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Investigation of the effects of nozzle exit mach number and nozzle pressure ratio on axisymmetric flow through suddenly expanded nozzles

Computational Fluid Dynamics simulations were carried out using ANSYS FLUENT for suddenly expanded flow through the convergent-divergent nozzle and a suddenly expanded duct. The Length-to-Diameter ratio of 10 for the duct was used in the analysis. Also, an Area Ratio between CD Nozzle exit area and...

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Main Authors: Khan, Sher Afghan, Mohiuddin, M, Saleel, Ahmad C, G M, Fharukh
Format: Article
Language:English
English
Published: Blue Eyes Intelligence Engineering & Sciences Publication 2019
Subjects:
TJ751 Miscellaneous motors and engines. Including gas, gasoline, diesel
Online Access:http://irep.iium.edu.my/71059/7/71059%20Investigation%20of%20the%20effects%20of%20nozzle%20exit%20mach%20number.pdf
http://irep.iium.edu.my/71059/8/71059%20Investigation%20of%20the%20effects%20of%20nozzle%20exit%20mach%20number%20SCOPUS.pdf
http://irep.iium.edu.my/71059/
https://www.ijeat.org/wp-content/uploads/papers/v8i3/C5986028319.pdf
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spelling my.iium.irep.710592019-07-12T07:42:23Z http://irep.iium.edu.my/71059/ Investigation of the effects of nozzle exit mach number and nozzle pressure ratio on axisymmetric flow through suddenly expanded nozzles Khan, Sher Afghan Mohiuddin, M Saleel, Ahmad C G M, Fharukh TJ751 Miscellaneous motors and engines. Including gas, gasoline, diesel Computational Fluid Dynamics simulations were carried out using ANSYS FLUENT for suddenly expanded flow through the convergent-divergent nozzle and a suddenly expanded duct. The Length-to-Diameter ratio of 10 for the duct was used in the analysis. Also, an Area Ratio between CD Nozzle exit area and Duct Area was used to be 1.6. The effects of Nozzle Exit Mach number and the Nozzle Pressure Ratios were evaluated by conducting the simulations for Nozzle Exit Mach numbers: 1.87, 2.25 and 2.58. For each Mach number then, Nozzle Pressure Ratios of 3, 5, 7, 9, and 11 were set respectively. Making a total of 15 cases. All the cases were simulated using the k-ω turbulence model. Simulated results agree with the experimental data. From the analysis, it is clear that the Nozzle Exit Mach number and Nozzle Pressure Ratio have a direct effect on the expanded flow exiting the nozzle. Blue Eyes Intelligence Engineering & Sciences Publication 2019-02 Article PeerReviewed application/pdf en http://irep.iium.edu.my/71059/7/71059%20Investigation%20of%20the%20effects%20of%20nozzle%20exit%20mach%20number.pdf application/pdf en http://irep.iium.edu.my/71059/8/71059%20Investigation%20of%20the%20effects%20of%20nozzle%20exit%20mach%20number%20SCOPUS.pdf Khan, Sher Afghan and Mohiuddin, M and Saleel, Ahmad C and G M, Fharukh (2019) Investigation of the effects of nozzle exit mach number and nozzle pressure ratio on axisymmetric flow through suddenly expanded nozzles. International Journal of Engineering and Advanced Technology (IJEAT), 8 (3). pp. 570-578. https://www.ijeat.org/wp-content/uploads/papers/v8i3/C5986028319.pdf
institution Universiti Islam Antarabangsa Malaysia
building IIUM Library
collection Institutional Repository
continent Asia
country Malaysia
content_provider International Islamic University Malaysia
content_source IIUM Repository (IREP)
url_provider http://irep.iium.edu.my/
language English
English
topic TJ751 Miscellaneous motors and engines. Including gas, gasoline, diesel
spellingShingle TJ751 Miscellaneous motors and engines. Including gas, gasoline, diesel
Khan, Sher Afghan
Mohiuddin, M
Saleel, Ahmad C
G M, Fharukh
Investigation of the effects of nozzle exit mach number and nozzle pressure ratio on axisymmetric flow through suddenly expanded nozzles
description Computational Fluid Dynamics simulations were carried out using ANSYS FLUENT for suddenly expanded flow through the convergent-divergent nozzle and a suddenly expanded duct. The Length-to-Diameter ratio of 10 for the duct was used in the analysis. Also, an Area Ratio between CD Nozzle exit area and Duct Area was used to be 1.6. The effects of Nozzle Exit Mach number and the Nozzle Pressure Ratios were evaluated by conducting the simulations for Nozzle Exit Mach numbers: 1.87, 2.25 and 2.58. For each Mach number then, Nozzle Pressure Ratios of 3, 5, 7, 9, and 11 were set respectively. Making a total of 15 cases. All the cases were simulated using the k-ω turbulence model. Simulated results agree with the experimental data. From the analysis, it is clear that the Nozzle Exit Mach number and Nozzle Pressure Ratio have a direct effect on the expanded flow exiting the nozzle.
format Article
author Khan, Sher Afghan
Mohiuddin, M
Saleel, Ahmad C
G M, Fharukh
author_facet Khan, Sher Afghan
Mohiuddin, M
Saleel, Ahmad C
G M, Fharukh
author_sort Khan, Sher Afghan
title Investigation of the effects of nozzle exit mach number and nozzle pressure ratio on axisymmetric flow through suddenly expanded nozzles
title_short Investigation of the effects of nozzle exit mach number and nozzle pressure ratio on axisymmetric flow through suddenly expanded nozzles
title_full Investigation of the effects of nozzle exit mach number and nozzle pressure ratio on axisymmetric flow through suddenly expanded nozzles
title_fullStr Investigation of the effects of nozzle exit mach number and nozzle pressure ratio on axisymmetric flow through suddenly expanded nozzles
title_full_unstemmed Investigation of the effects of nozzle exit mach number and nozzle pressure ratio on axisymmetric flow through suddenly expanded nozzles
title_sort investigation of the effects of nozzle exit mach number and nozzle pressure ratio on axisymmetric flow through suddenly expanded nozzles
publisher Blue Eyes Intelligence Engineering & Sciences Publication
publishDate 2019
url http://irep.iium.edu.my/71059/7/71059%20Investigation%20of%20the%20effects%20of%20nozzle%20exit%20mach%20number.pdf
http://irep.iium.edu.my/71059/8/71059%20Investigation%20of%20the%20effects%20of%20nozzle%20exit%20mach%20number%20SCOPUS.pdf
http://irep.iium.edu.my/71059/
https://www.ijeat.org/wp-content/uploads/papers/v8i3/C5986028319.pdf
_version_ 1643619962132103168
score 13.211869

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