$4\mathrm{.}4$ An inlet with an area $A_1$ of $10f{t}^2$ is designed to have an inlet Mach

number $M_1$ of $0\mathrm{.}6.$ Determine the additive drag at the flight conditions

of sea$-$level static test and Mach number of $0\mathrm{.}8$ at $40-kft$ altitude.

Sea level: p$0=2116$ lbf$/$ft$2$

$40000$ft: p$0=393\mathrm{.}15$lbf$/$ft$2$

To get A$0,$ you can use A$/$A$*$ expression from class