A turbine nozzle vane at high speed exhibits a normal shock. The flow is modelled as analogous to that through a convergent-divergent de Laval nozzle with a normal shock at the nozzle exit. Just upstream of the shock, the exit Mach number Me = 1.09, the absolute static pressure pe = 280 kPa, the static temperature Te = 586 K, the ratio of specific heats of the combustion products k = 1.35, and the constant pressure specific heat capacity Cp 1027 J-kg" "K-1. Assuming the combustion products are constant property ideal gasses, determine the density of the combustion products pb after the shock. State your answer in kg-m" to two decimal places and enter the numerical value only.

A turbine nozzle vane at high speed exhibits a normal shock. The flow is modelled as analogous to that through a convergent-divergent de Laval nozzle with a normal shock at the nozzle exit. Just upstream of the shock, the exit Mach number Me = 1.09, the absolute static pressure pe = 280 kPa, the static temperature Te = 586 K, the ratio of specific heats of the combustion products k = 1.35, and the constant pressure specific heat capacity Cp 1027 J-kg" "K-1. Assuming the combustion products are constant property ideal gasses, determine the density of the combustion products pb after the shock. State your answer in kg-m" to two decimal places and enter the numerical value only.

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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Solve by using isentropic and normal shock tables please
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