Washout built into the wings of the Ta-152H

[Broncazonk]

I was hoping you would join the discussion.

Thus, for clarity, is the following a reasonable supposition?

"The Ta-152H incorporated a +3 degree angle of incidence at the wing root with a constant washout to the flap-aileron junction, at which point the angle of incidence was zero, with no further twist in the span along the ailerons."

Bronc

[stephen f. polyak]

Running the numbers above with wing dimensions resulted in…

Ta152: 3 deg washout (constant, linear) from wing root to aileron junction (~ 60 % semi-span) equates to ~ 0.23 deg/ft negative twist

Fw190: 2 deg washout (constant, linear) from wing root to 80 % semi-span (note, washout runs past aileron junction) equates to ~ 0.17 deg/ft negative twist

Elsewhere online I found these values...

Spitfire: 2 deg positive for ~ .2 span, then start constant washout to the tip for approx zero incidence at the tip.

Fw190: 2 deg positive at root, then 2 deg washout from root to .85 span, then zero for remainining .15 span to approx zero incidence at the tip.

P-51B: ~ 0 deg at root increasing along strake 1 deg (positive) to about .18 span, then constant 1 deg washout to tip resulting in zero deg at tip.

P-51D: ~.2 deg at root increasing to 1 deg (positive) at strake/wing intersection at ~ . 2 span, then 1 deg negative until zero deg tip.