3. Consider an airfoil with chord length c and running distance x measured along the chord....

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3. Consider an airfoil with chord length c and running distance x measured along the chord. The leading edge is located at (x/c) = 0 and the trailing edge at (x/c) = 1. The pressure coefficient variations over the upper and lower surfaces are given, respectively, as Cp.u 300(=) * =1-300 Cpu -2.2277+2.2777 = Cpl =1-0.95 for 0 0.1 X for C 0.15 (2) 1.0 for Os(#)1.0 Chula ISE a. Using MATLAB, plot the pressure distribution b. Calculate the normal force coefficient C. Calculate the location of center of pressure d. Calculate the moment coefficient about the leading edge pg. 2/2 3. Consider an airfoil with chord length c and running distance x measured along the chord. The leading edge is located at (x/c) = 0 and the trailing edge at (x/c) = 1. The pressure coefficient variations over the upper and lower surfaces are given, respectively, as Cp.u 300(=) * =1-300 Cpu -2.2277+2.2777 = Cpl =1-0.95 for 0 0.1 X for C 0.15 (2) 1.0 for Os(#)1.0 Chula ISE a. Using MATLAB, plot the pressure distribution b. Calculate the normal force coefficient C. Calculate the location of center of pressure d. Calculate the moment coefficient about the leading edge pg. 2/2