Combined effect of nozzle pressure ratio and screech prone supersonic mach number in a suddenly expanded flow

This paper presents the results of an experimental study to evaluate the effectiveness of the micro jets to control the base pressure in a suddenly expanded flow at supersonic Mach numbers. Four micro jets of 1mm orifice diameter located at 90 intervals along a pitch circle diameter of 1.3 times th...

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Main Authors:	Bashir, Musavir, Khan, Sher Afghan, Rajendran, Parvathy
Format:	Conference or Workshop Item
Language:	English
Published:	2015
Subjects:	TL500 Aeronautics TL780 Rockets
Online Access:	http://irep.iium.edu.my/46658/ http://irep.iium.edu.my/46658/1/46658.pdf

id	iium-46658
recordtype	eprints
spelling	iium-466582016-05-24T01:11:30Z http://irep.iium.edu.my/46658/ Combined effect of nozzle pressure ratio and screech prone supersonic mach number in a suddenly expanded flow Bashir, Musavir Khan, Sher Afghan Rajendran, Parvathy TL500 Aeronautics TL780 Rockets This paper presents the results of an experimental study to evaluate the effectiveness of the micro jets to control the base pressure in a suddenly expanded flow at supersonic Mach numbers. Four micro jets of 1mm orifice diameter located at 90 intervals along a pitch circle diameter of 1.3 times the nozzle exit diameter in the base region were employed as active controls. The Mach numbers of the present study were 1.8 and 2.0. The jets were expanded suddenly into an axi-symmetric circular tube with cross-sectional area 2.56, 3.24, 4.84 and 6.25 times that of the nozzle exit area. The Length to Diameter ratio of the suddenly expanded duct was varied from 10 to 1 and experiment were conducted for Nozzle Pressure Ratio (NPR) from 3 to 11. Jets were over, under, and correctly expanded depending upon the NPR of the respective runs. When flow from the nozzle was over expanded or under expanded an oblique shock or expansion fan will be positioned at the nozzle lip, which in turn will result in increase or decrease of the base pressure. From the results it was observed that at NPRs 3 the control was not effective, however, at NPR 5, 7, 9, and 11 a significant change in the base pressure for all the area ratios was seen. From the results it was concluded that the level of expansion, Mach number, length-to-diameter ratio, and area ratio played an important role to fix the value of the base pressure and the control effectiveness by the micro jets. 2015-12-03 Conference or Workshop Item PeerReviewed application/pdf en http://irep.iium.edu.my/46658/1/46658.pdf Bashir, Musavir and Khan, Sher Afghan and Rajendran, Parvathy (2015) Combined effect of nozzle pressure ratio and screech prone supersonic mach number in a suddenly expanded flow. In: International Conference on Mechanical Engineering And Advanced Material (ICME-AM) 2015, 3rd-4th Dec. 2015, Kota Kinabalu, Sabah.
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
spellingShingle	TL500 Aeronautics TL780 Rockets Bashir, Musavir Khan, Sher Afghan Rajendran, Parvathy Combined effect of nozzle pressure ratio and screech prone supersonic mach number in a suddenly expanded flow
description	This paper presents the results of an experimental study to evaluate the effectiveness of the micro jets to control the base pressure in a suddenly expanded flow at supersonic Mach numbers. Four micro jets of 1mm orifice diameter located at 90 intervals along a pitch circle diameter of 1.3 times the nozzle exit diameter in the base region were employed as active controls. The Mach numbers of the present study were 1.8 and 2.0. The jets were expanded suddenly into an axi-symmetric circular tube with cross-sectional area 2.56, 3.24, 4.84 and 6.25 times that of the nozzle exit area. The Length to Diameter ratio of the suddenly expanded duct was varied from 10 to 1 and experiment were conducted for Nozzle Pressure Ratio (NPR) from 3 to 11. Jets were over, under, and correctly expanded depending upon the NPR of the respective runs. When flow from the nozzle was over expanded or under expanded an oblique shock or expansion fan will be positioned at the nozzle lip, which in turn will result in increase or decrease of the base pressure. From the results it was observed that at NPRs 3 the control was not effective, however, at NPR 5, 7, 9, and 11 a significant change in the base pressure for all the area ratios was seen. From the results it was concluded that the level of expansion, Mach number, length-to-diameter ratio, and area ratio played an important role to fix the value of the base pressure and the control effectiveness by the micro jets.
format	Conference or Workshop Item
author	Bashir, Musavir Khan, Sher Afghan Rajendran, Parvathy
author_facet	Bashir, Musavir Khan, Sher Afghan Rajendran, Parvathy
author_sort	Bashir, Musavir
title	Combined effect of nozzle pressure ratio and screech prone supersonic mach number in a suddenly expanded flow
title_short	Combined effect of nozzle pressure ratio and screech prone supersonic mach number in a suddenly expanded flow
title_full	Combined effect of nozzle pressure ratio and screech prone supersonic mach number in a suddenly expanded flow
title_fullStr	Combined effect of nozzle pressure ratio and screech prone supersonic mach number in a suddenly expanded flow
title_full_unstemmed	Combined effect of nozzle pressure ratio and screech prone supersonic mach number in a suddenly expanded flow
title_sort	combined effect of nozzle pressure ratio and screech prone supersonic mach number in a suddenly expanded flow
publishDate	2015
url	http://irep.iium.edu.my/46658/ http://irep.iium.edu.my/46658/1/46658.pdf
first_indexed	2023-09-18T21:06:25Z
last_indexed	2023-09-18T21:06:25Z
_version_	1777410963868221440

Combined effect of nozzle pressure ratio and screech prone supersonic mach number in a suddenly expanded flow

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