CBSE BOARD XII, asked by aspirantdefence380, 2 months ago

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 to the ambient pressure?

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

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

intake?​

Answers

Answered by pappi17071983
0

Answer:

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Explanation:

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?

Step-by-step solution

100% (20 ratings) for this solution

Step 1 of 3

(a)

Determine the inlet stagnation temperature,  by using the following relation:

Here, the ambient temperature is , the specific heat ratio is , and the flight Mach number is .

Substitute 1.4 for ,  for  and 0.9 for .

The inlet stagnation temperature,  is determined as .

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