Fokker DVIII stability
I have a drawing of a DVIII which seems to indicate that the horizontal stabilizer had a positive angle of attack. Is that accurate?
While the cambered airfoil should have a nose down pitching moment the positive lift on the tailplane would only add to this moment. The large, low landing gear and low "sub wing" would also only add to this nose down pitching moment. Did the DVIII have such an aft center of gravity that the horizontal stabilizer had to produce lift to balance the airplane in flight? I imagine that the large, delta tailplane could produce a lot of lift if necessary.
This seems, however, like a formula for pitch instability.
What was the actual situation for these planes?