A 5% thick biconvex airfoil with negative overall camber (2% upper thickness and 3% lower thickness) is shown below. Ass

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A 5 Thick Biconvex Airfoil With Negative Overall Camber 2 Upper Thickness And 3 Lower Thickness Is Shown Below Ass 1 (54.17 KiB) Viewed 17 times

A 5% thick biconvex airfoil with negative overall camber (2% upper thickness and 3% lower thickness) is shown below. Assume that the flow is directed from left to right and the conditions are: Mo> 1 and a = 0°. Moo 0.03 0.01 -0.01 -0.03 -0.05- 0.0 0.1 0.2 0.3 0.4 0.6 0.7 0.8 0.9 1.0 x/c Complete the following: (a) Draw a sketch of the airfoil with a pattern of all shock formations and path of a streamline across the shocks (10 pts). (b) Draw a plot of the relative pressure coefficient, Cp distributions for the upper and lower surfaces of the airfoil as a function of x/c. Does this airfoil produce positive or negative lift, explain why based on the camber and your pressure distributions? Note: the quantitative values of Cp are not relevant for the purpose of the problem, we are interested in the qualitative difference in Cp. (15 pts). T + I 11 II I | 1 1 0.5 III I I t +