$7\mathrm{.}2$ Calculate $c_p,c_v,e,$ and $h$ for

a$.$ The stagnation point conditions given in Problem $7\mathrm{.}1$

b$.$ Air at standard sea level conditions

$($If you do not remember what standard sea level conditions are, find them in an appropriate reference, suehas Referenee $2.)[$See Anderson appendix E$.]$

Note: In the following problems, you will deal with both the International System of Units $($SI$)($N$,$ kg$,$ m$,$ s$,$ K$)$ and the English Engineering System $($lb$,$ slug, ft$,$ s$,R).$ Which system to use will be self$-$evident in each problem. All problems deal with calorically perfect air as the gas, unless otherwise noted. Also, recall that $1$atm$=2116l\frac{b}{f}{t}^2=1\mathrm{.}01{10}^5\frac{N}{m^2}.$

Sorry here,!!!

$7\mathrm{.}1$ The temperature and pressure at the stagnation point of a high$-$speed missile are $934R$ and $7\mathrm{.}8$atm, respectively. Calculate the density at this point.