Quote:
Originally Posted by Broncazonk
So yes, this does make sense! (It took a couple of days for me to understand what you were saying.) The downward twist of the wing arrives at -3 degrees at flap-aileron junction, and then the twist was maintained at a constant -3 degrees throughout the aileron section to the tips.
Not likely. If the Ta 152 wing followed the Fw 190 and 190D philosophy, the angle of the airfoil chord relative to the vehicle axis at the root was a Positive 3 degrees, then twisting negatively spanwise from there
Interesting.
I wonder what the gradient of the twist was?
Thanks!!
Bronc
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Constant, linear decrease from root incidence of 3 degrees to zero. Again, if similar to FW 190 series, the twist would reach 80% semi span to reach zero.
The purpose of the twist is to control the spanwise lift distribution and stall characteristics.