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 2 300 ( =) C,,u=1300 C Cpu -2.2277 +2.2777 P,u = 0.95( =) C C, =10.95| X for for for 0s (2)0.1 0 = X 0.1 1.0 X s(x)1.0 0 Calculate the location of center of pressure Calculate the moment coefficient about the leading edge