Flow visualisation over the low sweep unmanned combat aerial vehicle (UCAV) configuration
Steady-state experimental and computational studies on a lambda planform low sweep MULti-DIsciplinary CONfiguration (MULDICON) Unmanned Combat Aerial Vehicle (UCAV) configuration with 53° blunt leading-edge sweep are presented. The experiments were carried out in Universiti Teknologi Malaysia Low-Sp...
Saved in:
Main Authors: | , , , |
---|---|
Format: | Conference or Workshop Item |
Published: |
2022
|
Subjects: | |
Online Access: | http://eprints.utm.my/id/eprint/99360/ http://dx.doi.org/10.1007/978-981-19-3923-5_2 |
Tags: |
Add Tag
No Tags, Be the first to tag this record!
|
id |
my.utm.99360 |
---|---|
record_format |
eprints |
spelling |
my.utm.993602023-02-22T08:43:42Z http://eprints.utm.my/id/eprint/99360/ Flow visualisation over the low sweep unmanned combat aerial vehicle (UCAV) configuration Haider, Bilal Mansor, Shuhaimi Mat, Shabudin Nasir, Nazri TJ Mechanical engineering and machinery Steady-state experimental and computational studies on a lambda planform low sweep MULti-DIsciplinary CONfiguration (MULDICON) Unmanned Combat Aerial Vehicle (UCAV) configuration with 53° blunt leading-edge sweep are presented. The experiments were carried out in Universiti Teknologi Malaysia Low-Speed wind Tunnel (UTM-LST), and the computational work was done using Ansys Fluent. The flow visualisation for experimental and computational was performed at 30 m/s corresponding to the Reynolds number of 4.50E+05, for the angle of attack, α = 5°, 10°, 15°, 20°. Surface flow visualisation results confirmed the onset and progression of flow separation for low sweep lambda wing configuration. The experimental and the computational results demonstrated that the low sweep MULDICON wing lambda configuration is encountered with highly complex and nonlinear aerodynamic flow behaviour. Especially at high angle of attack (AOA), such as leading-edge vortices separation, vortex breakdown (suggested by strong shear layer region behind the leading-edge vortex) and shear layer reattachment that increases with the incidence increase. The computational results compared well to the experimental flow visualisation results. 2022 Conference or Workshop Item PeerReviewed Haider, Bilal and Mansor, Shuhaimi and Mat, Shabudin and Nasir, Nazri (2022) Flow visualisation over the low sweep unmanned combat aerial vehicle (UCAV) configuration. In: CIM 2022: The 3rd International Conference on Control, Instrumentation and Mechatronics Engineering, 30th – 31st of March2022, Virtual, Online. http://dx.doi.org/10.1007/978-981-19-3923-5_2 |
institution |
Universiti Teknologi Malaysia |
building |
UTM Library |
collection |
Institutional Repository |
continent |
Asia |
country |
Malaysia |
content_provider |
Universiti Teknologi Malaysia |
content_source |
UTM Institutional Repository |
url_provider |
http://eprints.utm.my/ |
topic |
TJ Mechanical engineering and machinery |
spellingShingle |
TJ Mechanical engineering and machinery Haider, Bilal Mansor, Shuhaimi Mat, Shabudin Nasir, Nazri Flow visualisation over the low sweep unmanned combat aerial vehicle (UCAV) configuration |
description |
Steady-state experimental and computational studies on a lambda planform low sweep MULti-DIsciplinary CONfiguration (MULDICON) Unmanned Combat Aerial Vehicle (UCAV) configuration with 53° blunt leading-edge sweep are presented. The experiments were carried out in Universiti Teknologi Malaysia Low-Speed wind Tunnel (UTM-LST), and the computational work was done using Ansys Fluent. The flow visualisation for experimental and computational was performed at 30 m/s corresponding to the Reynolds number of 4.50E+05, for the angle of attack, α = 5°, 10°, 15°, 20°. Surface flow visualisation results confirmed the onset and progression of flow separation for low sweep lambda wing configuration. The experimental and the computational results demonstrated that the low sweep MULDICON wing lambda configuration is encountered with highly complex and nonlinear aerodynamic flow behaviour. Especially at high angle of attack (AOA), such as leading-edge vortices separation, vortex breakdown (suggested by strong shear layer region behind the leading-edge vortex) and shear layer reattachment that increases with the incidence increase. The computational results compared well to the experimental flow visualisation results. |
format |
Conference or Workshop Item |
author |
Haider, Bilal Mansor, Shuhaimi Mat, Shabudin Nasir, Nazri |
author_facet |
Haider, Bilal Mansor, Shuhaimi Mat, Shabudin Nasir, Nazri |
author_sort |
Haider, Bilal |
title |
Flow visualisation over the low sweep unmanned combat aerial vehicle (UCAV) configuration |
title_short |
Flow visualisation over the low sweep unmanned combat aerial vehicle (UCAV) configuration |
title_full |
Flow visualisation over the low sweep unmanned combat aerial vehicle (UCAV) configuration |
title_fullStr |
Flow visualisation over the low sweep unmanned combat aerial vehicle (UCAV) configuration |
title_full_unstemmed |
Flow visualisation over the low sweep unmanned combat aerial vehicle (UCAV) configuration |
title_sort |
flow visualisation over the low sweep unmanned combat aerial vehicle (ucav) configuration |
publishDate |
2022 |
url |
http://eprints.utm.my/id/eprint/99360/ http://dx.doi.org/10.1007/978-981-19-3923-5_2 |
_version_ |
1758950350635663360 |
score |
13.18916 |