At 07:39 AM 8/19/2016, you wrote: >Larry Flesner and I have seen wings where the spar broke on impact with >the ground at the bottom of a spin, and the spar broke a few inches from >the WAF, not at the WAF or the connections from WAF to spars. +++++++++++++++++++++++++++++++++++++++++++++++++++++++++
Here is a photo https://dl.dropboxusercontent.com/u/32133949/100_1497.JPG of what remained of a KR after a stall / spin (fatal) accident. All wing attach fittings were intact and none separated from the spar wood. The plans state that the "designed load factor" is 7 G's at 800 pounds. That is 5600 pounds. At 1200 pounds the "designed load factor" would be 4.666 G's ( 5600 / 1200 = 4.666 ) , a healthy number for non-aerobatic flying. As our KR's get heavier and heavier the load factor goes down as well as performance. An 800 pound E.W. KR with a VW is certainly not going to perform like a 600 pound E.W. KR with a Corvair or 0-200 engine. Ken's KR weighed 480 pounds empty and I doubt there has ever been another KR built to that spec. Many KR's are coming in at 700+ pounds with several going 800+. You will need 30 to 50 more horse power over a VW to make these birds perform to moderate standards. Performance is directly related to weight / horsepower. Just saying................ Larry Flesner
