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rb1957 - I don't know but my questions are. IRstuff - Lift as far as I can see arises due to the stagnation point on the lower surface of the wing and the curvature of the wing downwards, from momentum conservation there must be a resulting net upwards force. This is about the most qualitative...

But then on the application to a wing (the image above can be assumed to be the upper surface) NASA gives: from: https://www.grc.nasa.gov/www/k-12/airplane/wrong3.html "The part of the theory about Bernoulli's equation and a difference in pressure existing across the airfoil is correct. In...

This is correct btrueblood, but what is the reason for the adverse pressure gradient in the first place? perhaps a better image for my quesiton is this: Why is point (4) adverse?, the flow is recirculating due to the pressure gradient, but why does downward curvature result in an adverse...

Many thanks for the reply, For the flow regieme pictured I believe the flow is incompressible, I guess the confusing part is the low pressure on the rear of the circle. Via Bernoulli this would translate to a high velocity, but in reality it is seperated flow: Is it that Bernoulli cannot be...

Hi all, I have a simple quesiton on the pressure distribution over an aerofoil but I can't seem to conceptually visualise it. I am starting to convince myself of the flow over a circle such as the image below: The stagnation point is a region of obvious high pressure (Cp = 1.0) and zero...