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All Journal Angkasa: Jurnal Ilmiah Bidang Teknologi Scientific Journal of Mechanical Engineering Kinematika Vortex Indonesian Journal of Aerospace
Jalaali, Bahrul
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Aerospace Engineering Astronomy Automotive Engineering Computer Science & IT Earth & Planetary Sciences Energy Industrial & Manufacturing Engineering Materials Science & Nanotechnology Mechanical Engineering

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THE NAVIER-STOKES-CONTINUITY EQUATION SOLVER BASED ON ARTIFICIAL COMPRESSIBILITY METHOD Jalaali, Bahrul
Angkasa: Jurnal Ilmiah Bidang Teknologi Vol 12, No 1 (2020): Mei
Publisher : Sekolah Tinggi Teknologi Adisutjipto

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (2161.779 KB) | DOI: 10.28989/angkasa.v12i1.583

Abstract

Fluid dynamics analysis can be accurately approximated by using a computer-based numerical method. Rely on the mass and momentum governing equation, the mathematics model for the compressible condition is numerically difficult to overcome. Through an artificial compressibility method, the quasi-compressible condition solution can be simplified. This study will investigate the classical lid-driven cavity case model to affirm the artificial compressibility method. The result shows that the current model is in-line with the previous study for the lid-driven cavity case. A conventional benchmark with the previous numerical study is shown as well.
ANALISIS BERBASIS SIMULASI TERHADAP SIFAT AERODINAMIKA AIRFOIL NACA 2412 DENGAN PENAMBAHAN ELEMEN FLAP DAN SLAT Dinaryanto, Okto; Jalaali, Bahrul; Syahrizal; Subarjo, Abdul Haris; Setiabudi, Dedet Hermawan; Kumolosari, Eli
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%.
Manufacturing process and experimental study of a small scale archimedes hydro powerplant by varying the number of blade Abdillah, Helmi Fauzan; Dinaryanto, Okto; Jalaali, Bahrul
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 (1461.074 KB) | DOI: 10.28989/angkasa.v14i1.1221

Abstract

This study investigated the optimum value of Archimedes Screw Turbine (AST) performance by taking into account blades number. This paper also addressed the design approach based on a fixed incline angle of 30°, where this paper also addressed the design approach. Variations of the single and double blades were experimentally carried out concerning the turbine power output, torque, and rotation speed. This study's aim was related to the optimum power output between two blade variations, while the manufacturing and design steps were addressed as well. In the design process, the obtained blade length dimension was 0.180 m and 0.269 m for the single and double blades. Furthermore, the overall turbine's length was 1.7m, and the inner and outer of the turbine's radius were 0.069m and 0.128m. Meanwhile, the manufacturing process began with turbine modeling, plate cutting, plate withdrawal (thread formation), welding, and attained finishing process. Based on the experimental result, a double blade turbine generated turbine power by 48.8W at an average rotational speed of 115.3 rpm. Moreover, a single blade turbine produced 37.5W with turbine power averaging a rotational speed of 109.8 rpm. It was obtained that the values of turbine efficiency were 42% and 38% for double and single turbine types, respectively. Based on this finding, it can be suggested that a double blade was more efficient than a single one. This study is beneficial for the design consideration of the AST system.
SIMULASI NUMERIK KARAKTERISTIK AERODINAMIKA PADA AIRFOIL NACA 4415 DENGAN MEMPERTIMBANGKAN GROUND EFFECT Hayuningtyas, Rr Saskia Rianasari; Nugroho, Farhan Fathori; Jalaali, Bahrul
Vortex Vol 4, No 1 (2023)
Publisher : Institut Teknologi Dirgantara Adisutjipto

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.28989/vortex.v4i1.1339

Abstract

Ground effect phenomenon is found when the lift-device such as wing, is placed near the ground. This phenomenon influences the aerodynamics characteristic whereby its appearance is important to be investigated. This work aims to study the influence of ground effect towards aerodynamics characteristion on the NACA4415 airfoil by varying the airfoil’s angle of attack (AoA) as well as the height of ground proximity. Numerical approach conducted on Fluent was carried out while steady assumption, moving wall boundary, and Spalart-Allmaras turbulence model were utilized. The outcomes were aerodynamics characteristic represented by lift and drag coefficients. The results showed that maximum  was 1.736 on AoA 15o while maximum  was 0.0108 on AoA 18o respectively. It also found that ground proximity also was affecting the values of  and . On the height of 0.05 chord, maximum characteristic of lift was obtained while maximum drag was on the 0.8 chord at AoA 18o. It caused by airflow underneath the airfoil was faster due to the ground effect revaling the nozzle-effect, therefore the pressure was higher as according to the Bernoulli’s formulation. On the other hand, drag was related to the vortex generation in which AoA more influental than that of height. This work is hopefully beneficial as initial reference on the Wing-in-Ground (WIG) craft design, in particular on the airfoil selection. 
Integrated Numerical Investigation on the Aerodynamics Characteristic and Vortex Development of Airfoil using Spalart-Allmaras Model Dinaryanto, Okto; Jalaali, Bahrul; Hisyam, Muhammad; Wibowo, Teguh
Indonesian Journal of Aerospace Vol. 21 No. 1 (2023): Indonesian Journal of Aerospace
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.55981/ijoa.2023.116

Abstract

In this paper, the numerical simulation successfully obtained good results in analyzing fluid flow over the airfoil. Detailed explanations of simulation steps were also presented. The flow characteristics over three airfoil models were numerically simulated in this work: NACA0021, NACA2409, NACA2409+Fowler flap. The reliable Spalart-Allmaras (S-A) turbulent model was used and validated using reported data from experimental in terms of lift and drag coefficients. In this regard, the discrepancies of less than 10% were obtained for both coefficients, respectively. The boundary layer separation, vortex development, and air separation were clearly captured. The results of symmetric airfoil showed that the vortex shedding regimes occurred at α = 8o, and the stall critical-angle was about 14o. The value was higher for the NACA2409, where the airflow exhibited a relatively more stable behavior. Moreover, it is evident that flap addition altered lift-drag characteristics. The value of the lift-to-drag ratio increased due to the increase of Cl and the reduction of Cd. The parametric study was done on the α and flap deflection angle to attain the desirable airfoil configuration. The maximum result of airfoil configuration was obtained on the NACA2409 at α = 12o with 100 flap deflection angle while it enhanced the lift coefficient by about 54%. This result strengthens the robustness of the S-A turbulence model and projects the use of the S-A model for dealing with the aerodynamics analysis. This study is beneficial for initial aircraft design on the aerodynamics aspect of a wing.
Co-Authors Abdillah, Helmi Fauzan abdul haris subarjo, abdul haris Dedet Hermawan Setiabudi, Dedet Hermawan Eli Kumolosari Hayuningtyas, Rr Saskia Rianasari Muhammad Hisyam Nugroho, Farhan Fathori Okto Dinaryanto Syahrizal Teguh Wibowo