Question

A ramjet is flying at mach no 1.818 at an
altitude of
16.75 km. (Pa =9.122 kPa.
Ta= - 56.5c, sonic speed 295 m/sec (vel of sound),
The flow is assumed to enter the intake of the
romjet through a normal shock. standing at the
intake phase. No pre-entry loss
or fiction Loss
inside the engine is assumed
is assumed to exist. Combustion
delivery temp. is, 1280k and the fuel air
ratio is 1:40. The area at the intake phase
is A¹= 0.0929 m² and area of the combustion chamber, i.e.,
A³= 0.1858 m²​

Answer 1

Answer:

couldn't get your question.

Answer 2

Answer:

Good morning bro......