Engineers call the supersonic combustion in a scramjetengine almost miraculous, “like lighting a match in a hurricane.”Figure C9.8 is a crude idealization of the engine.Air enters, burns fuel in the narrow section, then exits, all at supersonic speeds. There are no shock waves. Assume areasof 1 m2 at sections 1 and 4 and 0.2 m2 at sections 2 and3. Let the entrance conditions be Ma1 = 6, at 10,000 mstandard altitude. Assume isentropic fl ow from 1 to 2,frictionless heat transfer from 2 to 3 with Q = 500 kJ/kg,and isentropic fl ow from 3 to 4. Calculate the exit conditionsand the thrust produced. CombustionMa >1Ma >14

Given Data: The area at section 1 and 4 is: A1=1 m2. The area at section 2 and 4 is: A2=0.2 m2. The…

Answered: Combustion Ma >1 Ma >1 4

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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Engineers call the supersonic combustion in a scramjet
engine almost miraculous, “like lighting a match in a hurricane.”
Figure C9.8 is a crude idealization of the engine.
Air enters, burns fuel in the narrow section, then exits, all at supersonic speeds. There are no shock waves. Assume areas
of 1 m² at sections 1 and 4 and 0.2 m² at sections 2 and
3. Let the entrance conditions be M_a1 = 6, at 10,000 m
standard altitude. Assume isentropic fl ow from 1 to 2,
frictionless heat transfer from 2 to 3 with Q = 500 kJ/kg,
and isentropic fl ow from 3 to 4. Calculate the exit conditions
and the thrust produced.

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