The airfoil was designed for the VK-30 but was tested on a cessna 210, its true the Reynolds number is higher, but in the Reynolds number range from R=1.000,000 to R=12.000,000 the results between a turbulent flow airfoil (RAF48) and the laminar flow airfoils (NLF 10414F) and AS5048 would be similar. You have 40counts of drag for the AS5048 at the design lift-coefficient and 50 counts of for the RAF48 this is a 20% reduction and many aerodynautical engineers would die for a reduction like that so you guys diden't waste any money.
Jim On Tue, 09 Nov 2004 13:34:35 -0500 "Dana Overall" <bo12...@hotmail.com> writes: > >From: JAMES FERRIS <mij...@juno.com> > > > >John: these airfoils would work on the KR1 as well as the Kr2 but > there > >iann even better that has laminar flo > > > Jim, > > The big questions are, was that NASA airfoil designed with the KR in > mind > and was that airfoil wind tunnel tested per KR flight envelope? > > We who donated to the research and wind tunnel funding along with > designers > would like to > know the answers to those two questions:-).............could be we > wasted > our time and money > > > > Dana Overall > 1999 & 2000 National KR Gathering host > Richmond, KY i39 > RV-7 slider, Imron black, "Black Magic" > Finish kit > 13B Rotary. Hangar flying my Dynon. > http://rvflying.tripod.com/aero1.jpg > http://rvflying.tripod.com/aero3.jpg > http://rvflying.tripod.com/blackrudder.jpg > do not archive > > > > _______________________________________ > to UNsubscribe from KRnet, send a message to krnet-le...@mylist.net > please see other KRnet info at http://www.krnet.org/info.html > >
