NB: $,1ft=0\mathrm{.}3048$ meters

$1$ mile $=5280ft$

$1$ gallon of fuel$=6\mathrm{.}75$ lb

Question $1$: Aircraft A $(6$ points$)$

$c=0\mathrm{.}9,G_3=0\mathrm{.}14$

The aircraft cruises at an altitude of $20,000ft.$ It has a cruise fuel weight ratio of $0\mathrm{.}14$ and a tsfc of $0\mathrm{.}90l\frac{b}{h}\frac{?}{lb}.)$

Calculate the initial airspeed $($ mph $)$ required to achieve maximum endurance at this altitude.

Find the maximum endurance time $($hours$)$ at this altitude.

Find the instantaneous range $($miles$/$gallons$)$ values for the max. endurance flight described above at the beginning and at the end of flight, assume constant altitude, constant lift coefficient flight.

Question $2$: Aircraft B $(6$ points$)$

Calculate the minimum absolute ceiling altitude for this aircraft $($in meters$).$

Calculate the corresponding velocity $(k\frac{m}{h})$ at this altitude.

Is this speed attainable? Justify.

Question $3$: Aircraft C$(8$ points$)w_{\text{\&}}=2000d$

$c=0\mathrm{.}92$

larr

The aircraft has a cruise fuel weight of $20,000lb$ and a tsfc of $0\mathrm{.}92l\frac{b}{h}\frac{?}{lb}.$ The aircraft is starting its cruise at $25,000ft$ under best range conditions using the cruise climb flight regime.

Calculate the airspeed $($ mph $)$& range $($miles$).$

What is the lift to drag ratio

Calculate the altitude at the end of flight and the flight path angle in degrees.

Calculate the thrust required at the beginning of flight.