Aerodynamics investigation of delta wing at low Reynold’s number

A numerical simulation has been carried out to investigate the aerodynamics of an oscillating delta wing and to evaluate the flow structure over the leading edge at different low Reynolds numbers. The numerical results of the coefficient of lift (CL) vs angle of attack are validated with the experi...

Full description

Bibliographic Details
Main Authors: Hamizi, Ilya Bashiera, Khan, Sher Afghan
Format: Article
Language:English
English
Published: Penerbit Akademia Baru 2019
Subjects:
Online Access:http://irep.iium.edu.my/70862/
http://irep.iium.edu.my/70862/
http://irep.iium.edu.my/70862/1/70862_Aerodynamics%20Investigation%20of%20Delta%20Wing.pdf
http://irep.iium.edu.my/70862/7/70862_Aerodynamics%20investigation%20of%20delta%20wing_SCOPUS.pdf
id iium-70862
recordtype eprints
spelling iium-708622020-01-07T09:01:44Z http://irep.iium.edu.my/70862/ Aerodynamics investigation of delta wing at low Reynold’s number Hamizi, Ilya Bashiera Khan, Sher Afghan TJ Mechanical engineering and machinery TL500 Aeronautics A numerical simulation has been carried out to investigate the aerodynamics of an oscillating delta wing and to evaluate the flow structure over the leading edge at different low Reynolds numbers. The numerical results of the coefficient of lift (CL) vs angle of attack are validated with the experimental results from the previous study. Effects of Reynolds number and angle of attack is investigated for the wing lift coefficient and the aerodynamic efficiency. Pressure contour and turbulence kinetic energy are also observed in each case. Vortex formation from each case is noted from pressure contour and lift coefficient. The stall condition is also observed. Considering the three Reynolds number at max CL, which is an angle of attack of 40 degrees, the CL only increased by 0.01, which is not a very significant increase. But L/D ratio has increased significantly for Reynolds number in the range from 8x104 to 1.5x105 and from Re 1.5x105 to 2.68x105. Whereas for each Reynolds number, the lift coefficient CL seems to attain the highest value of 0.4 at the angle of incidence between 10 degrees and -10 degrees to -20 degrees. Penerbit Akademia Baru 2019-02-09 Article PeerReviewed application/pdf en http://irep.iium.edu.my/70862/1/70862_Aerodynamics%20Investigation%20of%20Delta%20Wing.pdf application/pdf en http://irep.iium.edu.my/70862/7/70862_Aerodynamics%20investigation%20of%20delta%20wing_SCOPUS.pdf Hamizi, Ilya Bashiera and Khan, Sher Afghan (2019) Aerodynamics investigation of delta wing at low Reynold’s number. CFD letters, 11 (2). pp. 32-41. ISSN 2180-1363 http://www.akademiabaru.com/doc/CFDLV11_N2_P32_41.pdf
repository_type Digital Repository
institution_category Local University
institution International Islamic University Malaysia
building IIUM Repository
collection Online Access
language English
English
topic TJ Mechanical engineering and machinery
TL500 Aeronautics
spellingShingle TJ Mechanical engineering and machinery
TL500 Aeronautics
Hamizi, Ilya Bashiera
Khan, Sher Afghan
Aerodynamics investigation of delta wing at low Reynold’s number
description A numerical simulation has been carried out to investigate the aerodynamics of an oscillating delta wing and to evaluate the flow structure over the leading edge at different low Reynolds numbers. The numerical results of the coefficient of lift (CL) vs angle of attack are validated with the experimental results from the previous study. Effects of Reynolds number and angle of attack is investigated for the wing lift coefficient and the aerodynamic efficiency. Pressure contour and turbulence kinetic energy are also observed in each case. Vortex formation from each case is noted from pressure contour and lift coefficient. The stall condition is also observed. Considering the three Reynolds number at max CL, which is an angle of attack of 40 degrees, the CL only increased by 0.01, which is not a very significant increase. But L/D ratio has increased significantly for Reynolds number in the range from 8x104 to 1.5x105 and from Re 1.5x105 to 2.68x105. Whereas for each Reynolds number, the lift coefficient CL seems to attain the highest value of 0.4 at the angle of incidence between 10 degrees and -10 degrees to -20 degrees.
format Article
author Hamizi, Ilya Bashiera
Khan, Sher Afghan
author_facet Hamizi, Ilya Bashiera
Khan, Sher Afghan
author_sort Hamizi, Ilya Bashiera
title Aerodynamics investigation of delta wing at low Reynold’s number
title_short Aerodynamics investigation of delta wing at low Reynold’s number
title_full Aerodynamics investigation of delta wing at low Reynold’s number
title_fullStr Aerodynamics investigation of delta wing at low Reynold’s number
title_full_unstemmed Aerodynamics investigation of delta wing at low Reynold’s number
title_sort aerodynamics investigation of delta wing at low reynold’s number
publisher Penerbit Akademia Baru
publishDate 2019
url http://irep.iium.edu.my/70862/
http://irep.iium.edu.my/70862/
http://irep.iium.edu.my/70862/1/70862_Aerodynamics%20Investigation%20of%20Delta%20Wing.pdf
http://irep.iium.edu.my/70862/7/70862_Aerodynamics%20investigation%20of%20delta%20wing_SCOPUS.pdf
first_indexed 2023-09-18T21:40:35Z
last_indexed 2023-09-18T21:40:35Z
_version_ 1777413113212043264