Consider a thin, symmetric airfoil at a 6â° angle of attack flying at a dynamic pressure of if . = 6 kpa and with a chord length of 1.5 meters.

a) write the fundamental equation of thin airfoil theory. which assumptions were used to derive this equation and what does it state?

b) according to thin airfoil theory, what is the lift per unit span at this angle of attack?

c) according to thin airfoil theory, what is the moment per unit span about the leading edge at this angle of attack?

d) consider replacing this airfoil with a cylinder of diameter 1.5 meters. assuming the flow is inviscid, irrotational and steady, how fast must the cylinder rotate in order to generate the same lift?
hint: recall the relationship between the vortex velocity at r = r and the rotation speed.