Valentino, Daniel (2024) Studi Eksperimen Pengaruh Penggunaan Blended Winglet dengan Variasi Cant Angle 30º dan 45º dan Penambahan Counter Rotating Vortex Generator pada Airfoil NACA 23015. Other thesis, Institut Teknologi Sepuluh Nopember.
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Abstract
Sayap pada pesawat terbang merupakan salah satu komponen paling penting untuk menghasilkan gaya angkat (lift). Gaya lift terjadi akibat adanya perbedaan tekanan yang mengalir pada permukaan atas dan permukaan bawah dari sayap. Gaya lift meningkat seiring bertambahnya angle of attack begitu juga dengan gaya drag. Gaya drag bersifat merugikan karena dapat mengurangi performa penerbangan sehingga mengurangi efisiensi penggunaan bahan bakar. Terjadinya gaya drag diakibatkan oleh separasi aliran yang menyebabkan terbentuknya wake area di belakang sayap. Salah satu upaya yang dilakukan untuk mengurang gaya drag adalah dengan menambahkan winglet dan vortex generator pada sayap. Penelitian ini membahas tentang pengaruh blended winglet dengan variasi cant angle dan penambahan vortex generator terhadap performa aerodinamis sayap pesawat. Penelitian ini dilakukan dengan metode berbasis eksperimen menggunakan open circuit subsonic wind tunnel yang berada di Departemen Teknik Mesin FT-IRS ITS yang memiliki ruang test suction dengan luas penampang 660 x 660 mm dengan kecepatan freestream 10 m/s. Model uji yang digunakan untuk penelitian adalah sayap dengan profil airfoil NACA 23015 yang terdiri dari empat model sayap pesawat, yaitu plain wing (A), sayap blended winglet dengan cant angle 30° (B), sayap blended winglet dengan cant angle 45° (C), dan sayap blended winglet 45° dengan vortex generator (D). Model uji diuji pada angle of attack 0º, 4º, 8º, 12º, 14º, dan 16º untuk pengkuran lift dan drag serta angle of attack 0º, 8º, dan 16º untuk pengukuran tekanan dan profil kecepatan. Alat ukur yang digunakan antara lain alat force balance, pressure taps, manometer digital, anemometer, dan pitot tube. Berdasarkan hasil penelitian, penambahan blended winglet dengan variasi cant angle dapat meningkatkan nilai koefisien lift (CL) yang dihasilkan pada setiap model airfoil. Namun kenaikan nilai koefisien lift ini juga diikuti dengan kenaikan nilai koefisien drag (CD). Nilai performa aerodinamis (CL/CD) tertinggi dihasilkan oleh model sayap winglet dengan cant angle 45º yang ditambahkan VG, yang menunjukkan bahwa inilah konfigurasi yang optimal untuk sayap airfoil NACA 23015 pada penelitian ini. Penambahan VG menjadi nilai tambah untuk model sayap winglet dengan cant angle 45º, sehingga kombinasi antara blended winglet dan VG pada sayap menjadi yang terbaik diantara model lainnya
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The wings of an airplane are one of the most important components for producing lift. The lift force occurs due to the difference in pressure flowing on the upper surface and the lower surface of the wing. The lift force increases as the angle of attack increases as does the drag force. Drag force is detrimental because it can reduce flight performance, thereby reducing fuel use efficiency. The drag force occurs due to flow separation which causes the formation of a wake area behind the wing. One of the efforts made to reduce drag force is by adding winglets and vortex generators to the wings. This research discusses the effect of blended winglets with cant angle variations and the addition of a vortex generator on the aerodynamic performance of aircraft wings. This research was carried out using an experimental-based method using an open circuit subsonic wind tunnel located in the Department of Mechanical Engineering FT-IRS ITS which has a suction test room with a cross-sectional area of 660 x 660 mm with a freestream speed of 10 m/s. The test model used for research is a wing with a NACA 23015 airfoil profile which consists of four aircraft wing models, namely plain wing (A), blended winglet wing with a cant angle of 30° (B), blended winglet wing with a cant angle of 45° (C ), and 45° blended winglets with vortex generator (D). The test model was tested at angles of attack 0º, 4º, 8º, 12º, 14º, and 16º for measuring lift and drag and angles of attack 0º, 8º, and 16º for measuring pressure and speed profiles. The measuring instruments used include force balances, pressure taps, digital manometers, anemometers and pitot tubes. Based on the research results, the addition of blended winglets with cant angle variations can increase the lift coefficient (CL) value produced for each airfoil model. However, the increase in the lift coefficient value is also followed by an increase in the drag coefficient (CD) value. The highest aerodynamic performance (CL/CD) value was produced by the winglet model with a 45º cant angle with added VG, which shows that this is the optimal configuration for the NACA 23015 airfoil wing in this study. The addition of VG is an added value for winglet wing models with a cant angle of 45º, so that the combination of blended winglet and VG on the wing is the best among other models
| Item Type: | Thesis (Other) |
|---|---|
| Uncontrolled Keywords: | Airfoil NACA 23015, Blended Winglet, Cant Angle, Gaya Aerodinamis, Vortex generator; Aerodynamic Force, Airfoil NACA 23015, Blended Winglet, Cant Angle, Vortex generator |
| 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: | Daniel Valentino |
| Date Deposited: | 10 Feb 2024 05:49 |
| Last Modified: | 10 Feb 2024 05:49 |
| URI: | http://repository.its.ac.id/id/eprint/106721 |
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