Studi Eksperimental Dan Numerik Efek Fairing Leading Edge Terhadap Separasi Aliran Tiga Dimensi Pada Wing-Body Junction

Rozi, Khoiri (2009) Studi Eksperimental Dan Numerik Efek Fairing Leading Edge Terhadap Separasi Aliran Tiga Dimensi Pada Wing-Body Junction. Masters thesis, Institut Teknologi Sepuluh Nopember.

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Abstract

Penelitian ini bertujuan mengamati pengaruh fairing leading edge terhadap struktur aliran melewati wing body junction profil asimetris dengan divariasikan angle of attack. Kajian dilakukan secara eksperimental dan numerik dengan teknik visualisasi skin friction line atau pathlines pada permukaan endwall. Hasil eksperimen dan simulasi dengan CFD ditemukan perubahan struktur aliran dengan modifikasi leading edge.. Adanya fairing ditemukan posisi saddle point semakin mendekat leading edge dan kurva imprint horseshoe vortex lebih sempit. Sedangkan dengan bertambhanya angle of attack ditemukan posisi saddle point bergerak menjauh dari leading edge dengan kurva imprint horseshoe vortex menjadi lebih lebar. Fenomena ini secara jelas menunjukkan perubahan wall shear angle (Pr) dan sudut distorsi orientasi vortisitas boundary layer (Bz) akibat cross flow dan deformasi angular dengan adanya perubahan kelengkungan leading edge dan angle of attack. Modifikasi geometri wing body junction dengan fairing leading edge dapat menghasilkan karakteristik aerodinamis lebih baik daripada geometri wing body junction tanpa fairing.
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The research is purposed to investigate fairing leading edge effect to flow structure through the wing body junction by unsymmetrical profile with angle of attack variation. The study is conducted by experimental and numerically with visualization technique for skin friction line or pathlines on wall surface. The results of experiments and CFD simulation showed change of flow structure through leading edge modification. There is fairing showed saddle point position more close to leading edge and imprint horseshoe vortex curve more closed. Therefore, with as increasing angle of attack then showed that saddle point position move away from leading edge and imprint horseshoe vortex curve became more opened. The phenomena is obviously to show that wall shear angle (Br) and reorientation vorticity of boundary layer distorted (Bz) duo to cross flow effect and angular deformation that causes by change of leading edge curve and angle of attack. Modification of wing body junction geometry by fairing leading edge can be result aerodynamics characteristic more than better that result by wing body junction geometry without fairing.

Item Type:	Thesis (Masters)
Additional Information:	RTM 620.106 4 Roz s 2009 3100009035226 (WEEDING)
Uncontrolled Keywords:	fairing, skin friction line, pathlines, saddle point, horseshoe vortex, wall shear angle, boundary layer, angle of attack.
Subjects:	Q Science > QC Physics > QC151 Fluid dynamics T Technology > TJ Mechanical engineering and machinery > TJ935 Pipe--Fluid dynamics. Tubes--Fluid dynamics
Divisions:	Faculty of Industrial Technology > Mechanical Engineering > 21101-(S2) Master Thesis
Depositing User:	Anis Wulandari
Date Deposited:	11 Mar 2026 05:28
Last Modified:	11 Mar 2026 05:28
URI:	http://repository.its.ac.id/id/eprint/132722

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