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All Journal Jurnal Ilmu Pendidikan JPTK: Jurnal Pendidikan Teknologi dan Kejuruan Jurnal Pamator : Jurnal Ilmiah Universitas Trunojoyo Madura International Journal of Artificial Intelligence Research INTEGER: Journal of Information Technology Prosiding SNITP (Seminar Nasional Inovasi Teknologi Penerbangan) Letters in Information Technology Education (LITE) Journal of Research in Social Science and Humanities Indonesian Journal of Applied and Industrial Sciences (ESA) Journal of Public Transportation Community Sainstech Nusantara
Pambudiyatno, Nyaris
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The Effect of Triangular Vortex Generator Straight Arrangements on the NACA 0012 Airfoil Using a Smoke Generator Trysnavirensa, Saniyya Nahda; Putro, Setyo Hariyadi Suranto; Pambudiyatno, Nyaris
SAINSTECH NUSANTARA Vol. 2 No. 1 (2025): February 2025
Publisher : Nusantara Publisher

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.71225/jstn.v2i1.86

Abstract

Aerodynamics is a fundamental discipline in the field of aviation, as it governs the airflow around an aircraft, enabling lift generation. The design and construction of aircraft wings are critical, as they directly impact the aircraft's stability and lift efficiency. Thus, aerodynamics plays a pivotal role in the performance, functionality, and overall design of aircraft. With advancements in modern aviation, continuous improvements are being made in the design and configuration of wing models. To analyze the aerodynamic characteristics of an aircraft wing, the airflow distribution method is commonly employed, one of which includes the use of vortex generators. This study investigates the effects of adding triangular vortex generators to a NACA 0012 airfoil, utilizing the smoke generator method in a straight arrangement. The experiments were conducted in an open-circuit wind tunnel with an airflow velocity of 5 m/s. The angles of attack tested were 0°, 4°, 8°, 10°, 15°, 17°, and 20°. The vortex generators were positioned 20% of the chord length from the leading edge of the airfoil. The experimental results demonstrate that the addition of triangular vortex generators increases the distance to the furthest point of separation and enhances the transition point on the airfoil. The aerodynamic performance of the airfoil was evaluated based on the observed airflow patterns around the airfoil, which showed notable differences compared to the airfoil without vortex generators.
3 Dimensional Aerodynamic Analysis of Additional Slat and Slot on Airfoil Naca 23018 Using Computational Fluid Dynamic Method Rimadhani Hermawati, Tarysa; Hariyadi Suranto, Setyo; Pambudiyatno, Nyaris
SAINSTECH NUSANTARA Vol. 2 No. 2 (2025): May 2025
Publisher : Nusantara Publisher

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.71225/jstn.v2i2.112

Abstract

Slat and Slot is one of the components of high lift devices in addition to the flaps used on the wings of the aircraft. It has a function to provide a lifting force when the attack angle of the aircraft wing is high. The topic studied in this study was the flow that crossed the NACA 23018 airfoil with the addition of slats and slots. The research method used is a 3-dimensional analysis method using ansys fluent software. The test object to be used is the NACA 23018 airfoil. This research was conducted numerically using the CFD (computational fluid dynamic) method. The purpose of this study was to compare the characteristics of fluid flow with or without the addition of slats and slots. The speed used is 40m/s with a spacing of 5%, 8%, and 10% chords and the angle of attack used as variation parameters are (α) = 0°, 2°, 4°, 6°, 8°, 10°, 12°, 15°, 16°, 17°, 18°, 19° and 20°. The results showed that with the addition of slats and slots on the NACA 23018 Airfoil, it can increase the lifting force at the high angle of attack, as well as delay the stall due to delays in airflow separation. In the airfoil variation with a slat clearence of S = 10% (α = 20⁰) has a lift coefficient with the most maximum value and a more even distribution. So in this study, it came to the conclusion that the most effective variation used in the NACA 23018 Airfoil was with a 10% slat clearence at subsonic speed
NTP Server Design as a Mitigation of Time Difference at Perum LPPNPI Kendari Branch Pambudiyatno, Nyaris; Kurniawan Putra, Muh. Rayhan; Pragolo, Argo
SAINSTECH NUSANTARA Vol. 1 No. 3 (2024): August 2024
Publisher : Nusantara Publisher

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.71225/jstn.v1i3.70

Abstract

In the world of aviation, it takes the right time, time synchronization is very important for the aviation system. If the time of the flight telecommunication facility is out of sync or out of sync, the flight data will be chaotic, so it is not known when the aircraft will land. If the time is not synchronized, data on accident incidents will be difficult to find. This research method uses an Microcontroller connected to the Network Time Protocol Server through internet media, then the Network Time Protocol Server generates time data in the form of Coordinate Universal Time. The Microcontroller functions as a server on the device that will perform time synchronization, and the Network Time Protocol Server data has accurate time accuracy. In the event of a time shift it will be compensated by the Microcontroller.
Co-Authors Anung Nugroho, Dimas Bagus Hariyanto, Bambang Bambang Bagus Harianto Dwi Irawati, Viona Fatmawati Sabur Harianto, B.B Harianto, Bambang Bagus Hariyadi Suranto, Setyo Imam Suharto, Teguh Irfansyah, Ade Kurniawan Putra, Muh. Rayhan p, Achmad Setiyo Prabowo, Achmad Setiyo Pragolo, Argo Pratama, Rionara Sendi Prayitno, Hadi Setiyo Rifai, Moch. Rimadhani Hermawati, Tarysa Sazali, Abdul Muti Setiawan, Ariyono Setyo Hariyadi Suharto, Teguh Imam Sukma, Meita Maharani Thiro Kabul Yuniar, Yudhis Trysnavirensa, Saniyya Nahda WULANDARI, RR.RETNO SAFITRI Yuyun Suprapto