At a given point on the surface of an airfoil at low speed, the pressure coefficient is -0.175. Use MATLAB to generate a Cp vs M plot for M = 0.5 - 0.8 in increments of ).05. Make sure to include labels and grids on the plot.
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For a given airfoil, the critical Mach number is 0.8. Calculate the value of p/p[infinity] at the minimum pressure point when M[infinity] = 0.8.
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