Ramadhany, Triasa (2008) Studi Eksperimental Tentang Pengaruh Dinding Terhadap Karakteristik Aliran Fluida Melintasi Airfoil Simetri Studi Kasus Untuk Variasi Kelengkungan Leading Edge 0.15 C, 0.3 C dan 0.5. Other thesis, Institut Teknologi Sepuluh Nopember.
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Abstract
Gradient kontur dari airfoil sangat berpengaruh terhadap distribusi tekanan statis dari aliran sepanjang kontur airfoil. Lebih jauh, gradien tekanan dari aliran dekat permukaan airfoil tersebut, sangat berpengaruh terhadap perkembangan boundary layer sepanjang kontur. Transisi laminar boundary layer menjadi turbulen boundary layer yang lebih cepat terjadi dengan kondisi gradient tekanan yang lebih tajam, pada akhirnya berpengaruh terhadap penundaan separasi aliran di buritan airfoil. Karakteristik aliran akan mengalami perubahan apabila terdapat gangguan, misalnya dinding yang didekatkan pada salah satu sisi airfoil. Berdasarkan pemikiran diatas maka dilakukanlah penelitian aliran melintasi airfoil simetri yang diganggu dengan dinding. Penelitian ini dilakukan secara eksperimental dalam sebuah wind tunnel, benda uji yang digunakan adalah satu dinding dan sejumlah airfoil simetri dengan variasi posisi ketebalan maksimum 0.15 C, 0.3 C dan 0.5 C. Penelitian dilakukan dengan cara airfoil yang memiliki perbedaan posisi maksimum thickness salah satu sisi lowernya didekatkan terhadap dinding. Karakteristik aliran fluida yang diteliti adalah distribusi koefisien tekanan (Cp), koefisien drag (CD), koefisien lift (CJ, profil kecepatan di belakang airfoil dan dilakukan visualisasi menggunakan metode oil flow picture pada subsonic wind tunnel dengan Re1= 5xl 04. Hasil yang didapatkan dari penelitian eksperimental ini adalah perubahan posisi maksimum thickness airfoil merubah posisi titik stagnasi. Semakin mundur posisi dari maksimum thickness mengakibatkan titik stagnasi bergeser menuju lower side. Pengaruh perubahan posisi maksimum thickness yang semakin mundur, mengakibatkan koefisien lift semakin membesar
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The contour gradient of the airfoil significantly influences the static pressure distribution of the flow along the contour of the airfoil. Furthermore, the pressure gradient of the flow near the surface of the airfoil significantly influences the development of the boundary layer along the contour. A faster transition of the laminar boundary layer to a turbulent boundary layer occurs with sharper pressure gradient conditions, ultimately affecting the delay in flow separation at the aft of the airfoil. Flow characteristics will change if there is a disturbance, for example a wall that is brought close to one side of the airfoil. Based on the above considerations, a study was conducted on the flow across a symmetrical airfoil disturbed by a wall. This study was conducted experimentally in a wind tunnel, the test objects used were one wall and a number of symmetrical airfoils with variations in maximum thickness positions of 0.15 C, 0.3 C and 0.5 C. The study was conducted by means of airfoils that have different maximum thickness positions on one of their lower sides being brought close to the wall. The fluid flow characteristics studied are the distribution of pressure coefficient (Cp), drag coefficient (CD), lift coefficient (CJ), velocity profile behind the airfoil and visualization was carried out using the oil flow picture method in a subsonic wind tunnel with Re1 = 5xl 04. The results obtained from this experimental study are changes in the maximum thickness position of the airfoil change the position of the stagnation point. The further backward position from the maximum thickness causes the stagnation point to shift towards the lower side. The effect of changing the maximum thickness position that is getting further backward, results in an increasing lift coefficient
| Item Type: | Thesis (Other) |
|---|---|
| Additional Information: | RSM 620.106 4 Ram s-1 2008 (weeding) |
| Uncontrolled Keywords: | Airfoil simetri, ground effect, maksimum thickness (t), koefisien tekanan (C~, koefisien lift (CJ.; symmetrical airfoil, ground effect, IIUlksimum thickness (t), pressure coeffiCient (CJ, lift coeffiCient (CJ). |
| Subjects: | Q Science > QA Mathematics > QA911 Fluid dynamics. Hydrodynamics |
| Divisions: | Faculty of Industrial Technology > Mechanical Engineering > 21201-(S1) Undergraduate Thesis |
| Depositing User: | EKO BUDI RAHARJO |
| Date Deposited: | 09 Oct 2025 06:33 |
| Last Modified: | 09 Oct 2025 06:33 |
| URI: | http://repository.its.ac.id/id/eprint/128541 |
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