MAE112HW3

# MAE112HW3 - Due February 1 2008 MAE 112 Winter 2008...

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1 Due: February 1, 2008 MAE 112 Winter 2008 Homework Assignment #3 1. Consider a jet engine flying at a Mach number of 1.4. A normal shock sits at the entrance of the divergent diffuser. The diffuser entrance cross-sectional area is 2.5 ft 2 . The ambient conditions are 490 ° R for temperature and 1 atmosphere for pressure. (a) What is the stagnation pressure immediately behind the shock? What is the Mach number immediately behind the shock? What is the mass flow through the diffuser? (b) What is the minimum cross-sectional area required at the other end of the diffuser in order to insure that the Mach number of the flow entering the compressor does not exceed 0.12? 2. Consider a Kantrowitz-Donaldson diffuser designed for a flight Mach number of 1.5. The entrance area equals 2.0 ft 2 and the ambient air temperature and pressure are 530 ° R and one atmosphere. The flow is isentropic everywhere except across the normal shockwave. Determine: (a) the minimum cross-sectional area of the throat such that a normal shock may be

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## This homework help was uploaded on 04/07/2008 for the course MAE 112 taught by Professor Sirgiano during the Winter '08 term at UC Irvine.

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MAE112HW3 - Due February 1 2008 MAE 112 Winter 2008...

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