Originally Posted by Lyman
It would be interesting to imagine a wind tunnel with the forward ten metres of A330 fuselage mounted level and subjected to 200knots of airstream impacting the belly at 35 degrees AoA.
The airstream in windtunnels is horizontal (except in spin tunnels where it is vertical). You would need a relatively small airplane model to mount it at 35 degrees AoA without getting too close to the tunnel walls. What would you be interested in? I would be interested in the pressure near the static port, and in the pitching moment at various angles of elevator and THS. I take it that the noise registered on the CVR is generated by the flow separation on the wing. And why 200 kt? The airplane wasn't stalled until the speed was much less.
Though I'm curious about the cause of the 'zipper trace', I don't see any effect of it on the airplane. As the AB simulation shows, the airplane behavior is entirely consistent with the SS control input. There is no delay in the response in pitch attitude.