Consider an infinitely thin flat plate of chord c at an angle of attack a in a supersonic flow. The pressures on the upper and lower surfaces are different but constant over each surface; i.e., p_u(s) = c₁ and p₁(s) = c₂, where c₁ and c₂ are constants and c₂ > c₁. Ignoring the shear stress, calculate the location of the center of pressure.