Well, the new airfoil series, designed by Dr. Michael Selig and Dr. Ashok Gopalaratham with consulting assistance by Dr. Richard Mole and Mark Lougheed and many other contributors around the world was extensively modeled and then real time wind tunnel tested. I still have the thousands of e-mail posts from the Area 51 Skunk Works private e-mail list that the contributors from around the world used to communicate during the development of the new wing. There is little need to try and second guess anything about this wing. Real documented scientific test data exists.
Steve Eberhart Myron (Dan) Freeman wrote: > Hi Fred; > > >> I'm not sure I completely understand why at higher speeds >your wing >> angle of attack will be less. >> > > Yeah, I know what you mean. That's where this model is a big help because > you can see the results. As speed increases, so does lift. Therefore you > have to add down trim to stay level, but not much. I tried +2.5 degrees AOA > at the root and it makes the fuselage fly even more nose down at high speed. > If I were to set the AOA at 0 degrees at the root then the fuselage flies > more nose up (or level) at high speed but then it become too high at slow > speed when landing. So as Mark said +1.75 AOA with 3 degrees washout is the > best compromise I have observed with the AS-5046 root and AS-5045 tip > airfoil and having a 0 degree horizontal stabilizer. Flying at 150 mph at > low altitude (2500 ft)the fuselage is level. Flying at full throttle at > 10,500 ft it flies slightly nose down, I don't know how many degrees (maybe > 1.5 - 2.0) but if this flight model is anyway near correct then it's not > enough to be conserned about. So, I'm going to stick to the plans on this > one. > > Posted - Tuesday, 02/06/07 2:23 pm > Regards > Myron (Dan) Freeman > Indpls, Ind. 46203 USA > mfreem...@indy.rr.com > > > _______________________________________ > Search the KRnet Archives at http://www.maddyhome.com/krsrch/index.jsp > to UNsubscribe from KRnet, send a message to krnet-le...@mylist.net > please see other KRnet info at http://www.krnet.org/info.html > >
