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the camber of a thin aerofoil with unit chord is given by the equation:
?(?) = ??(? − 1)(? − ?) where k > 0 and b > 0. Depending on the choice of b, this equation can represent a reflex aerofoil in which the mean camber line curves upward toward the trailing edge. To check whether the aerofoil is reflex, one checks to see whether the above curve has both a maximum and minimum (with the maximum occurring ahead of the minimum). (i) Obtain the value of x where corresponding to maximum camber, and if...
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Screenshot 2021-03-29 083338.pngFind the Average power Dissipated in R1 and R2 algabraically.let Vi = acos(ωt)
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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.