Location of center of pressure is given as \[{x_{cp}} = \left( {\frac{c}{4}} \right) – \frac{{M_{c/4}^\prime }}{{{L^{^\prime }}}}\]

Where\({x_{cp}}\)  is the distance of center of pressure from the leading edge of airfoil, and ‘c’ is the chord length .\(M_{c/4}^\prime \) is moment per unit span about quarter-chord point and \({L^\prime }\) is the lift per unit span;\[\begin{array}{l}{x_{cp}} = \frac{c}{4} – \frac{{M_{c/4}^\prime }}{{{L^\prime }}}\\\frac{{{x_{cp}}}}{c} = \frac{1}{4} – \frac{{\left( {M_{c/4}^\prime /{q_\infty }{c^2}} \right)}}{{\left( {{L^\prime }/{q_\infty }c} \right)}}\end{array}\]\[\begin{array}{l} = \frac{1}{4} – \left( {\frac{{{c_{m,c/4}}}}{{{c_l}}}} \right)\\ = \frac{1}{4} – \left( {\frac{{ – 0.08}}{{0.80}}} \right)\\ = \frac{1}{4} + 0.1\\ = 0.25 + 0.1\\ = 0.35\end{array}\]Therefore, location of center of pressure is at 0.35 with respect to chord length.