Buona sera Roberto,

 

Interesting theory about the contribution of lift hysteresis in the stall regime contributing to recovery difficulties. I wonder if NACA/NASA has performed any tests of this behavior using a full scale model?

 

After reviewing the various NACA 6-Series wing sections, it appears that many of the 12% thickness airfoils exhibit similar characteristics. In many cases, this behavior goes away with thicker sections. Alternatively, a slight reprofiling of the wingtip using a 65212 wing section would eliminate this tendency as well, although at the cost of a slightly sharper stall. The sharper stall characteristics can be tamed somewhat by a more generous leading edge radius.

 

Roberto points out yet another reason to consider installing an AOA device in our experimental aircraft. I just wish I could install one in my T210 without an act of congress!

 

Best Regards,

Mike