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Engineering, 18.11.2019 20:31 adiaripley6408

Consider an naca 2412 airfoil in a low-speed fl ow at zero degrees angle of attack and a reynolds number of 8.9 × 10 6 . calculate the percentage of drag from pressure drag due to fl ow separation (form drag). assume a fully turbulent boundary layer over the airfoil. assume that the airfoil is thin enough that the skin-friction drag can be estimated by the fl at-plate results discussed in ch. 4.

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Consider an naca 2412 airfoil in a low-speed fl ow at zero degrees angle of attack and a reynolds nu...

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