Problem 1: The inlet of a jet engine flying at supersonic speed (M∞ > 1) is supposed to compress (decelerate) flow to subsonic Mach number. We consider a simplified design with inlet area A; and throat area A*. The area ratio is A = 1.3. Assuming that the throat is always sonic find: (a) the flight Mach number Moo for which the compression is completely isentropic; (b) the flight Mach number M∞ for which a normal shock occurs at the inlet lip. In this case, calculate also the total pressure loss. Inlet Throat M Isentropic M=1 M<1 A* Inlet Throat Engine M + Shock M=1 M<1 A₁ A Engine
Problem 1: The inlet of a jet engine flying at supersonic speed (M∞ > 1) is supposed to compress (decelerate) flow to subsonic Mach number. We consider a simplified design with inlet area A; and throat area A*. The area ratio is A = 1.3. Assuming that the throat is always sonic find: (a) the flight Mach number Moo for which the compression is completely isentropic; (b) the flight Mach number M∞ for which a normal shock occurs at the inlet lip. In this case, calculate also the total pressure loss. Inlet Throat M Isentropic M=1 M<1 A* Inlet Throat Engine M + Shock M=1 M<1 A₁ A Engine
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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Transcribed Image Text:Problem 1:
The inlet of a jet engine flying at supersonic speed (M∞ > 1) is supposed to compress
(decelerate) flow to subsonic Mach number. We consider a simplified design with inlet area
A; and throat area A*. The area ratio is A 1.3. Assuming that the throat is always
sonic find:
(a) the flight Mach number M∞ for which the compression is completely isentropic;
(b) the flight Mach number M∞ for which a normal shock occurs at the inlet lip. In this
case, calculate also the total pressure loss.
Inlet
Throat
M
Isentropic
M=1
M<1
A₁
A*
Engine
Inlet
Throat
M
Shock M=1
M<1
A₁
A*
Engine
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