Question $1$:

Answer All Questions

Consider the Gulfstream like, having a maximum available thrust at $30,000(f)(T_A{)}_{\text{m}\text{a}\text{n}}=$

$15,371($lb$).$ At $30,000($ft$),$ the air temperature is $)$ and the universal gas constant,

$R=1716($ft$-$lb$/\frac{?}{?}R$ 'slug$)$ with $=1\mathrm{.}4.$ Assume that the flight Mach number at which the large

transonic drag rise begins $M_{DO}=0\mathrm{.}82.$ Calculate the maximum velocity of the airplane at an

altitude of $30,000ft.$

Fig. $1.$ Same trend of the drag$-$

divergence data of Gulfstream like,

at $30,000ft$ altitude.

Fig $2.$ Drag versus Mach number,

including drag$-$divergence effects,

estimated for the Gulfstream like

Altitude $=30,000ft,W=73,000lb.$