Problem C:

Following that first initial study, you decide to gain some more insight, by looking at one of

aviation$$s classic engine: the Rolls$-$Royce Olympus, used in the Concorde. This was one of the

first two$-$spool engines ever designed, a big achievement, but what matters here is that the flow

also had to be slowed down before reaching the main engine, and that$$s what you care about.

At its main cruise design point, the plane traveled at Mach $2\mathrm{.}2$ at $20$km altitude. Its intake clever

design dropped the speed to Mach $1\mathrm{.}3$ isentropically $($see Problem B$,$ above...$).$ Then, the flow

passed through a normal shock, and expanded through an isentropic diffuser, before entering the

compressor at Mach $0\mathrm{.}4.$

Determine:

a$)$ The state of the flow downstream of the normal shock.

b$)$ The total pressure and total temperature of the flow as it enters the engine.

c$)$ The static pressure and static temperature of the flow as it enters the engine.

d$)$ Compare to the outside static and stagnation pressure and temperature of the flow, before

reaching the planeProblem C:

Following that first initial study, you decide to gain some more insight, by looking at one of

aviation$$s classic engine: the Rolls$-$Royce Olympus, used in the Concorde. This was one of the

first two$-$spool engines ever designed, a big achievement, but what matters here is that the flow

also had to be slowed down before reaching the main engine, and that$$s what you care about.

At its main cruise design point, the plane traveled at Mach $2\mathrm{.}2$ at $20$km altitude. Its intake clever

design dropped the speed to Mach $1\mathrm{.}3$ isentropically $($see Problem B$,$ above...$).$ Then, the flow

passed through a normal shock, and expanded through an isentropic diffuser, before entering the

compressor at Mach $0\mathrm{.}4.$

Determine:

a$)$ The state of the flow downstream of the normal shock.

b$)$ The total pressure and total temperature of the flow as it enters the engine.

c$)$ The static pressure and static temperature of the flow as it enters the engine.

d$)$ Compare to the outside static and stagnation pressure and temperature of the flow, before

reaching the plane