Answer:
hello your question is incomplete attached below is the complete question
A) optimum compressor ratio = 9.144
B) specific thrust = 2.155 N.s /kg
C) Thrust specific fuel consumption = 1670.4 kg/N.h
Explanation:
Given data :
Mo = 2.1 , To = 220k , Tt4 = 1700 k, hpr = 42000 kj/kg, Cp = 1.004 kj/ kg.k
γ = 1.4
attached below is the detailed solution
Answer:
mass flow rate = 0.0534 kg/sec
velocity at exit = 29.34 m/sec
Explanation:
From the information given:
Inlet:
Temperature
Quality
Outlet:
Temperature
Quality
The following data were obtained at saturation properties of R134a at the temperature of -16° C
Answer:
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Explanation:
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Answer:
False
Explanation:
MRK ME BRAINLIEST PLZZZZZZZZZZZZZZZZZZ
Answer:
A mock-up
Explanation:
It is made of cheap and easy to access parts.