The jet is flying at M = 1.3, where the absolute air pressure is 55 kPa . A shock is formed at the inlet of the engine. Assume isentropic flow within the engine. k = 1.40 for air. Determine the Mach number of the air flow just within the engine where the diameter is 0.6 m.What is the stagnation pressure in this region? What is the pressure in this region? The jet is flying at M = 1.3, where the absolute airpressure is 55 kPa. A shock is formed at the inlet ofthe engine. Assume is entropic flow within the engine.k = 1.40 for air.(Figure 1)Figure0.4 m0,6 mM = 1.31 of 1Part ADetermine the Mach number of the air flow just within the engine where the diameter is 0.6 m.Express your answer using three significant figures.17 ΑΣΦM =SubmitPart BPo =SubmitPart CRequest AnswerWhat is the stagnation pressure in this region?Express your answer to three significant figures and include the appropriate units.p=μÀValueRequest AnswervecμAValueBUnitsWhat is the pressure in this region?Express your answer to three significant figures and include the appropriate units.Units?PUT??

Given:upstream Mach number M1 = 1.3upstream pressure P1 = 55 kPaTo find:downstreamA. Mach numberB.…

Answered: The jet is flying at M = 1.3, where the…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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The jet is flying at M = 1.3, where the absolute air pressure is 55 kPa . A shock is formed at the inlet of the engine. Assume isentropic flow within the engine. k = 1.40 for air.

Determine the Mach number of the air flow just within the engine where the diameter is 0.6 m.

What is the stagnation pressure in this region?

What is the pressure in this region?

The jet is flying at M = 1.3, where the absolute air
pressure is 55 kPa. A shock is formed at the inlet of
the engine. Assume is entropic flow within the engine.
k = 1.40 for air.(Figure 1)
Figure
0.4 m
0,6 m
M = 1.3
1 of 1
Part A
Determine the Mach number of the air flow just within the engine where the diameter is 0.6 m.
Express your answer using three significant figures.
17 ΑΣΦ
M =
Submit
Part B
Po =
Submit
Part C
Request Answer
What is the stagnation pressure in this region?
Express your answer to three significant figures and include the appropriate units.
p=
μÀ
Value
Request Answer
vec
μA
Value
B
Units
What is the pressure in this region?
Express your answer to three significant figures and include the appropriate units.
Units
?
PUT
?
?

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