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I read on a website that the Bernoulli's expression can be applied to airplane wings by using the equation:

Difference in pressure above and below wing

= 1/2 x air density x [(airflow velocity below wing)^2 - (airflow velocity above wing)^2]

I tried using it but the units don't seem to add up correctly when I use the metric system (kg/m^3 for density, m/s for velocity).

The website uses (slugs/ft^3) for density, and (ft/s) for velocity.

Can anybody tell me if this equation is correct?

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# Aerospace Question on Bernoulli's law

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