Cover Image

Effect of cavities in suddenly expanded flow at supersonic mach number

The contribution from the base drag due to the sub-atmospheric pressure is significant. It can be more than two-thirds of the net drag. There is a need to increase the base pressure and hence decrease the base drag. This research examines the effect of Mach number on base pressure. To accomplish thi...

Full description

Saved in:
Bibliographic Details
Main Authors: Ismail, Atifatul Ismah, Khan, Sher Afghan, Rajendran, Parvathy, Sulaeman, Erwin
Format: Article
Language:English
English
Published: Semarak Ilmu Publishing 2021
Subjects:
TL780 Rockets
Online Access:http://irep.iium.edu.my/92639/7/92639_Effect%20of%20cavities%20in%20suddenly%20expanded%20flow%20at%20supersonic%20mach%20number.pdf
http://irep.iium.edu.my/92639/13/92639_Effect%20of%20cavities%20in%20suddenly%20expanded%20flow%20at%20supersonic%20mach%20number_Scopus.pdf
http://irep.iium.edu.my/92639/
https://semarakilmu.com.my/journals/index.php/CFD_Letters/article/view/5
https://doi.org/10.37934/cfdl.13.9.5771
Tags: Add Tag
No Tags, Be the first to tag this record!
id my.iium.irep.92639
record_format dspace
spelling my.iium.irep.926392021-11-18T02:20:48Z http://irep.iium.edu.my/92639/ Effect of cavities in suddenly expanded flow at supersonic mach number Ismail, Atifatul Ismah Khan, Sher Afghan Rajendran, Parvathy Sulaeman, Erwin TL780 Rockets The contribution from the base drag due to the sub-atmospheric pressure is significant. It can be more than two-thirds of the net drag. There is a need to increase the base pressure and hence decrease the base drag. This research examines the effect of Mach number on base pressure. To accomplish this objective, it controls the efficacy in an enlarged duct computed by the numerical approach using Computational Fluid Dynamics (CFD) Analysis. This experiment was carried out by considering the expansion level and the aspect cavity ratio. The computational fluid dynamics method is used to model supersonic motion with the sudden expansion, and a convergent-divergent nozzle is used. The Mach number is 1.74 for the present study, and the area ratio is 2.56. The L/D ratio varied from 2, 4, 6, 8, and 10, and the simulated nozzle pressure ratio ranged from 3 to 11. The two-dimensional planar design used commercial software from ANSYS. The airflow from a Mach 1.74 convergent-divergent axisymmetric nozzle expanded suddenly into circular ducts of diameters 17 and 24.5 mm with and without annular rectangular cavities. The diameter of the duct is taken D=17mm and D=24.5mm. The C-D nozzle was developed and modeled in the present study: K-ε standard wall function turbulence model was used with the commercial computational fluid dynamics (CFD) and validated. The result indicates that the base pressure is impacted by the expansion level, the enlarged duct size, and the passage’s area ratio. Semarak Ilmu Publishing 2021-09-30 Article PeerReviewed application/pdf en http://irep.iium.edu.my/92639/7/92639_Effect%20of%20cavities%20in%20suddenly%20expanded%20flow%20at%20supersonic%20mach%20number.pdf application/pdf en http://irep.iium.edu.my/92639/13/92639_Effect%20of%20cavities%20in%20suddenly%20expanded%20flow%20at%20supersonic%20mach%20number_Scopus.pdf Ismail, Atifatul Ismah and Khan, Sher Afghan and Rajendran, Parvathy and Sulaeman, Erwin (2021) Effect of cavities in suddenly expanded flow at supersonic mach number. CFD Letters, 13 (9). pp. 57-71. ISSN 2180-1363 https://semarakilmu.com.my/journals/index.php/CFD_Letters/article/view/5 https://doi.org/10.37934/cfdl.13.9.5771
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 TL780 Rockets
spellingShingle TL780 Rockets
Ismail, Atifatul Ismah
Khan, Sher Afghan
Rajendran, Parvathy
Sulaeman, Erwin
Effect of cavities in suddenly expanded flow at supersonic mach number
description The contribution from the base drag due to the sub-atmospheric pressure is significant. It can be more than two-thirds of the net drag. There is a need to increase the base pressure and hence decrease the base drag. This research examines the effect of Mach number on base pressure. To accomplish this objective, it controls the efficacy in an enlarged duct computed by the numerical approach using Computational Fluid Dynamics (CFD) Analysis. This experiment was carried out by considering the expansion level and the aspect cavity ratio. The computational fluid dynamics method is used to model supersonic motion with the sudden expansion, and a convergent-divergent nozzle is used. The Mach number is 1.74 for the present study, and the area ratio is 2.56. The L/D ratio varied from 2, 4, 6, 8, and 10, and the simulated nozzle pressure ratio ranged from 3 to 11. The two-dimensional planar design used commercial software from ANSYS. The airflow from a Mach 1.74 convergent-divergent axisymmetric nozzle expanded suddenly into circular ducts of diameters 17 and 24.5 mm with and without annular rectangular cavities. The diameter of the duct is taken D=17mm and D=24.5mm. The C-D nozzle was developed and modeled in the present study: K-ε standard wall function turbulence model was used with the commercial computational fluid dynamics (CFD) and validated. The result indicates that the base pressure is impacted by the expansion level, the enlarged duct size, and the passage’s area ratio.
format Article
author Ismail, Atifatul Ismah
Khan, Sher Afghan
Rajendran, Parvathy
Sulaeman, Erwin
author_facet Ismail, Atifatul Ismah
Khan, Sher Afghan
Rajendran, Parvathy
Sulaeman, Erwin
author_sort Ismail, Atifatul Ismah
title Effect of cavities in suddenly expanded flow at supersonic mach number
title_short Effect of cavities in suddenly expanded flow at supersonic mach number
title_full Effect of cavities in suddenly expanded flow at supersonic mach number
title_fullStr Effect of cavities in suddenly expanded flow at supersonic mach number
title_full_unstemmed Effect of cavities in suddenly expanded flow at supersonic mach number
title_sort effect of cavities in suddenly expanded flow at supersonic mach number
publisher Semarak Ilmu Publishing
publishDate 2021
url http://irep.iium.edu.my/92639/7/92639_Effect%20of%20cavities%20in%20suddenly%20expanded%20flow%20at%20supersonic%20mach%20number.pdf
http://irep.iium.edu.my/92639/13/92639_Effect%20of%20cavities%20in%20suddenly%20expanded%20flow%20at%20supersonic%20mach%20number_Scopus.pdf
http://irep.iium.edu.my/92639/
https://semarakilmu.com.my/journals/index.php/CFD_Letters/article/view/5
https://doi.org/10.37934/cfdl.13.9.5771
_version_ 1717092999881555968
score 13.211869

Similar Items