Computers and Technology

Consider a flat-plate airfoil of chord length l = 3m. Using MATLAB or other computing program (DO NOT DRAW BY HAND), plot the pressure coefficients over the top and bottom surfaces as functions of x/l, where x is the distance from the leading edge. Obtain the plot for four different values of angle of attack as 5O , 10O , 20O and 40O .

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Consider a flat-plate airfoil of chord length l = 3m. Using MATLAB or other computing program (DO NO...

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