distribution p given by Consider a circular airfoil with a surface pressure p = P +...

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distribution p given by Consider a circular airfoil with a surface pressure p = P + = pU² - 2U² (sin 0 – sin 3)², (3.19) where U and P are flow velocity and pressure far away; p is fluid mass density supposed uniform; 0 is angular position measured from the horizontal anti-clockwise, and ß gives the angular position of the stagnation points. (1) Find the lift and the drag. (2) Find the moment about a normal centroidal axis. distribution p given by Consider a circular airfoil with a surface pressure p = P + = pU² - 2U² (sin 0 – sin 3)², (3.19) where U and P are flow velocity and pressure far away; p is fluid mass density supposed uniform; 0 is angular position measured from the horizontal anti-clockwise, and ß gives the angular position of the stagnation points. (1) Find the lift and the drag. (2) Find the moment about a normal centroidal axis. distribution p given by Consider a circular airfoil with a surface pressure p = P + = pU² - 2U² (sin 0 – sin 3)², (3.19) where U and P are flow velocity and pressure far away; p is fluid mass density supposed uniform; 0 is angular position measured from the horizontal anti-clockwise, and ß gives the angular position of the stagnation points. (1) Find the lift and the drag. (2) Find the moment about a normal centroidal axis.

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Here are the steps to solve this problem 1 Find the lift and drag The ... View the full answer