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I need to calculate Cp per chord unit of a symmetrical thin airfoil at 10 aoa,...

I need to calculate Cp per chord unit of a symmetrical thin airfoil at 10 aoa, V_infinity = 85 ft/s using the circulation distribution of thin airfoil theory. I know how to get Cp but I need the velocity at each point of the airfoil which I have no idea how to get. This is all the information I have.

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Answer #1

As per the symmetrical thin airfoil ,velocity at each point is calculated according to defined equation at their instant location . In that equation were adding total length in that way calculate the instant location of the velocity.   

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