A jet engine in an aircraft flying at M = 0.9 ingests an airflow of 100 kg/s through an inlet area of 3.07 m2. The adiabatic efficiency of the (internal) diffuser is 0.9, and the Mach number of the flow entering the compressor is 0.4, The ambient temperature and pressure are 222 K and 9.57 kPa, respectively.

a.What is the ratio of the inlet static pressure (at entrance to the engine intake) to the ambient pressure?

b.What is the static pressure ratio across the internal diffuser?

c.What fraction of the inlet dynamic pressure is converted to static pressure in the intake?

 

PROBLEM 2