Maximum Weight $=50,265lb.$

Maximum Fuel $=11,023$ lb$.$

Maximum Payload $=16,645lb.$

Operating Weight Empty $=28,682lb.$

Powerplant $=$ PW$127$M$/$N$/$XT $(2)2,750$ HP each.

Cruise Speed:

Cruise Altitud $lon$

Consider the aircraft in the attachment.

If the aircraft uses Jet$-$A$-1$ fuel, what is its fuel volume in gallons and liters? $($Assume that Jet$-$A$-1$ has a specific density of $6\mathrm{.}5lb\frac{m}{g}al.)$

If its maximum range is $740$ nautical miles, what is that range in kilometers and statute miles?

Using the attached drawing, how would you obtain the maximum external width of the fuselage? What is it$?$

Using the attached drawing, how would you obtain the approximate area of the planar top view of the fuselage in English Engineering Units? What is it$?$

The aircraft cruises at Mach $0\mathrm{.}45$ while at a standard altitude of $20,000ft.$

a$.$ What is the ambient temperature at that altitude, in SI Units?

b$.$ What is the ambient pressure at that altitude, in English Engineering Units?

c$.$ The speed of sound $a$ is only a function of the nature of the fluid and its temperature: $a=\sqrt[\phantom{2}]{RT}$;$=1\mathrm{.}4$;$R=287\frac{J}{kg*K}.$ What is the aircraft's velocity in knots?