4)Carbon dioxide flows steadily through a varying cross-sectional-area duct such as a nozzle shown in the figure. The throat area is (10+0.1*A) cm². The carbon dioxide enters the duct at a pressure of (1400+A) kPa and 200°C with a low velocity, and it expands in the nozzle to a pressure of 200 kPa. The duct is designed so that the flow can be approximated as isentropic. Determine the flow rate in the nozzle. A = LAST DIGIT OF YOUR CLASS ID Stagnation region 1400 - AXP 200°C CO₂ 1400

4)Carbon dioxide flows steadily through a varying cross-sectional-area duct such as a nozzle shown in the figure. The throat area is (10+0.1*A) cm². The carbon dioxide enters the duct at a pressure of (1400+A) kPa and 200°C with a low velocity, and it expands in the nozzle to a pressure of 200 kPa. The duct is designed so that the flow can be approximated as isentropic. Determine the flow rate in the nozzle. A = LAST DIGIT OF YOUR CLASS ID Stagnation region 1400 - AXP 200°C CO₂ 1400

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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Concept explainers

Work and Heat Transfer

It is generally related to thermal engineering which tells about the use, creation, conversion and transfer of heat energy between the systems. It is also considered that to transfer heat from one source to another, transfer of masses is also required. There are various mechanisms by which, transfer of heat takes place i.e. thermal conduction, convection, radiation or by change of phase. All these mechanisms have their own specific features which sometimes occur simultaneously within the same system.

Question

4)Carbon dioxide flows steadily through a varying cross-sectional-area duct such as a nozzle shown in
the figure. The throat area is (10+0.1*A) cm². The carbon dioxide enters the duct at a pressure of
(1400+A) kPa and 200°C with a low velocity, and it expands in the nozzle to a pressure of 200 kPa. The
duct is designed so that the flow can be approximated as isentropic. Determine the flow rate in the
nozzle. A = LAST DIGIT OF YOUR CLASS ID
Stagnation
region 1400 - ALPw
200°C
CO₂
1400
P. KP

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