I need to verify the fuel flow rate on my KR-2. The VW 2180 would burn about 6 gallons per hour full throttle 3600 RPM, full rich, max climb rate at 14 degrees AOA. FAA says there must be a 50 percent safety factor. So, need to verify 9 gallon per hour fuel flow. I cannot just fly to see if the aircraft will not run out of fuel under these conditions because that would not demonstrate the safety factor and a couple of other things. Other considerations: All fuel is in the wings; have an engine driven mechanical fuel pump. Just windmilling with the starter won't get but a few hundred RPM. I can block up the aircraft on the ground for the 14-degree AOA. Yes, I know about the 2-minute max throttle de-rating. There are lots of references in the archives on flow testing and Facet pumps. I find nothing for on testing engine-driven fuel pumps or how the flow was actually measured. Any suggestions on how I can demonstrate a 9 gallon per hour fuel flow rate? (which, of course, the 2180 will never need)
Sid Wood Tri-gear KR-2 N6242 Mechanicsville, MD, USA
