 AN or JIC tap.  I tapped the inside of the intake nozzel and

screwed a

male/male -16 adapter into the hole and had the external end to screw on

the

hose fitting.  I got a Ford thermostat housing out of Earl's Performance
catalog which has a male -16 fitting.  The size and bolt holes match up

with

the two bolt 13B thermostat housing and viola -16 AN fittings on each

end of

the water pump.
    Since the iron pump is replaceable, the aluminum pump casting of

course can

be used indefinetly. If you  proceed with offering modified water pumps

then

you might consider offering the tapping of the water pump inlet as a

service

for those that might want it.

Ed Anderson
Matthews NC

I think perhaps the best service that could come from all this is a pump
characteristic and engine characteristic.  Then you or anyone else need
simply install pressure taps in the pump housing at inlet and outlet to
know coolant flow of the entire system.  For any pressure differential and
RPM one can get flow.  For this flow, the pressure differential across the
engine will be known (less manufacturing tolerances)  The remainder is
pressure drop of the rest of the system.  I expect that a significant
portion of the "cooling problems" of the past and present are simply
restrictive systems.  If you don't want to fix the system then you install
a better pump.  

I'll say it again: AN-16 is not big enough for 40 GPM
unless you have almost no length and few fittings.  The 30 GPM number that
PL just cited from racing beat is probably for a stock installation with
1.5" hose (and no fittings).  Your flow *will* be less.  I would not accept
anything less than 40 GPM for my plane because I prefer to use a small,
efficient radiator.  I actually have the goal of zero cooling drag.  I'll
know if I actually get it when I instrument the airflow system in flight.

Jeff Spitzer

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