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Aerodynamics vs pressure Gradient
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[QUOTE="boneh3ad, post: 5441722, member: 268837"] Well, the flow above your control surface isn't stagnated, for one. That flow is absolutely moving. Inside that separation bubble, there is a large amount of vorticity, so it actually likely to be moving quite a bit and very well may have a very low pressure, which would explain why the flow starts to bend up at the trailing edge like that. We can't really see what is occurring inside that separation bubble, so it is difficult to make any real conclusions, but it is even possible that the flow is locally moving upstream (relative to the free stream) in some locations, which would create a whole lot of shear and could also help bend the streamlines upward. Also, in a fire hose there is no reason for the stream to narrow like that. Generally speaking, with an incompressible jet, the outlet pressure is equal to the ambient pressure (atmospheric in this case). Also also, if the pressure below a wing is lower than on top, the plane would fall from the sky. It would have negative lift. Now, they could be lower in pressure in the image you linked because of the huge separation region, so the wing is quite likely to be stalled at that point, but in general you shouldn't see faster, lower-pressure flow underneath. In fact, based on the streamlines, I would guess this particular airfoil [I]is[/I] stalled and generating negative lift right now. In this case, I would say it is simply most likely that the pressure below is still higher than in the separated region but that the overall effective change in shape of the airfoil (which now incorporates effects of the separation bubble) has caused it to enter stall, so the streamlines don't angle downward anymore like they normally would leaving the trailing edge. [/QUOTE]
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Aerodynamics vs pressure Gradient
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