Andy Ross writes:

 > The real reason for washout (or at least a better physical
 > explanation) is this: the washout that maintains the tips below
 > stall AoA keeps as much of the "stable" derivative as possible out
 > on the wing tips where the moment arm is long.  If the early stall
 > happens near the fuselage on a short moment arm, then the overall
 > behavior will still be stable, not divergent, even past the peak of
 > the "whole aircraft" lift curve.

I found it easier simply to picture different 2D sections of the wing
stalling at different times, but I can see how your explanation might
lead to a programmatic solution faster.

 > Cool.  I learned something this weekend.  A "snap roll" is a
 > physically well-defined thing: it is a roll executed in a
 > post-stall environment where the roll-moment-due-to-roll-rate
 > coefficient is divergent.

Isn't the snap roll usually uncoordinated?  I've never done aerobatics
myself.  If it is, then I wonder what the role of the uncoordination
is.

 > So anyway, YASim needs to model washout.  In principle, this should be
 > pretty easy.  Each wing segment (Surface object, as currently
 > implemented) gets its own orientation already.  We just need to decide
 > on a way to specify it to the solver.  Would a linear interpolation
 > between "base" and "tip" incidences work?  I don't know much about
 > washout design as implemented on typical aircraft.  A fancier
 > mechanism would allow you to specify washout as an interpolated curve
 > per-station curve along the span, but that sounds like it might be
 > overkill to me.  Does anyone have a preference?

Start linear -- the real-world is probably not predictable enough that
anyone would notice increased realism from an interpolated curve.

On a separate note, I make no claim to understand how flaps and
washout interact, but perhaps that's more obvious to others.


All the best,


David

-- 
David Megginson, [EMAIL PROTECTED], http://www.megginson.com/

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