Problem $05\mathrm{.}010-$ Calculate pressure coefficient for compressible flow

Consider a wing mounted in the test$-$section of a subsonic wind tunnel. The velocity of the airflow is $\backslash (160\backslash$mathrm$\{$ft$\}/\backslash$mathrm$\{$s$\}\backslash ),$ and the velocity at a point on the wing is $\backslash (244\backslash$mathrm$\{$ft$\}/\backslash$mathrm$\{$s$\}\backslash ).$ If the test$-$section air temperature is $\backslash (510^\{\backslash$circ$\}\backslash$mathrm$\{$R$\}\backslash )$ and the flow velocity is increased to $\backslash (777\backslash$mathrm$\{$ft$\}/\backslash$mathrm$\{$s$\}\backslash ),$ what is the pressure coefficient at the same point?

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The pressure coefficient at the point is

Hint