ESDU Challenge: Fighter Aircraft Wing Design

It seem like it should pitch down at high angles of attack.

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As the flow detaches at the root of the wing, the resulting vorticity down the sweep of the wing should help flow stay attached further aft. With lift reduced on the forward portion but maintained at the rear, it seems likely to exhibit pitch down behavior.

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If it isn't already apparent, this is not a field in which I am well versed, so this isn't much above a WAG on my part. I am interested to see if intuition is helpful or misleading here.

Not my field at all. My thinking though, is that at a high angle of attack the wing is at a steep angle to the air and lift is almost all due to ram pressure on the bottom of the wing. With a sweep back, the larger surface area at the rear means the rear of the wing will have more pressure on it than the front, thereby generating a pitch-down force (torque).

[And I have a feeling that aircraft designers will laugh at my explanation!]

Pitch down as the lift is greater on the trailing edge of the wing.

I would hope pitch down, for stability.