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All Journal Journal of Science and Applicative Technology Angkasa: Jurnal Ilmiah Bidang Teknologi KACANEGARA Jurnal Pengabdian pada Masyarakat Scientific Journal of Mechanical Engineering Kinematika
Bahrul Jalaali
Institut Teknologi Dirgantara Adisutjipto
Automotive Engineering Civil Engineering, Building, Construction & Architecture Computer Science & IT Earth & Planetary Sciences Education Energy Engineering Industrial & Manufacturing Engineering Materials Science & Nanotechnology Mechanical Engineering

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Numerical study of drag force on the UAV tilt and fixed wing model during vertical take off landing Muhammad Musyfiq Haikal; Rully Hidayat; Bahrul Jalaali
Angkasa: Jurnal Ilmiah Bidang Teknologi Vol 14, No 1 (2022): Mei
Publisher : Institut Teknologi Dirgantara Adisutjipto

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (1215.511 KB) | DOI: 10.28989/angkasa.v14i1.1170

Abstract

A hybrid vertical take-off landing (VTOL) UAV combines the concepts of fixed-wing and rotary-wing UAV aircraft in one platform while performing in both conventional and vertical take-off landings. This aircraft has a drawback of significant drag force generated due to fixed-wing. Therefore, a Tilt-Wing often utilized to overcome this obstacle whereby it could be adjusted to the vertical and horizontal directions. To enhance the understanding of generated drag force on both wing model, this study was performed by examine the drag characteristic of the VTOL UAV. The simulations were carried out in the wind speed range by 1.4 m/s, 4.17 m/s, and 6.94 m/s. Simulation results showed that the drag of the UAV Hybrid Tilt-Wing and Fixed-Wing increased at the speed of 1.4 m/s to 6.94 m/s while the highest drag value was 177.51 N on a Fixed-Wing UAV aircraft and 1.97 N on a Tilt-Wing UAV aircraft. The result concluded that Tilt-Wing UAV has less drag which was more efficient than fixed-wing.
Simulasi aliran dua fase pada campuran air-minyak di pipa horizontal dengan parameter termal Bahrul Jalaali; Eli Kumolosari
Angkasa: Jurnal Ilmiah Bidang Teknologi Vol 13, No 2 (2021): November
Publisher : Institut Teknologi Dirgantara Adisutjipto

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (680.164 KB) | DOI: 10.28989/angkasa.v13i2.1042

Abstract

A CFD study of Water-Oil flow in the horizontal pipe was conducted using the VoF multiphase model coupled with the SST  turbulence model scheme. This study aimed to simulate the mixture flow characteristic by takes account temperature parameter. It was numerically solved using a finite-volume model utilized in Fluent software. The simulation results compared towards experimental showed good prediction on the particular flow pattern. In this study, the thermal parameter was then solved by utilizing energy equation coupled by multiphase model. The water flow temperatures were varied in ranged of 300-340K. The results showed that temperature affected reducing the viscosity of the fluid as well ass the density. Furthermore, the flow pattern changed whereby oil was above the water due to its viscosity and density. This study is beneficial for accessing the temperature effect on the water-oil flow as represented in the applied petroleum industry of oil-lifting.
Implementasi program peningkatan kompetensi siswa SMK melalui pelatihan CAD dan CFD serta evaluasi berbasis Key Performance Indicator Bahrul Jalaali; Eli Kumolosari; Okto Dinaryanto
KACANEGARA Jurnal Pengabdian pada Masyarakat Vol 6, No 1 (2023): Januari
Publisher : Institut Teknologi Dirgantara Adisutjipto

