Starting from isentropuc state relationships, show that the coefficient of thrust can be expressed as the following:$c_T=y\sqrt[\phantom{2}]{\frac{2}{y-1}}(\frac{2}{y+1}{)}^{\frac{y+1}{2(y-1)}}\sqrt[\phantom{2}]{1-(\frac{P_e}{P_o})\frac{(y-1)}{y}}$