Cover Image

Experimental study of Bias Acoustic Liner on nacelle lip-skin/ Qummare Azam ...[et al.]

The paper demonstrates the effect of Bias Acoustic Liner for nacelle lip-skin for civil aircraft. The effect of drag on nacelle lip-skin porous surface profile with liner. Additionally, the absorption of noise that reduced by using of Bias acoustic liner has been discussed. An acoustically absorbent...

Full description

Saved in:
Bibliographic Details
Main Authors: Azam1,, Qummare, Ismail1*, Mohd Azmi, Mazlan2, Nurul Musfirah
Format: Article
Language:English
Published: Faculty of Mechanical Engineering Universiti Teknologi MARA (UiTM) 2018
Subjects:
Engineering mathematics. Engineering analysis
TJ Mechanical engineering and machinery
Online Access:http://ir.uitm.edu.my/id/eprint/39373/1/39373.pdf
http://ir.uitm.edu.my/id/eprint/39373/
Tags: Add Tag
No Tags, Be the first to tag this record!
id my.uitm.ir.39373
record_format eprints
spelling my.uitm.ir.393732020-12-21T01:11:17Z http://ir.uitm.edu.my/id/eprint/39373/ Experimental study of Bias Acoustic Liner on nacelle lip-skin/ Qummare Azam ...[et al.] Azam1,, Qummare Ismail1*, Mohd Azmi Mazlan2, Nurul Musfirah Engineering mathematics. Engineering analysis TJ Mechanical engineering and machinery The paper demonstrates the effect of Bias Acoustic Liner for nacelle lip-skin for civil aircraft. The effect of drag on nacelle lip-skin porous surface profile with liner. Additionally, the absorption of noise that reduced by using of Bias acoustic liner has been discussed. An acoustically absorbent material is employed with honeycomb liner for the required acoustic attenuation features for the aircraft engines. The BAL system behaves differently at different positions, around the rotor fan to absorb the fan noise; however, at the nacelle position along with anti-icing system, it shows dual nature i.e., noise reduction as well as drag reduction by using of bias flow through the micro-channels of the liner. The experiment runs between 00-50 (degree) angle of attack and Reynolds no. 2.2×105 to 5.8×105 to achieve drag reduction by 22%. At 20 angles of attack found the effective inclination for drag reduction. Backplate using at the large area over where the acoustic reducing material is used from the close source. In this paper, we will also discuss briefly Bias Acoustic Liner applications in aircraft engines. Faculty of Mechanical Engineering Universiti Teknologi MARA (UiTM) 2018 Article PeerReviewed text en http://ir.uitm.edu.my/id/eprint/39373/1/39373.pdf Azam1,, Qummare and Ismail1*, Mohd Azmi and Mazlan2, Nurul Musfirah (2018) Experimental study of Bias Acoustic Liner on nacelle lip-skin/ Qummare Azam ...[et al.]. Journal of Mechanical Engineering (JMechE), SI 5 (2). pp. 67-77. ISSN 18235514
institution Universiti Teknologi Mara
building Tun Abdul Razak Library
collection Institutional Repository
continent Asia
country Malaysia
content_provider Universiti Teknologi Mara
content_source UiTM Institutional Repository
url_provider http://ir.uitm.edu.my/
language English
topic Engineering mathematics. Engineering analysis
TJ Mechanical engineering and machinery
spellingShingle Engineering mathematics. Engineering analysis
TJ Mechanical engineering and machinery
Azam1,, Qummare
Ismail1*, Mohd Azmi
Mazlan2, Nurul Musfirah
Experimental study of Bias Acoustic Liner on nacelle lip-skin/ Qummare Azam ...[et al.]
description The paper demonstrates the effect of Bias Acoustic Liner for nacelle lip-skin for civil aircraft. The effect of drag on nacelle lip-skin porous surface profile with liner. Additionally, the absorption of noise that reduced by using of Bias acoustic liner has been discussed. An acoustically absorbent material is employed with honeycomb liner for the required acoustic attenuation features for the aircraft engines. The BAL system behaves differently at different positions, around the rotor fan to absorb the fan noise; however, at the nacelle position along with anti-icing system, it shows dual nature i.e., noise reduction as well as drag reduction by using of bias flow through the micro-channels of the liner. The experiment runs between 00-50 (degree) angle of attack and Reynolds no. 2.2×105 to 5.8×105 to achieve drag reduction by 22%. At 20 angles of attack found the effective inclination for drag reduction. Backplate using at the large area over where the acoustic reducing material is used from the close source. In this paper, we will also discuss briefly Bias Acoustic Liner applications in aircraft engines.
format Article
author Azam1,, Qummare
Ismail1*, Mohd Azmi
Mazlan2, Nurul Musfirah
author_facet Azam1,, Qummare
Ismail1*, Mohd Azmi
Mazlan2, Nurul Musfirah
author_sort Azam1,, Qummare
title Experimental study of Bias Acoustic Liner on nacelle lip-skin/ Qummare Azam ...[et al.]
title_short Experimental study of Bias Acoustic Liner on nacelle lip-skin/ Qummare Azam ...[et al.]
title_full Experimental study of Bias Acoustic Liner on nacelle lip-skin/ Qummare Azam ...[et al.]
title_fullStr Experimental study of Bias Acoustic Liner on nacelle lip-skin/ Qummare Azam ...[et al.]
title_full_unstemmed Experimental study of Bias Acoustic Liner on nacelle lip-skin/ Qummare Azam ...[et al.]
title_sort experimental study of bias acoustic liner on nacelle lip-skin/ qummare azam ...[et al.]
publisher Faculty of Mechanical Engineering Universiti Teknologi MARA (UiTM)
publishDate 2018
url http://ir.uitm.edu.my/id/eprint/39373/1/39373.pdf
http://ir.uitm.edu.my/id/eprint/39373/
_version_ 1687396771300376576
score 13.211869

Similar Items