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.28989/kacanegara.v6i1.1280

Abstract

Dalam rangka meningkatkan pengetahuan dan kompetensi siswa SMK mengenai teknologi komputasi perancangan dan dinamika fluida, dilakukanlah kegiatan pengabdian masyarakan berupa workshop dan pelatihan computer-aided-design (CAD) dan computational-fluid-dynamics (CFD). Adapun untuk melakukan evaluasi luaran dari program dilakukan dilakukan kajian berbasis metode key performance indicators (KPI) untuk mendapatkankan hasil dan pembahasan yang akurat pada peforma dan aspek sustainability kegiatan. Kegiatan pengabdian kepada masyarakat ini berhasil terlaksana dengan baik dan lancar. Materi yang disampaikan bagi peserta adalah sebagai salah satu sarana pembelajaran untuk meningkatkan pemahaman siswa dan guru SMK Penerbangan Techno Terapan Makassar. Berdasarkan kajian evaluasi program menggunakan metode KPI, secara umum didapatkan hasil yang baik dan lancar sesuai dengan argumen sebelumnya. Dari hasil analisis dan evaluasi didapatkan bahwa mayoritas peserta (>90%) menyatakan bahwa acara berlangsung sesuai dengan tema, menambah pengetahuan dan sesuai harapan peserta. Kedepan, diharapkan pemahaman akan komputasi dinamika fluida ini dapat berintegrasi dengan konsep Revolusi Industri 4.0. Kegiatan ini diharapkan dapat memberikan gambaran dan pengetahuan kepada siswa mengenai penggunaan dan pemanfaatan komputasi dinamika fluida.
Studi Eksperimental Pengaruh Variasi Sudut Kemiringan Poros Terhadap Kinerja Turbin Ulir Archimedes Kukuh Pribadi; Dedet Hermawan Setiabudi; Bahrul Jalaali
Journal of Science and Applicative Technology Vol 6 No 2 (2022): Journal of Science and Applicative Technology December Chapter
Publisher : Lembaga Penelitian dan Pengabdian Masyarakat (LPPM), Institut Teknologi Sumatera, Lampung Selatan, Lampung, Indonesia

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35472/jsat.v6i2.938

Abstract

This study aims to design and conduct an experimental study of axle tilt angles variation on the performance of the Archimedes screw turbine (AST). The AST was constructed based on Rorres (2000) [3] formulation to achieve the optimum design of AST. This design was obtained with the followings parameters: 1.7m turbine axle length, 0.069m and 0.128m of internal and external turbine radius, 0.260m pitch length, 6.5 pitches number, 59° and 72° of external and internal blade angel, and 2 number of blades. The screw turbine performance was experimentally carried out by varying the angle of the turbine axle in the range of 25°, 30°, 35°, 40°, and 45°. The test was utilized the natural river flow with an average discharge of 0.011 m3/s. The result was yielded that the optimum angle of the turbine was at a turbine tilt axle of 35° while the rotational speed was 265.5 rpm, whereby the turbine generated 48.81W power and 4.09Nm of torque. This study is hopefully beneficial for the turbine design reference as well as its experimental evaluation.
ANALISIS BERBASIS SIMULASI TERHADAP SIFAT AERODINAMIKA AIRFOIL NACA 2412 DENGAN PENAMBAHAN ELEMEN FLAP DAN SLAT Okto Dinaryanto; Bahrul Jalaali; Syahrizal; Abdul Haris Subarjo; Dedet Hermawan Setiabudi; Eli Kumolosari
Scientific Journal of Mechanical Engineering Kinematika Vol 10 No 2 (2025): SJME Kinematika Desember 2025
Publisher : Mechanical Engineering Department, Faculty of Engineering, Universitas Lambung Mangkurat

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.20527/sjmekinematika.v10i2.724

Abstract

The original concept for the Easy-Fly project was to create an ultra-light STOL (Short Takeoff and Landing) plane featuring minimal drag and speed attributes. To support this goal, CFD (Computational Fluid Dynamics) was applied by varying the configuration of single-grooved flaps and slats and the angle of attack on the NACA 2412 airfoil. The viscous model used in this case is Spalart-Allmaras. The variation of the angle of attack (α) was modified in the range of 0°-20°. For the flap model, the deflection angle was adjusted to 30° and 40°, and slats were added to the configuration. Based on the results of the study, it was found that flap deflections of 30° and 40° resulted in higher CL values ​​at an angle of attack of 0°. The use of flap and slat designs on the NACA 2412 airfoil effectively delayed airflow separation until it reached a maximum angle of attack of 24°. In addition to the high-lift system design on the NACA 2412 airfoil, changes in camber and effective chord line adjustments resulted in significant improvements in the lift coefficient (CL), drag coefficient (CD), and stall angle. Finally, a 30° flap deflection was more efficient than a 40° deflection in takeoff conditions. The average percentage increase in CL/CD from a 30° to a 40° flap was 17.61%.
Co-Authors Abdul Haris Subarjo Dedet Hermawan Setiabudi Eli Kumolosari Kukuh Pribadi Muhammad Musyfiq Haikal Okto Dinaryanto Rully Hidayat Syahrizal