Consider an infinitely thin flat plate of chord c at an angle of attack α in a supersonic flow. the pressures on the upper and lower surfaces are different and linearly varying over each surface; that is, pu(s) = c1 (x/c) and pl(s) = c2 (x/c), where c1 and c2 are constants and c2 > c1. ignoring the shear stress, calculate the location of the center of pressure. (round the final answer to two decimal place.)