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All Journal MACHINERY: Jurnal Teknologi Terapan Industrial Research Workshop and National Seminar Science, Technology, and Communication Journal Indonesian Journal of Aerospace
Kartanegara, Radi Suradi
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Aerospace Engineering Humanities Astronomy Chemical Engineering, Chemistry & Bioengineering Civil Engineering, Building, Construction & Architecture Computer Science & IT Control & Systems Engineering Education Electrical & Electronics Engineering Energy Engineering Industrial & Manufacturing Engineering Materials Science & Nanotechnology Mechanical Engineering Other

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Kaji Komputasional Struktur Pesawat Model Wing in Ground Effect Tipe Sayap Tandem Barus, Michael Bastanta; Kartanegara, Radi Suradi; Hartono, Budi
Prosiding Industrial Research Workshop and National Seminar Vol. 13 No. 01 (2022): Vol 13 (2022): Prosiding 13th Industrial Research Workshop and National Semin
Publisher : Politeknik Negeri Bandung

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (606.872 KB) | DOI: 10.35313/irwns.v13i01.4166

Abstract

Artikel ini menjelaskan mengenai kaji komputasional struktur pesawat model wing in ground effect. Pengkajian ini bertujuan untuk memastikan apakah struktur yang dirancang dan material yang digunakan mampu untuk menahan beban yang terjadi pada pesawat model sebelum dilakukan rancang bangun. Pembebanan static berupa berat struktur, berat engine dan gaya angkat yang terjadi pada sayap dan fuselage. Struktur yang dilakukan simulasi kekuatan struktur dikatakan aman jika safety of factor >1.5. Nilai maksimum von misses sebesar 1,968 Mpa, angka ini masih berada dibawah nilai yield strength kayu balsa sebesar 12 Mpa sehingga material dan struktur dapat disimpulkan dapat digunakan dan aman.
A numerical study on T-reduce junction flow distribution Haryadi, Haryadi; Sugianto, Sugianto; Mahmudi, Ali; Kartanegara, Radi Suradi
Science, Technology and Communication Journal Vol. 2 No. 2 (2022): SINTECHCOM Journal (February 2022)
Publisher : Lembaga Studi Pendidikan and Rekayasa Alam Riau

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.59190/stc.v2i2.208

Abstract

Although many manifold shapes have been studied, research on venturi-shaped manifolds with holes smaller than the inner diameter of the pipe, hereinafter referred to as T-reducer, has so far not been found. This research studies the effect of hole diameter and Reynolds number on the debit that comes out of the branch pipe. The venturi hole diameter is varied from 40% to 80% of the main pipe diameter, while the bulk velocity is varied from 2 to 10 m/s. The research started by creating a 3D T-reducer model, followed by CFD simulation using Fluent software. From the simulation results, curve fitting is performed using multiple regression to obtain an equation which is the correlation of dimensionless numbers. The maximum difference between the flow coefficient obtained from the curve fitting equation and the CFD simulation results is 3.35%.
ANALISIS PERFORMA PROPELLER TIPE TOROIDAL DAN WINGLET BERBASIS CFD Zaim Sidqi Islami; Wuwung, Vicky; Kartanegara, Radi Suradi; Ardi, Hanni Maksum
MACHINERY Jurnal Teknologi Terapan Vol. 6 No. 2 (2025): Machinery: Jurnal Teknologi Terapan
Publisher : Politeknik Negeri Sriwijaya, Indonesia

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.5281/zenodo.16938188

Abstract

Penggunaan wahana udara tanpa awak (UAV) yang semakin meluas mendorong perkembangan perancangan propeler modern ke arah peningkatan performa dan pengurangan tingkat kebisingan. Studi pada winglet propeler dan propeler tipe toroidal dilakukan secara numerik CFD untuk membandingkan gaya dorong, daya dan efisiensinya dengan propeler biasa / konvensional APC 20x10.  Simulasi CFD dilakukan dengan metode Frozen Rotor dan Periodik Rotasional pada putaran 3000 RPM dan 5 kecepatan aliran. Hasil simulasi menunjukkan propeler winglet justru mengalami penurunan efisiensi sebesar 1% dan penurunan gaya dorong sebesar 5% sedangkan propeler toroidal menunjukkan peningkatan efisiensi 6% walaupun gaya dorong turun 10% dibandingkan propeler biasa. Propeler toroidal juga memiliki distribusi tekanan yang lebih merata sepanjang bilah yang mengindikasikan tip vortex yang sangat rendah. Studi pengaruh variasi rancangan winglet atau toroidal terhadap pembentukan tip vortex dan performa propeler dapat dikembangkan lebih lanjut untuk mendukung pengembangan UAV yang ramah lingkungan.
Design of Mini Turbojet Engine Combustion Chamber Liner With 200N Static Thrust Santoso, Rais Ryacudu; Wuwung, Vicky; Annisa, Reina Fadjrin Nurul; Kartanegara, Radi Suradi
Indonesian Journal of Aerospace Vol. 21 No. 2 (2023): Indonesian Journal Of Aerospace
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.55981/ijoa.2023.38

Abstract

Design of mini turbojet engine with 200N static thrust at an air mass flow of 0.55kg/s, requiring annular type combustion chamber with liner capability of dividing the air mass flow in the primary zone by 20%, secondary zone 30%, dilution zone 50%, and with 4%- 10% pressure loss. In the primary zone, it is necessary to have a recirculation zone that will become a stable combustion place. Liner geometry is obtained by analytical and empirical calculations, that is validated by numerical simulations at cold flow steady conditions. Analytical and empirical calculations resulting in the primary, secondary, and dilution zone respectively: the hole diameter: 2.153mm, 2.503mm, 5.005mm; number of holes: 44, 52, 44 holes; the distance of hole from inlet liner: 28.5mm, 47.5mm, 113.6 mm; air mass flow rates: 19.4%, 29.6%, 50%, and the pressure loss of the combustion chamber is 4%. The numerical simulation is performed by using the turbulent k-e model (extended wall) and has a difference resulted with analytical and empirical calculations on mass flow in the primary, secondary, and dilution zone: 3.44%, 9.09%, 8.88%, and the pressure drop is 10.86%. The recirculation zone that is fulfil injector placement criteria formed in the primary zone at the longitudinal cross-section position (q) from 32.72o to 360o with 32.73o in increment, with horizontal (H) and vertical (V) distance from inner liner wall are varies from 34 to 40 mm for H, and from 35 to 43 mm for V with outer recirculation tangential velocity variation from 43 to 60 m/s.
Co-Authors Ali Mahmudi Annisa, Reina Fadjrin Nurul Ardi, Hanni Maksum Barus, Michael Bastanta Budi Hartono Haryadi - Santoso, Rais Ryacudu Sugianto Sugianto Wuwung, Vicky Zaim Sidqi Islami