Experimental Study of The Effect Adding Triangular Vortex Generator Counter-Rotating and Co-Rotating Arrangements on NACA 23015

Budiman, Muhammad Hanif (2023) Experimental Study of The Effect Adding Triangular Vortex Generator Counter-Rotating and Co-Rotating Arrangements on NACA 23015. Other thesis, Institut Teknologi Sepuluh Nopember.

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Abstract

One of the most important parts of designing an aircraft is choosing the most appropriate wing shape. Because the shape of an aircraft wing is very influential in producing 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 Vortex generator on aircraft performance. In this study using an open loop wind tunnel in Mechanical Engineering FTIRS ITS which has a limited suction test room with a cross-sectional area of 660 x 660 mm. This research uses NACA 23015 airfoil profiles with three aircraft wing models, namely wings without vortex generators (A), wings with vortex generators using a co-rotating arrangement (B), and wings with vortex generators using a counter-rotating arrangement (C). The measuring instruments used include force balance, pressure taps, anemometer, and digital manometer. In this study, an experiment-based analysis was conducted on the effect of installing vortex generators with various arrangements on aerodynamic performance, pressure distribution, and velocity profile on NACA 23015 airfoil. The research was conducted using the ITS Mechanical Engineering Department wind tunnel at a freestream speed of 10 m/s. The wing model used has a tapered configuration and uses NACA 23015 airfoil. Variations exist in the type of vortex generator arrangement used, namely the arrangement of co-rotating VG and counter-rotating VG. Based on the research conducted, the use of a vortex generator on the NACA 23015 airfoil configuration can increase the pressure difference between the upper surface and the lower surface. This indicates that the vortex effect produced by the vortex generator that occurs around the upper surface of the wing can increase the momentum of the flowing stream. In addition, it is found that the addition of vortex generators with various arrangements can affect the aerodynamic efficiency of the NACA 23015 airfoil wing. By looking at changes in the average CL, CD, and CL/CD values, it is found that the addition of both vortex generator arrangements can improve aerodynamic performance where vortex generators with co-rotating arrangements have good performance when the angle of attack is small and then for counter-rotating arrangements have good performance when the angle of attack is large.
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Salah satu bagian terpenting dalam mendesain sebuah pesawat terbang adalah memilih bentuk sayap yang paling tepat. Karena bentuk sayap pesawat sangat berpengaruh dalam menghasilkan gaya angkat pada pesawat, karena adanya perbedaan tekanan yang mengalir pada sisi atas dan bawah sayap pesawat. Penelitian ini membahas tentang pengaruh vortex generator terhadap performa pesawat terbang. Pada penelitian ini menggunakan terowongan angin open loop di Teknik Mesin FTIRS ITS yang memiliki ruang uji hisap terbatas dengan luas penampang 660 x 660 mm. Penelitian ini menggunakan profil airfoil NACA 23015 dengan tiga model sayap pesawat, yaitu sayap tanpa vortex generator (A), sayap dengan vortex generator menggunakan susunan co-rotating (B), dan sayap dengan vortex generator menggunakan susunan counter-rotating (C). Alat ukur yang digunakan antara lain neraca gaya, pressure tap, anemometer, dan manometer digital. Pada penelitian ini dilakukan analisa berbasis eksperimen mengenai pengaruh pemasangan vortex generator dengan berbagai variasi susunan terhadap performa aerodinamika, distribusi tekanan, dan profil kecepatan pada airfoil NACA 23015. Penelitian dilakukan dengan menggunakan terowongan angin Jurusan Teknik Mesin ITS pada kecepatan freestream 10 m/s. Model sayap yang digunakan memiliki konfigurasi tapered dan menggunakan airfoil NACA 23015. Variasi terdapat pada jenis susunan vortex generator yang digunakan, yaitu susunan co-rotating VG dan counter-rotating VG. Berdasarkan penelitian yang dilakukan, penggunaan vortex generator pada konfigurasi airfoil NACA 23015 dapat meningkatkan perbedaan tekanan antara permukaan atas dan permukaan bawah. Hal ini mengindikasikan bahwa efek vortex yang dihasilkan oleh vortex generator yang terjadi di sekitar permukaan atas sayap dapat meningkatkan momentum aliran yang mengalir. Selain itu, didapatkan bahwa penambahan vortex generator dengan berbagai macam susunan dapat mempengaruhi efisiensi aerodinamika sayap airfoil NACA 23015. Dengan melihat perubahan nilai rata-rata CL, CD, dan CL/CD, didapatkan bahwa penambahan kedua susunan vortex generator dapat meningkatkan performa aerodinamika dimana vortex generator dengan susunan co-rotating memiliki performa yang baik ketika sudut serang kecil dan kemudian untuk susunan counter-rotating memiliki performa yang baik ketika sudut serang besar

Item Type:	Thesis (Other)
Uncontrolled Keywords:	Airfoil NACA 23015, Drag, Lift, Susunan, Vortex Generator, Arrangement
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:	Muhammad Hanif Budiman
Date Deposited:	23 Aug 2023 03:33
Last Modified:	23 Aug 2023 03:33
URI:	http://repository.its.ac.id/id/eprint/102342

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