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Wingtip vortex reduction study/Lim Shih Chun

Wingtip vortex reduction study_Lim Shih Chun_A2_2011_NI
Vortex hujung sayap berlaku di sekeliling hujung sayap apabila kapal terbang terbang, fenomena ini tidak dapat dielakkan bagi sayap tiga dimensi. Daya heretan akan berlaku disebabkan oleh vortex hujung sayap. Oleh sebab itu, pengurangan vortex hujung sayap sangat penting untuk sesebuah kapal terbang. Satu penyelidikan tentang vortex hujung sayap bagi NACA 4415 model sayap telah dijalankan. Analisa melalui simulasi bagi pelarut berbeza, “meshing” saiz, dan sudut serangan telah diambil kira untuk mendapatkan keputusan analisa yang jitu, tepat dan memuaskan untuk dibanding dengan data-data eksperimen lepas. Objektif utama untuk kajian ini adalah untuk mendapatkan idea baru bagi mengurangkan vortex hujung sayap selain daripada mengguna vortex hujung sayap mechanism yang sedia ada seperti “winglets”, “tip-sails”, “delta sail”, “wing-grid” dan sebagainya. Idea baru ini menggunakan satu 8mm diameter tiupan jet di tepi hujung sayap untuk mengubah arah vortex hujung sayap. Namun, idea ini disimulasikan sebagai tiupan angin di dalam Komputasi Dinamik Bendalir tanpa mengambil kira keluasan dan bentuk tiupan jet tersebut. Kajian tersebut telah menunjukkan keputusan yang memuaskan di hujung sayap. Pengenalan dan kajian berikutnya diperkenalkan untuk melengkapkan dan membuktikan bahawa idea ini boleh dipraktikkan. Kata Kunci: Komputasi Dinamik Bendalir, vortex hujung sayap, tiupan jet ______________________________________________________________________________________ The wing tip vortex occurs in the wing tip neighborhood on an aircraft in flight, and cannot be avoided for three-dimensional wing. Hence, the induced drag is generated by the wing tip vortex. So the reduction of the wing tip vortex is very important problem for an aircraft. A study of wing tip vortices on NACA 4415 wing model is presented. Numerical simulation with different solver, meshing size and angle of attack has been carried out to obtain the accurate results for NACA 4415 wing model and validate with the experimental data from the research which has been done before. The main objective of this research is to find an alternative method to reduce the wing tip vortex instead of using the conventional wing tip vortex reduction devices such as winglets, tip-sails, delta tip, wing-grid and etc. The idea is by using the blowing vent at the side of the wing in an attempt to alter the flow field around the tip. However, this case is simulated in Computational Fluid Dynamics (CFD) as a flow blowing at the side of the wing without considering the shape and size of the blowing vent’s nozzle. The study has produced promising results showing that one chordwise 8mm in diameter blowing vent implemented near the tip can influence the flow favorably. Recommendations and future works have been made in order to practically verify the data obtained by using Computational Fluid Dynamics (CFD) with experimental data for this case. Keywords: CFD, wing tip vortex, blowing vent
Contributor(s):
Lim Shih Chun - Author
Primary Item Type:
Final Year Project
Language:
English
Subject Keywords:
CFD ; wing tip vortex ; blowing vent
First presented to the public:
5/1/2011
Original Publication Date:
8/1/2019
Previously Published By:
Universiti Sains Malaysia
Place Of Publication:
School of Aerospace Engineering
Citation:
Extents:
Number of Pages - 80
License Grantor / Date Granted:
  / ( View License )
Date Deposited
2019-08-01 14:29:15.125
Submitter:
Nor Hayati Ismail

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