Studi aliran 3-D near endwall pada interaksi airfoil dan plat datar tanpa pengaruh clearence (kasus variasi geometri dan angle of attack)

Rachman, Arfidian (2005) Studi aliran 3-D near endwall pada interaksi airfoil dan plat datar tanpa pengaruh clearence (kasus variasi geometri dan angle of attack). Other thesis, Institut Teknologi Sepuluh Nopember.

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Abstract

Kajian-kajian mengenai keberadaan struktur aliran sekunder ini didasarkan pada efek munculnya aliran sekunder pada konfigurasi wing-body pada pesawat terbang, yaitu adanya wingtip-vortex pada tip region dan terciptanya beberapa unsur aliran vortex pada daerah sambungan (endwall region). Keduanya bersama-sama akan menyebabkan blockage aliran utama. Adanya efek blockage ini akan memengaruhi karakteristik aerodinamis lift dan drag, di mana hal ini secara langsung berpengaruh terhadap efektivitas dan efisiensi wing.

Studi eksperimen yang telah dilakukan oleh peneliti sebelumnya menunjukkan bahwa tip-vortex terbentuk semakin kuat seiring membesarnya angle of attack. Hal ini diindikasikan dengan kemiringan defleksi barisan skin friction line menuju midspan yang semakin tajam pada upper surface. Pada daerah endwall, fenomena yang bisa diamati adalah terjadinya pergeseran posisi saddle point menuju pressure side. Sedangkan dari kontur isobar ditemukan pergerakan titik minimum pressure pada upper surface semakin mendekati leading edge, dan area maximum pressure pada lower surface bergerak menuju ke minimum pressure pada upper side.

Penelitian yang dilakukan dengan uji numerik dan eksperimental pada tiga buah variasi geometri wing yang dimodelkan pada flat plate dengan variasi angle of attack (α) = 0°, 8°, dan 12°. Hasil yang akan didapat berupa isobar contour pada endwall yang semakin menuju leading edge seiring meningkatnya efek source dan angle of attack serta flow visualization pada endwall dan body.
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The study concerning the existence of this secondary flow structure is based on the effect of the appearance of secondary flow in the wing-body configuration of an aircraft, namely the existence of wingtip-vortex at the tip region and the creation of several vortex flow elements at the junction area (endwall region). Both together will cause blockage of the main flow. The existence of this blockage effect will influence the aerodynamic characteristics of lift and drag, which directly affects the effectiveness and efficiency of the wing.

Experimental studies conducted by previous researchers indicate that the tip-vortex becomes stronger as the angle of attack increases. This is indicated by the increasingly steep deflection of the skin friction lines toward the midspan on the upper surface. In the endwall region, the observable phenomenon is the displacement of the saddle point toward the pressure side. Meanwhile, from the isobar contour, the movement of the minimum-pressure point on the upper surface is found to progressively approach the leading edge, while the area of maximum pressure on the lower surface moves toward the minimum-pressure area on the upper side.

The research will be conducted using numerical and experimental tests on three variations of wing geometry modeled on a flat plate with variations in the angle of attack of 0°, 8°, and 12°. The results will be obtained in the form of isobar contours at the endwall and body, as well as flow visualization at the endwall and body.

Item Type:	Thesis (Other)
Additional Information:	629.134 32 Rac s
Uncontrolled Keywords:	secondary flow, tip-vortex, horseshoe vortex, wing-tip, endwall, skin-friction line, saddle point, pressure side, contour isobar, angle of attack, secondary flow, tip-vortex, horseshoe vortex, wing-tip, endwall, skinfriction line, saddle point, pressure side, contour isobar, angle of attack.
Subjects:	T Technology > TL Motor vehicles. Aeronautics. Astronautics > TL521 Aerodynamics, Hypersonic.
Divisions:	Faculty of Industrial Technology > Mechanical Engineering > 21101-(S2) Master Thesis
Depositing User:	magang .
Date Deposited:	07 Oct 2026 06:39
Last Modified:	07 Oct 2026 06:39
URI:	http://repository.its.ac.id/id/eprint/145388

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