Had I started from scratch and knew what I do now, I would have done the solid wing also. Stronger, less weight and cheaper. Just need the room to build it. ----- Original Message ----- From: "Doug Rupert" <[email protected]> To: "'Orma Robbins'" <[email protected]>; "'KRnet'" <[email protected]> Sent: Wednesday, April 07, 2004 7:42 PM Subject: RE: KR> !!
> Another way around this problem, for those that have the room required for > such a structure is to build the wing as a single structure, wing tip to > wing tip, thereby eliminating the WAF's altogether. This is the way Marcel > Jurca designed the wing structure for his 75% Spitfire replica and it has > proved a very strong structure. Personally, I would try this on my personal > KR before actually endorsing the practice but plan on exactly that as well > as keeping a very detailed record as to time involved and overall weight. I > also like the idea of being able to keep all fuel in the wings and out of > the cockpit for obvious reasons. Will keep you updated as construction > begins. > Doug Rupert > Simcoe Ontario. > > -----Original Message----- > From: [email protected] [mailto:[email protected]] On Behalf > Of Orma Robbins > Sent: Wednesday, April 07, 2004 8:21 PM > To: KRnet > Subject: Re: KR> !! > > The spar pillar spacing > > I accidently deleted some of the threads about this subject, and like Mark, > I have no real engineering experiese in this area. I do remember that these > pillars have been called load distribution blocks. In a discussion long ago > it was mentioned that if the rigidity of the wing changed, then the stress > is changed(moved). It was said that care must be taken to ensure that the > stress load that would be taken up by the bending of the spar of a standard > wing is not somehow transferred to the WAF's by a wing that no longer bends > as it should as would be the case by changing the spacing of the load > distribution blocks or in some other way making the spar less flexable like > installing a large tank. My non expert opinion is that if the wing is less > flexible then the original design then the G loading of the wing should be > reduced. > > Orma L. Robbins Southfield MI > 19 Years flying KR-2 N110LR > http://www.aviation-mechanics.com > > > > > _______________________________________ > to UNsubscribe from KRnet, send a message to [email protected] > please see other KRnet info at http://www.krnet.org/info.html > >
