Control of suddenly expanded flow with cavity at sonic Mach number

Airflow from a convergent nozzle at sonic Mach number expanded suddenly into a circular duct of larger cross-sectional area, provided with annular rectangular cavities, which was studied numerically, focusing attention on the base pressure, and the flow development in the enlarged duct. It was found...

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Main Authors: Fiqri, Muhammad Ikhwan, Ahmed Pathan, Khizer, Khan, Sher Afghan
Other Authors: Siddiqui, Altamush
Format: Book Chapter
Language:English
English
Published: Springer 2024
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Online Access:http://irep.iium.edu.my/111346/6/49d0aee4-661b-4019-9579-d1f692033d79%20%281%29.pdf
http://irep.iium.edu.my/111346/1/Ikhwan%20Paper.pdf
http://irep.iium.edu.my/111346/
https://link.springer.com/bookseries/11693.
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spelling my.iium.irep.1113462024-03-16T03:39:56Z http://irep.iium.edu.my/111346/ Control of suddenly expanded flow with cavity at sonic Mach number Fiqri, Muhammad Ikhwan Ahmed Pathan, Khizer Khan, Sher Afghan TL787 Astronautics Airflow from a convergent nozzle at sonic Mach number expanded suddenly into a circular duct of larger cross-sectional area, provided with annular rectangular cavities, which was studied numerically, focusing attention on the base pressure, and the flow development in the enlarged duct. It was found that the base pressure is strongly influenced by the expansion level at the nozzle exit, the area ratio of the passage, and the length-to-diameter ratio of the enlarged duct. For the low area ratio, the annular cavities increase the base pressure. Also, the cavity aspect ratio influences the base pressure significantly for the lower area ratio. The nozzle pressure ratio (NPR), the cavity aspect ratio (ASR), and the cavity location (CL) were considered as the flow and geometrical parameters in this study. The computational fluid dynamics approach uses flow from a convergent nozzle for subsonic and sonic Mach numbers with sudden expansion. For this investigation, the Mach number is 1.00, which is sonic, and the duct-to-nozzle exit area ratio is 2.25. The length-to-diameter ratio (L/D) was altered as 1, 2, 3, 4, and 6, while the simulated nozzle pressure ratio (NPR) was 1.5, 2, 3, 4, and 5. The annular rectangular cavities with a width of 3 mm and height of 3 mm for ASR 1. A width of 3 mm and a height of 6 mm for ASR 2 are considered to compare the base pressure results. The nozzle was modeled and analyzed using this work's K-standard wall function turbulence model. The results show that the NPR and cavity placement from the base wall significantly impacted the base pressure. Springer Siddiqui, Altamush Hassan, Nadeem Tariq, Andallib 2024 Book Chapter PeerReviewed application/pdf en http://irep.iium.edu.my/111346/6/49d0aee4-661b-4019-9579-d1f692033d79%20%281%29.pdf application/pdf en http://irep.iium.edu.my/111346/1/Ikhwan%20Paper.pdf Fiqri, Muhammad Ikhwan and Ahmed Pathan, Khizer and Khan, Sher Afghan (2024) Control of suddenly expanded flow with cavity at sonic Mach number. In: Advances in Heat Transfer and Fluid Dynamics. Select Proceedings of AHTFD 2022 . Springer, pp. 1-425. ISBN 978-981-99-7212-8 https://link.springer.com/bookseries/11693. 10.1007/978-981-99-7213-5
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 TL787 Astronautics
spellingShingle TL787 Astronautics
Fiqri, Muhammad Ikhwan
Ahmed Pathan, Khizer
Khan, Sher Afghan
Control of suddenly expanded flow with cavity at sonic Mach number
description Airflow from a convergent nozzle at sonic Mach number expanded suddenly into a circular duct of larger cross-sectional area, provided with annular rectangular cavities, which was studied numerically, focusing attention on the base pressure, and the flow development in the enlarged duct. It was found that the base pressure is strongly influenced by the expansion level at the nozzle exit, the area ratio of the passage, and the length-to-diameter ratio of the enlarged duct. For the low area ratio, the annular cavities increase the base pressure. Also, the cavity aspect ratio influences the base pressure significantly for the lower area ratio. The nozzle pressure ratio (NPR), the cavity aspect ratio (ASR), and the cavity location (CL) were considered as the flow and geometrical parameters in this study. The computational fluid dynamics approach uses flow from a convergent nozzle for subsonic and sonic Mach numbers with sudden expansion. For this investigation, the Mach number is 1.00, which is sonic, and the duct-to-nozzle exit area ratio is 2.25. The length-to-diameter ratio (L/D) was altered as 1, 2, 3, 4, and 6, while the simulated nozzle pressure ratio (NPR) was 1.5, 2, 3, 4, and 5. The annular rectangular cavities with a width of 3 mm and height of 3 mm for ASR 1. A width of 3 mm and a height of 6 mm for ASR 2 are considered to compare the base pressure results. The nozzle was modeled and analyzed using this work's K-standard wall function turbulence model. The results show that the NPR and cavity placement from the base wall significantly impacted the base pressure.
author2 Siddiqui, Altamush
author_facet Siddiqui, Altamush
Fiqri, Muhammad Ikhwan
Ahmed Pathan, Khizer
Khan, Sher Afghan
format Book Chapter
author Fiqri, Muhammad Ikhwan
Ahmed Pathan, Khizer
Khan, Sher Afghan
author_sort Fiqri, Muhammad Ikhwan
title Control of suddenly expanded flow with cavity at sonic Mach number
title_short Control of suddenly expanded flow with cavity at sonic Mach number
title_full Control of suddenly expanded flow with cavity at sonic Mach number
title_fullStr Control of suddenly expanded flow with cavity at sonic Mach number
title_full_unstemmed Control of suddenly expanded flow with cavity at sonic Mach number
title_sort control of suddenly expanded flow with cavity at sonic mach number
publisher Springer
publishDate 2024
url http://irep.iium.edu.my/111346/6/49d0aee4-661b-4019-9579-d1f692033d79%20%281%29.pdf
http://irep.iium.edu.my/111346/1/Ikhwan%20Paper.pdf
http://irep.iium.edu.my/111346/
https://link.springer.com/bookseries/11693.
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score 13.18916