Consider an infinitely thin flat plate with a $1$ m chord at an angle of $10$ in a supersonic flow

as shown in figure below.

The pressure and shear distributions on the upper and lower surfaces are given by$,$

$p_u=4{10}^4(x-1{)}^2+5\mathrm{.}4{10}^4$

$p_l=2{10}^4(x-1{)}^2+1\mathrm{.}73{10}^5$

${}_u=288x^{-0\mathrm{.}2}$

${}_l=731x^{-0\mathrm{.}2}$

respectively, where $x$ is the distance from the leading edge along the plate in meters and $p$

and $$ are in Newtons per square meter. Calculate the normal and axial forces, the lift and

drag, moments about the leading edge, and moments about quarter chord, all per unit span.

Calculate the location of the center of pressure. Calculate and plot pressure coefficient, $c_p,$

versus $x.$ Need help calculating and plotting the pressure coefficient Cp versus x$.$