Cover Image

Determination of wall pressure flows at supersonic Mach numbers

This article investigates the wall pressure dissemination on a circular duct when the flow is exhausted into a CD nozzle. This study aims at to scrutinize the static pressure on the duct wall and its growth when the control is activated. The microjets are employed at the base at pitch circle radius...

Full description

Saved in:
Bibliographic Details
Main Authors: Aabid, Abdul, Khan, Sher Afghan
Format: Article
Language:English
English
Published: Elsevier Ltd Kidlington Corporate Office, Kidlington, United Kingdom 2020
Subjects:
TL Motor vehicles. Aeronautics. Astronautics
Online Access:http://irep.iium.edu.my/81933/1/supersonic%20mach%20numbers.pdf
http://irep.iium.edu.my/81933/7/81933_Determination%20of%20wall%20pressure%20flows_Scopus.pdf
http://irep.iium.edu.my/81933/
http://www.elsevier.com/locate/matpr
https://doi.org/10.1016/j.matpr.2020.06.538
Tags: Add Tag
No Tags, Be the first to tag this record!
id my.iium.irep.81933
record_format dspace
spelling my.iium.irep.819332021-04-11T04:52:45Z http://irep.iium.edu.my/81933/ Determination of wall pressure flows at supersonic Mach numbers Aabid, Abdul Khan, Sher Afghan TL Motor vehicles. Aeronautics. Astronautics This article investigates the wall pressure dissemination on a circular duct when the flow is exhausted into a CD nozzle. This study aims at to scrutinize the static pressure on the duct wall and its growth when the control is activated. The microjets are employed at the base at pitch circle radius (PCR) of 6.5 mm, and the radius of the microjets are 0.5 mm. The Mach numbers and the duct area ratio used are 2.56, Mach (M) 2 and 3. The lift to diameter ratio (L/D) and nozzle pressure ratio (NPR) of the study were from L/D = 10 to 1 and NPRs from 3 to 11. The NPRs tested were at different expansion level for M = 2. The oscillations in the duct flow field are seen when they are under expanded, and this trend continues for the total length of pipe. When the nozzles are ideally expanded the oscillations are absent as at this NPR only the Mach waves will be present. Similar trends are also seen at NPR 3 as well as whenever there is an adverse pressure gradient at Mach 2. With the decline in pipe length, the wavy nature of the flow is getting died out, and pressure recovery is smooth. The duct length and the backpressure has a crucial role to play in dictating the magnitude of wall pressure. L/D = 2 seems to be sufficient for M = 2 to continue to remain committed with the pipe, whereas for M = 3 the lowest duct size required is L/D = 4. Elsevier Ltd Kidlington Corporate Office, Kidlington, United Kingdom 2020-07-30 Article PeerReviewed application/pdf en http://irep.iium.edu.my/81933/1/supersonic%20mach%20numbers.pdf application/pdf en http://irep.iium.edu.my/81933/7/81933_Determination%20of%20wall%20pressure%20flows_Scopus.pdf Aabid, Abdul and Khan, Sher Afghan (2020) Determination of wall pressure flows at supersonic Mach numbers. Materials Today, 38. pp. 2347-2352. ISSN 2214-7853 http://www.elsevier.com/locate/matpr https://doi.org/10.1016/j.matpr.2020.06.538
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 TL Motor vehicles. Aeronautics. Astronautics
spellingShingle TL Motor vehicles. Aeronautics. Astronautics
Aabid, Abdul
Khan, Sher Afghan
Determination of wall pressure flows at supersonic Mach numbers
description This article investigates the wall pressure dissemination on a circular duct when the flow is exhausted into a CD nozzle. This study aims at to scrutinize the static pressure on the duct wall and its growth when the control is activated. The microjets are employed at the base at pitch circle radius (PCR) of 6.5 mm, and the radius of the microjets are 0.5 mm. The Mach numbers and the duct area ratio used are 2.56, Mach (M) 2 and 3. The lift to diameter ratio (L/D) and nozzle pressure ratio (NPR) of the study were from L/D = 10 to 1 and NPRs from 3 to 11. The NPRs tested were at different expansion level for M = 2. The oscillations in the duct flow field are seen when they are under expanded, and this trend continues for the total length of pipe. When the nozzles are ideally expanded the oscillations are absent as at this NPR only the Mach waves will be present. Similar trends are also seen at NPR 3 as well as whenever there is an adverse pressure gradient at Mach 2. With the decline in pipe length, the wavy nature of the flow is getting died out, and pressure recovery is smooth. The duct length and the backpressure has a crucial role to play in dictating the magnitude of wall pressure. L/D = 2 seems to be sufficient for M = 2 to continue to remain committed with the pipe, whereas for M = 3 the lowest duct size required is L/D = 4.
format Article
author Aabid, Abdul
Khan, Sher Afghan
author_facet Aabid, Abdul
Khan, Sher Afghan
author_sort Aabid, Abdul
title Determination of wall pressure flows at supersonic Mach numbers
title_short Determination of wall pressure flows at supersonic Mach numbers
title_full Determination of wall pressure flows at supersonic Mach numbers
title_fullStr Determination of wall pressure flows at supersonic Mach numbers
title_full_unstemmed Determination of wall pressure flows at supersonic Mach numbers
title_sort determination of wall pressure flows at supersonic mach numbers
publisher Elsevier Ltd Kidlington Corporate Office, Kidlington, United Kingdom
publishDate 2020
url http://irep.iium.edu.my/81933/1/supersonic%20mach%20numbers.pdf
http://irep.iium.edu.my/81933/7/81933_Determination%20of%20wall%20pressure%20flows_Scopus.pdf
http://irep.iium.edu.my/81933/
http://www.elsevier.com/locate/matpr
https://doi.org/10.1016/j.matpr.2020.06.538
_version_ 1696976065795194880
score 13.211869

Similar Items