Cover Image

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...

Full description

Saved in:
Bibliographic Details
Main Authors: Haider, Bilal, Mansor, Shuhaimi, Mat, Shabudin, Nasir, Nazri
Format: Book Section
Published: Springer Science and Business Media Deutschland GmbH 2022
Subjects:
TJ Mechanical engineering and machinery
Online Access:http://eprints.utm.my/id/eprint/100733/
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.100733
record_format eprints
spelling my.utm.1007332023-04-30T10:21:48Z http://eprints.utm.my/id/eprint/100733/ 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. Springer Science and Business Media Deutschland GmbH 2022 Book Section 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: Control, Instrumentation and Mechatronics: Theory and Practice. Lecture Notes in Electrical Engineering, 921 (NA). Springer Science and Business Media Deutschland GmbH, Singapore, pp. 13-21. ISBN 978-981193922-8 http://dx.doi.org/10.1007/978-981-19-3923-5_2 DOI: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 Book Section
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
publisher Springer Science and Business Media Deutschland GmbH
publishDate 2022
url http://eprints.utm.my/id/eprint/100733/
http://dx.doi.org/10.1007/978-981-19-3923-5_2
_version_ 1765296695445291008
score 13.211869

Similar Items