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All Journal Jurnal Asiimetrik: Jurnal Ilmiah Rekayasa Dan Inovasi
Saphira Anggraita Siswanto
Universitas Pembangunan Nasional Veteran Jakarta
Civil Engineering, Building, Construction & Architecture Computer Science & IT Electrical & Electronics Engineering Industrial & Manufacturing Engineering

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Analysis of the Use of Bio Flap on NACA 4415 with Numerical Methods James Julian; Saphira Anggraita Siswanto; Fitri Wahyuni; Nely Toding Bunga
Jurnal Asiimetrik: Jurnal Ilmiah Rekayasa dan Inovasi Volume 5 Nomor 2 Tahun 2023
Publisher : Fakultas Teknik Universitas Pancasila

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35814/asiimetrik.v5i2.4768

Abstract

This study was conducted using the Computational Fluid Dynamics (CFD) method using the Reynolds Averaged Navier Stokes (RANS) approach. The type of airfoil used in this study is the asymmetry NACA 4415 airfoil type. In this paper, computational tests were carried out on the airfoil with the addition of bionic flaps on its trailing edge. This study's update tests three variations of the Reynolds number: Re = 106, Re = 5 × 105, and Re = 3 × 105. The airfoil test was carried out at AoA 0°–25°. The addition of bionic flaps causes a decrease in lift performance at low AoA, but at high AoA, it can increase lift performance on airfoils. In addition, adding a bionic flap on the airfoil can delay the occurrence of a stall. At AoA 10°–13°, the Cd of the three variations of the Reynolds number experiences an increase in performance. Then, from this computational test, the resulting Coefficient moment (Cm) is a pitch down because the torque is below zero.
Numerical Investigation on Aerodynamic Characteristics of Bio-Inspired Nose Airfoil NACA 4415 Fitri Wahyuni; James Julian; Saphira Anggraita Siswanto; Riki Hendra Purba; Fathin Muhammad Mahdhudhu; Elvi Armadani; Nely Toding Bunga
Jurnal Asiimetrik: Jurnal Ilmiah Rekayasa Dan Inovasi Volume 8 Number 1 (2026)
Publisher : Fakultas Teknik Universitas Pancasila

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35814/asiimetrik.v8i1.9428

Abstract

It is widely believed that bionic airfoils can influence aerodynamic performance. Therefore, this study focuses on analyzing the effect of a bio-inspired nose on the NACA 4415 airfoil. This study uses roughtoothed dolphins and spinner dolphins as modifications of the airfoil, which are then tested at Re = 1.6×105 using Computational Fluid Dynamics (CFD). From the simulation results, it was shown that the baseline NACA 4415 has the best aerodynamic performance across all Angles of Attack (AoA). The average percentage increase in Cd for the spinner dolphin is lower, at 40.399% compared to the baseline. On the other hand, the roughtoothed dolphin shows a higher percentage increase in Cd with an average of 51.479% compared to the baseline. While in the Cl data, the rough-toothed dolphin has a larger average percentage decrease, at -10.472%, whereas the spinner dolphin achieves an average decrease of only -5.194% compared to the baseline. Therefore, it can be concluded that the rough-toothed and spinner dolphin modifications do not enhance the aerodynamic performance of the NACA 4415 airfoil at AoA. However, at low AoA, the roughtoothed dolphin modification performs comparably to the baseline NACA 4415 airfoil.
Analysis of the Use of Bio Flap on NACA 4415 with Numerical Methods: Analisis Penggunaan Bio Flap pada NACA 4415 dengan Metode Numerik James Julian; Saphira Anggraita Siswanto; Fitri Wahyuni; Nely Toding Bunga
Jurnal Asiimetrik: Jurnal Ilmiah Rekayasa Dan Inovasi Volume 5 Nomor 2 Tahun 2023
Publisher : Fakultas Teknik Universitas Pancasila

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35814/asiimetrik.v5i2.4768

Abstract

This study was conducted using the Computational Fluid Dynamics (CFD) method using the Reynolds Averaged Navier Stokes (RANS) approach. The type of airfoil used in this study is the asymmetry NACA 4415 airfoil type. In this paper, computational tests were carried out on the airfoil with the addition of bionic flaps on its trailing edge. This study's update tests three variations of the Reynolds number: Re = 106, Re = 5 × 105, and Re = 3 × 105. The airfoil test was carried out at AoA 0°–25°. The addition of bionic flaps causes a decrease in lift performance at low AoA, but at high AoA, it can increase lift performance on airfoils. In addition, adding a bionic flap on the airfoil can delay the occurrence of a stall. At AoA 10°–13°, the Cd of the three variations of the Reynolds number experiences an increase in performance. Then, from this computational test, the resulting Coefficient moment (Cm) is a pitch down because the torque is below zero.
Co-Authors Bunga, Nely Toding Elvi Armadani Fathin Muhammad Mahdhudhu Fitri Wahyuni James Julian Riki Hendra Purba