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I'm looking for someone who could explain how I can mathematically model airflow over an aerofoil using the "correct theory of lift" - Turning airflow.

I have tried several approaches but all fail because of one step... all text books I have read on the subject say that the airflow velocity parallel to the horizontal is constant. Therefore the air must accelerate over the aerofoil because velocity must change. The forces required for this to happen act on the aerofoil through the viscous forces of the air. I have however not even got this far in my model because...

Taking any equation for one surface of an aerofoil, at least two parts of it have a 0 gradient. When I differentiate this equation to get velocity, at these points I therefore have infinite velocity, which is obviously not the case.

Please can anybody guide me in the right direction as I am obviously doing something terribly wrong!?

Thanks, Chris

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# Aerospace Mathematically model airflow over an aerofoil

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