Experimental and numerical studies on flow from axisymmetric nozzle flow with sudden expansion for Mach 3.0 using CFD

Researches over the recent past in the field of aerodynamic vehicles have been concerned with the problem of flow separation over its base which has lead to the formation of low pressure circulation region. This pressure is found to be noticeably lower than the free stream atmospheric pressure....

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Main Authors:	Quadros, Jaimon Dennis, Khan, Sher Afghan, A. J., Antony, Vas, Jolene S.
Format:	Conference or Workshop Item
Language:	English
Published:	ISET 2016 2016
Subjects:	TL500 Aeronautics TL780 Rockets TL787 Astronautics
Online Access:	http://irep.iium.edu.my/51127/ http://irep.iium.edu.my/51127/ http://irep.iium.edu.my/51127/1/51127_Experimental_and_numerical_studies.pdf

id	iium-51127
recordtype	eprints
spelling	iium-511272017-10-12T12:38:51Z http://irep.iium.edu.my/51127/ Experimental and numerical studies on flow from axisymmetric nozzle flow with sudden expansion for Mach 3.0 using CFD Quadros, Jaimon Dennis Khan, Sher Afghan A. J., Antony Vas, Jolene S. TL500 Aeronautics TL780 Rockets TL787 Astronautics Researches over the recent past in the field of aerodynamic vehicles have been concerned with the problem of flow separation over its base which has lead to the formation of low pressure circulation region. This pressure is found to be noticeably lower than the free stream atmospheric pressure. Base drag due to such pressure differences can be up to twothirds of the total drag and is principally dictated by base pressure. The present study aims to conduct experiments in order to study the variation of base pressure from an axisymmetric nozzle exit of 10mm diameter. Area ratio i.e. ratio of area of suddenly expanded duct to nozzle exit area considered in this particular study is 4.84. The fundamental control parameters considered in the study are the nozzle pressure ratio (NPR) and length-to-diameter (L/D) ratio which apparently are the inertia and geometric parameters respectively. The tests are conducted for NPR’s ranging from 3 to 11 in steps of 2. Accordingly L/D ratio was considered from 10 to 1 where tests were conducted for L/D 10, 9, 8, 7, 6, 5, 4, 3, 2 and 1. The results showed that for increase in the NPR values once the flow is attached to the duct, the base pressure progressively decreased. Wall pressure distribution throughout the enlarged duct is also studied to understand the oscillatory nature of flow. This work also proposes an effective numerical model for base pressure using Computational Fluid Dynamics (CFD). The computational/numerical model of the axisymmetric nozzle and the enlarged duct was constructed using ANSYS Fluent which is the CFD solver and employed in the present work. Numerical iterations were completed, and the detailed values for base pressure are analyzed. The numerical results were found to agree well with the experimental ones. ISET 2016 2016-02-19 Conference or Workshop Item PeerReviewed application/pdf en http://irep.iium.edu.my/51127/1/51127_Experimental_and_numerical_studies.pdf Quadros, Jaimon Dennis and Khan, Sher Afghan and A. J., Antony and Vas, Jolene S. (2016) Experimental and numerical studies on flow from axisymmetric nozzle flow with sudden expansion for Mach 3.0 using CFD. In: International Conference on Energy Systems and Developments (ICESD2016), 19th-20th Feb. 2016, Pune, India. http://iset2016.com/
repository_type	Digital Repository
institution_category	Local University
institution	International Islamic University Malaysia
building	IIUM Repository
collection	Online Access
language	English
topic	TL500 Aeronautics TL780 Rockets TL787 Astronautics
spellingShingle	TL500 Aeronautics TL780 Rockets TL787 Astronautics Quadros, Jaimon Dennis Khan, Sher Afghan A. J., Antony Vas, Jolene S. Experimental and numerical studies on flow from axisymmetric nozzle flow with sudden expansion for Mach 3.0 using CFD
description	Researches over the recent past in the field of aerodynamic vehicles have been concerned with the problem of flow separation over its base which has lead to the formation of low pressure circulation region. This pressure is found to be noticeably lower than the free stream atmospheric pressure. Base drag due to such pressure differences can be up to twothirds of the total drag and is principally dictated by base pressure. The present study aims to conduct experiments in order to study the variation of base pressure from an axisymmetric nozzle exit of 10mm diameter. Area ratio i.e. ratio of area of suddenly expanded duct to nozzle exit area considered in this particular study is 4.84. The fundamental control parameters considered in the study are the nozzle pressure ratio (NPR) and length-to-diameter (L/D) ratio which apparently are the inertia and geometric parameters respectively. The tests are conducted for NPR’s ranging from 3 to 11 in steps of 2. Accordingly L/D ratio was considered from 10 to 1 where tests were conducted for L/D 10, 9, 8, 7, 6, 5, 4, 3, 2 and 1. The results showed that for increase in the NPR values once the flow is attached to the duct, the base pressure progressively decreased. Wall pressure distribution throughout the enlarged duct is also studied to understand the oscillatory nature of flow. This work also proposes an effective numerical model for base pressure using Computational Fluid Dynamics (CFD). The computational/numerical model of the axisymmetric nozzle and the enlarged duct was constructed using ANSYS Fluent which is the CFD solver and employed in the present work. Numerical iterations were completed, and the detailed values for base pressure are analyzed. The numerical results were found to agree well with the experimental ones.
format	Conference or Workshop Item
author	Quadros, Jaimon Dennis Khan, Sher Afghan A. J., Antony Vas, Jolene S.
author_facet	Quadros, Jaimon Dennis Khan, Sher Afghan A. J., Antony Vas, Jolene S.
author_sort	Quadros, Jaimon Dennis
title	Experimental and numerical studies on flow from axisymmetric nozzle flow with sudden expansion for Mach 3.0 using CFD
title_short	Experimental and numerical studies on flow from axisymmetric nozzle flow with sudden expansion for Mach 3.0 using CFD
title_full	Experimental and numerical studies on flow from axisymmetric nozzle flow with sudden expansion for Mach 3.0 using CFD
title_fullStr	Experimental and numerical studies on flow from axisymmetric nozzle flow with sudden expansion for Mach 3.0 using CFD
title_full_unstemmed	Experimental and numerical studies on flow from axisymmetric nozzle flow with sudden expansion for Mach 3.0 using CFD
title_sort	experimental and numerical studies on flow from axisymmetric nozzle flow with sudden expansion for mach 3.0 using cfd
publisher	ISET 2016
publishDate	2016
url	http://irep.iium.edu.my/51127/ http://irep.iium.edu.my/51127/ http://irep.iium.edu.my/51127/1/51127_Experimental_and_numerical_studies.pdf
first_indexed	2023-09-18T21:12:21Z
last_indexed	2023-09-18T21:12:21Z
_version_	1777411336319270912

Experimental and numerical studies on flow from axisymmetric nozzle flow with sudden expansion for Mach 3.0 using CFD

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