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All Journal IAES International Journal of Artificial Intelligence (IJ-AI) Indonesian Journal of Aerospace
Soemaryanto, Arifin Rasyadi
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Aerospace Engineering Astronomy Computer Science & IT Engineering

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Predicting water resistance and pitching angle during take-off: an artificial neural network approach Fajar, Muhammad; Atmaja, Sigit Tri; Pinindriya, Sinung Tirtha; Soemaryanto, Arifin Rasyadi; Hidayat, Kurnia
IAES International Journal of Artificial Intelligence (IJ-AI) Vol 14, No 1: February 2025
Publisher : Institute of Advanced Engineering and Science

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.11591/ijai.v14.i1.pp142-150

Abstract

This research addresses the challenges faced by seaplanes and amphibious aircraft during takeoff and landing on water, emphasizing the limitations and costs associated with traditional towing tank tests and computational fluid dynamics (CFD) simulations. The study proposes an innovative approach that employs artificial neural networks (ANN) to predict water resistance and pitching angle during amphibious aircraft take-off, minimizing the reliance on expensive towing tank tests. The ANN models are developed and optimized using Bayesian optimization, showcasing improved accuracy in predicting water resistance and pitching angle. The research demonstrates the potential of machine learning, specifically ANNs, to significantly reduce the need for costly experimental tests, providing an efficient alternative for designing amphibious aircraft. The results indicate high accuracy in predicting water resistance and pitching angle, offering substantial time and resource savings during the experimental phase. However, the study highlights the need for model adaptation for different designs and test variations to enhance overall applicability.
Impact of Airfoil Section on Winglet Design for Enhancing Aerodynamics Performance of Aircraft using CFD Analysis Pinindriya, Sinung Tirtha; Soemaryanto, Arifin Rasyadi; Fajar, Muhammad; Hidayat, Kurnia; Hamonangan, Jefri Abner; Ramadiansyah, Mohamad Luthfi
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.2023.900

Abstract

This research paper investigates the influence of airfoil section on winglet design to enhance aerodynamic performance while considering structural aspects. The selection of the airfoil section significantly affects the distribution of lift and drag along the winglet, influencing the overall lift-to-drag ratio of the aircraft and its ability to reduce drag by smoothing the airflow over the wingtip. Three airfoil sections, namely NACA 0010 (symmetrical), NACA 64-009 (thin cambered), and PSU 94-047 (cambered), were compared using computational fluid dynamics (CFD) simulations. The study examines the forces and moments experienced by the winglet, including drag force, lift force, and bending moment on wing surface. The CFD simulations were conducted using a Computational Wind Tunnel (CWT) tool, which employs numerical methods and mathematical models to analyze fluid flow around objects. The solver code is based on RANS method. The wind tunnel testing is provided to validate one of CFD simulation results. The findings indicate that the installation of winglets increases both the lift-to-drag ratio and bending moment compared to the clean wing configuration. Among the studied airfoil profiles, NACA 0010 demonstrated the optimum lift-to-drag ratio, showing a 9.5% improvement over the clean wing configuration. Although it is a symmetrical airfoil, the thickness of NACA 0010 contributed to higher lift production and increased bending moment compared to the cambered airfoils (NACA 64-009 and PSU 94-047), which showed approximately 10% improvement in lift-to-drag ratio. While the differences in aerodynamic characteristics between the airfoil profiles were marginal, the overall addition of winglets proved effective in increasing lift and reducing induced drag. The research highlights the significance of airfoil shape and thickness in optimizing winglet performance. Future studies should focus on refining the winglet airfoil profile to maximize the benefits derived from both thickness and cambered shape, aiming to further enhance aerodynamic efficiency.
Identification of Flow-Induced Noise Sources on Two-Dimensional High Lift Devices of Commuter Aircraft Soemaryanto, Arifin Rasyadi; Fajar, M; Hakim, TMI; Hidayat, Kurnia; Tirtha, Sinung
Indonesian Journal of Aerospace Vol. 19 No. 2 (2021)
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3500

Abstract

A numerical predictive tool of flow induced noise generated by deployed high-lift devices of commuter aircraft is presented in this paper. The aircraft high-lift devices are consisting of vane and flap component. The aim of this study is to identify the sources of flow induced noise on the wing and flap cross-section of the aircraft. This study is investigated only two-dimensional effects and two configuration of flap deflection. A numerical computation is carried out using a CFD software with Large Eddy Simulation fluid turbulence model and Ffowcs-Williams & Hawkings analogy for acoustic prediction. Several sound receivers have been installed on far-field and near-field region of the wing-vane-flap cross-section of aircraft to measure the sound spectra. It has been identified that on the cavity of wing and vane-flap cross-section has the highest sound pressure level than another region. There is a vortical separation and shear layer which is contributed to the generation of sound emission downward the cross-section
VERIFICATION OF SCHRENK METHOD FOR WING LOADING ANALYSIS OF SMALL UNMANNED AIRCRAFT USING NAVIERSTOKES BASED CFD SIMULATION Soemaryanto, Arifin Rasyadi; Rosid , Nurhayyan H
Indonesian Journal of Aerospace Vol. 15 No. 2 Desember (2017): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2017.v15.a2747

Abstract

Prediksi dari beban aerodinamika yang terjadi pada sayap menjadi salah satu tahap yang penting dalam analisis struktur perancangan pesawat. Beberapa metode telah digunakan untuk mengestimasi besarnya beban aerodinamika pada sayap. Metode Schrenk umum digunakan untuk estimasi cepat perhitungan besar distribusi gaya angkat di sepanjang sayap. Guna mencapai tingkat akurasi yang tinggi dari prediksi aerodinamika, simulasi Computational Fluid Dynamics (CFD) dengan berbasis persamaan Navier-Stokes dapat digunakan. Pesawat nirawak LSU dipilih untuk merepresentasikan analisis aerodinamika pada pesawat nirawak dengan konfigurasi twin-tailboom pusher. Fokus dari studi yang dilakukan adalah untuk memverifikasi dari metode pendekatan dari Schrenk dengan menggunakan metode yang memiliki akurasi tinggi seperti simulasi CFD. Tujuan dari studi adalah untuk menghitung distribusi gaya angkat sepanjang sayap dan menentukan seberapa besar error dari kedua metode.
Co-Authors Atmaja, Sigit Tri Fajar, M Hakim, TMI Hamonangan, Jefri Abner Hidayat, Kurnia Muhammad Fajar Pinindriya, Sinung Tirtha Ramadiansyah, Mohamad Luthfi Rosid , Nurhayyan H Tirtha, Sinung