Studi Eksperimen Pengaruh Penambahan Vortex Generator Tipe Triangular Terhadap Performa Aerodinamis Sayap UAV Arnayadirga Bayucaraka ITS

Sebastian, Johan Elbert (2022) Studi Eksperimen Pengaruh Penambahan Vortex Generator Tipe Triangular Terhadap Performa Aerodinamis Sayap UAV Arnayadirga Bayucaraka ITS. Other thesis, Institut Teknologi Sepuluh Nopember.

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Abstract

Teknologi Unmanned Aerial Vehicle (UAV) kini sudah berkembang pesat dan banyak aplikasinya, hingga pemerintah menyelenggarakan Kontes Robot Terbang Indonesia (KRTI) untuk memacu perkembangannya di Indonesia. Dalam salah satu kategorinya, Fixed Wing dengan misi pemetaan dan pengamatan, sering ditemukan masalah dimana kapasitas baterai yang tersedia tidak cukup karena payload yang berat dan sebagian besar dayanya habis saat take off. Masalah tersebut dapat diatasi dengan mengoptimasi airfoil agar mampu menghasilkan lift yang besar dengan menambahkan vortex generator yang bertujuan menunda separasi aliran pada sayap pesawat, sehingga daya yang dihabiskan saat take off lebih kecil. Penelitian ini dilakukan secara eksperimen menggunakan terowongan angin yang ada di Departemen Teknik Mesin FT-IRS ITS dengan ukuran test section 660 x 660 x 2000 mm dan kecepatan maksimum 15 m/s, serta alat ukur drag and lift balance dan manometer digital. Model dari penelitian ini adalah sayap UAV Arnayadirga dengan profil airfoil NACA 2312 dan bentuk tapered tanpa dan dengan vortex generator. Vortex generator berbentuk triangular terpasang pada x/c = 0,2 dengan konfigurasi counter-rotating. Hasil penelitian ini menunjukkan bahwa penambahan vortex generator pada upper side sayap UAV meningkatkan lift pada sudut serang 0⁰ hingga stall angle, namun setelah stall angle nilai lift-nya justru lebih rendah dari model plain. Penambahan vortex generator juga menurunkan drag dan meningkatkan performa sayap, namun juga menurunkan optimum angle of attack. Penambahan vortex generator juga mempengaruhi distribusi pressure coefficient upper side sayap pada sudut serang 0⁰ dan 8⁰ menjadi lebih negatif, sedangkan pada sudut serang 16⁰ distribusi pressure coefficient justru lebih positif tetapi mampu menunda separasi aliran. Distribusi pressure coefficient pada lower side sayap tidak berubah secara signifikan akibat penambahan vortex generator. Hasil penelitian juga menunjukkan penambahan vortex generator pada bilangan Reynolds yang lebih besar menghasilkan efek yang lebih besar, maka dapat dikatakan penambahan vortex generator akan menguntungkan bagi UAV karena UAV beroperasi pada bilangan Reynolds yang lebih besar.
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Unmanned Aerial Vehicle (UAV) technology has developed rapidly and now has many applications, which drove the government to create the Indonesian Flying Robot Contest (KRTI) to accelerate its development in Indonesia. One of its categories, the Fixed Wing category, has a mapping and monitoring mission, where insufficient battery capacity problems are often found on UAVs with this mission due to its heavy payload and most of its energy is exhausted during take-off. This can be overcome by optimizing the airfoil to be able to produce larger lift force by adding vortex generators which aims to delay the flow separation on the
aircraft wing, so that the power consumed during take-off is decreased. This research was conducted experimentally using a wind tunnel in the Department of Mechanical Engineering FT-IRS ITS with a test section size of 660 x 660 x 2000 mm and a maximum speed of 15 m/s, as well as a drag and lift balance measuring instrument and a digital manometer. The model of this research is the wing of the Arnayadirga UAV with a NACA 2312 airfoil profile and a tapered shape without and with a vortex generator. The vortex generator is triangular in shape and mounted at x/c = 0.2 with a counter-rotating configuration. The results of this study indicates that the addition of vortex generators on the upper side of the UAV wing increases the lift from 0⁰ to the stall angle, but after the stall angle the lift is actually lower than the plain model. Vortex generators addition also reduces drag and improves wing performance, but also reduces the optimum angle of attack. It also affects the pressure coefficient distribution on the upper side of the wing at angles of attack 0⁰ and 8⁰ to be more negative, while at an angle of attack of 16⁰ the pressure coefficient distribution is actually more positive but is able to delay flow separation. Vortex generator addition does not change the pressure coefficient distribution on the wing’s lower side significantly. The results also show that vortex generator addition at higher Reynolds number produces a greater effect, so it can be said that vortex generator addition will benefit the UAV because it operates at a higher Reynolds number.

Item Type:	Thesis (Other)
Additional Information:	RSM 629.132 3 Seb s-1 2022
Uncontrolled Keywords:	Unmanned Aerial Vehicle, Vortex Generator, lift, drag, pressure coefficient
Subjects:	T Technology > TL Motor vehicles. Aeronautics. Astronautics > TL521 Aerodynamics, Hypersonic.
Divisions:	Faculty of Industrial Technology and Systems Engineering (INDSYS) > Mechanical Engineering > 21201-(S1) Undergraduate Thesis
Depositing User:	Mr. Marsudiyana -
Date Deposited:	24 Feb 2025 07:38
Last Modified:	24 Feb 2025 07:38
URI:	http://repository.its.ac.id/id/eprint/118861

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