Question 4 - Critical Mach Number Estimation (8 Points): The incompressible Cp distribution of an airfoil...

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Question 4 - Critical Mach Number Estimation (8 Points): The incompressible Cp distribution of an airfoil at a given angle of attack has been determined based on wind tunnel testing. The data is given in the following figure. Cp -2.0 -1.5 -1.0 - Upper surface -0.5 0 x/c 1.0 0.5 Lower surface 1.04 Based on the measured data, estimate the critical Mach number for this airfoil at this particular angle of attack. Fell free to use MATLAB. Question 4 - Critical Mach Number Estimation (8 Points): The incompressible Cp distribution of an airfoil at a given angle of attack has been determined based on wind tunnel testing. The data is given in the following figure. Cp -2.0 -1.5 -1.0 - Upper surface -0.5 0 x/c 1.0 0.5 Lower surface 1.04 Based on the measured data, estimate the critical Mach number for this airfoil at this particular angle of attack. Fell free to use MATLAB.