The 'Great Debate' - Spitfire vs BF109

[Crumpp]

No when the boundary layer separates the center of lift moves aft and flow on the undeside of the wing is allowed to curl up over the trailing edge, this simly causes turbulence behind the wing.

Not sure what you mean here. The aerodynamic center does not change with AoA.

The Center of Pressure moves forward with increased angle of attack and disapates at the stall.

Is that what you mean? The CP moves forward, the AC is stationary and when the CP is gone, down the wing comes about the AC.

Cause otherwise you have it backwards, the CP moves backwards in infinity as we approach zero lift AoA.

One of the reason's why CP is obsolete.

Light buffet comes from the separation but for most aircraft the significant stall buffet is from the turbulent air impinging on the tailplane.

Washout is what prevents the tips of the wing stalling before the inboard.

All true. Some airplanes the turbulence is the predominate factor. As a general rule though, it is the buffet.

In fact, it is really not good design to put the tail in the wings wake. It can lead to an unrecoverable stall condition. That is the big issue with T-tails.

Near the stall incidence, in most airplanes, the tail by design is in clean air.

I have never heard of an increase in drag inceasing lift

Well it is the co-efficients not the forces. In level flight we are lucky our lift force remains constant.

The co-efficients have a direct relationship. So as the airplane's co-efficient of lift increases, the co-efficient of drag increases.

Drag, unlike lift does not remain constant. So when our CL increases lift force stays the same but our drag force goes up.