Another Delta builder has done some testing and come back to me with some hard data for the pressure differential between the wheel wells and the wing's trailing edge.  A mamometer with a line terminated in both places gave:
- 1/16" differential during taxi
- 1.25" takeoff/touchdown
- 1" during climb out (100 mph IAS)
- 2.25" with the gear down
- 2" during base and final

I sure someone has, but I don't remember anyone quoting the pressure differential across their radiators.  Do these numbers look workable?  The airplane doesn't have a scoop dropping down as tested, and the front edge of the wheel well is squared off.  I would expect these modifications to significantly increase the numbers, but if this is sufficient neither one may be necessary.

These numbers are not from a duct with air passing through it, but just points on the solid surface of the aircraft.  Will that make a huge difference?

--
        ,|"|"|,                                    |
----===<{{(oQo)}}>===----        Dyke Delta         |
       o|  d  |o          www.ernest.isa-geek.org  |