Studi Eksperimen Pengaruh Penambahan Blended Winglet dengan Variasi Cant Angle 45° dan 90° pada Airfoil NACA 23015

Ramadhani, Dimas Ihza (2023) Studi Eksperimen Pengaruh Penambahan Blended Winglet dengan Variasi Cant Angle 45° dan 90° pada Airfoil NACA 23015. Other thesis, Institut Teknologi Sepuluh Nopember.

Text 02111940000111-Undergraduate_Thesis.pdf - Accepted Version Restricted to Repository staff only until 1 October 2025. Download (3MB) | Request a copy

Abstract

Salah satu bagian terpenting dalam mendesain pesawat adalah memilih bentuk sayap pesawat yang paling sesuai dengan kebutuhan. Karena bentuk suatu sayap pesawat sangat berpengaruh dalam menghasilkan lift force pada pesawat, akibat adanya perbedaan tekanan yang mengalir pada sisi atas dan sisi bawah dari sayap pesawat. Penelitian ini membahas tentang pengaruh blended winglet terhadap performa pesawat. Pada penelitian ini menggunakan wind tunnel open loop yang ada di Teknik Mesin FTIRS ITS. Penelitian ini menggunakan profil airfoil NACA 23015 dengan tiga model sayap pesawat, yaitu sayap tanpa blended winglet (A), sayap blended winglet dengan cant angle 45° (B), dan sayap blended winglet dengan cant angle 90° (C). Alat ukur yang digunakan antara lain force balance, pressure taps, anemometer, dan manometer digital. Berdasarkan penelitian yang dilakukan, penggunaan blended winglet pada airfoil NACA 23015 dapat meningkatkan perbedaan tekanan antara permukaan atas dan permukaan bawah ujung sayap. Hal ini mengindikasikan bahwa efek wingtip vortex yang terjadi di sekitar ujung sayap berkurang. Selain itu, didapatkan bahwa penambahan blended winglet dengan cant angle bervariasi dapat mempengaruhi performa aerodinamika dari sayap NACA 23015. Dengan melihat perubahan nilai CL, CD, dan CL/CD, didapatkan bahwa penambahan blended winglet dengan cant angle 45° memiliki nilai CL/CD yang paling bagus.
=================================================================================================================================
One of the most important parts of designing an aircraft is choosing the wing shape that best suits your needs. Because the shape of an aircraft wing is very influential in generating lift force on the aircraft, due to the difference in pressure flowing on the upper and lower sides of the aircraft wing. This research discusses the effect of blended winglets on aircraft performance. This research uses an open loop wind tunnel in Mechanical Engineering FTIRS. This study used NACA 23015 profile with three aircraft wing models, namely wings without blended winglets (A), blended winglets with cant angles of 45° (B), and blended winglets with cant angles of 90° (C). The measuring instruments used include force balance, pressure taps, anemometers, and digital manometers. Based on the research conducted, the use of blended winglets on NACA 23015 airfoil can increase the pressure difference between the upper surface and the lower surface of the wingtip. This indicates that the wingtip vortex effect that occurs around the wing tip is reduced. In addition, it is found that the addition of blended winglets with variations in cant angle can affect the aerodynamic performance of the NACA 23015 wing. By looking at changes in CL, CD, and CL/CD values, it is found that the addition of blended winglets with a cant angle of 45° has the best CL/CD value.

Item Type:	Thesis (Other)
Uncontrolled Keywords:	Blended Winglet, Lift, Drag, Cant Angle
Subjects:	T Technology > TJ Mechanical engineering and machinery
Divisions:	Faculty of Industrial Technology and Systems Engineering (INDSYS) > Mechanical Engineering > 21201-(S1) Undergraduate Thesis
Depositing User:	Dimas Ihza Ramadhani
Date Deposited:	26 Oct 2023 07:59
Last Modified:	26 Oct 2023 07:59
URI:	http://repository.its.ac.id/id/eprint/102314

Actions (login required)

View Item