On 3/7/2011 7:24 AM, Mike the Strike wrote:


We have discussed this many times before. The nose-up attitude of the
glider results in extra forces that have to be overcome by the wings
and tail surfaces. In particular, modern standard-class ships with a
low angle of incidence of the wing have a pronounced nose-up attitude
that results in loss of control at speeds well above free-flight stall
speed.

I'm having trouble picturing the influence of a low angle of incidence
of the wing (I assume that's compared to the fuselage) on loss of
control. Why would the wing be affected by the fuselage attitude being a
few degrees higher, relative to the air, than on an older glider?

--
Eric Greenwell - Washington State, USA (change ".netto" to ".us" to
email me)