Short Title: Int. J. Mech. Eng. Robot. Res.
Frequency: Bimonthly
Professor of School of Engineering, Design and Built Environment, Western Sydney University, Australia. His research interests cover Industry 4.0, Additive Manufacturing, Advanced Engineering Materials and Structures (Metals and Composites), Multi-scale Modelling of Materials and Structures, Metal Forming and Metal Surface Treatment.
2025-02-28
2025-01-20
2025-01-09
Manuscript received July 30, 2024; revised August 23, 2024; accepted October 3, 2024; published February 10, 2025
Abstract—This research aims to determine the aerodynamic performance of the swayasa aircraft airfoil flap angle configuration. The aerodynamic performance is the pressure coefficient (CP) and flow separation of the optimal swayasa aircraft airfoil flap angle configuration. For this purpose, a computational approach using a Computational Fluid Dynamics (CFD) program and experimental research in a sub-sonic wind tunnel were conducted. The wing model of the swayasa aircraft uses the NACA 23012 airfoil model with pressure taps around the surface by giving the same main flap angle (Fu) configuration treatment at 4 levels of flap angle, namely −10°, 0°, 15° and 30°; then each level is given a variation of the control flap or aileron angle (Fk) at angles of −10°, 0°, 15°, 30°, and 45°. Furthermore, an airflow velocity of 22 m/s or Reynolds number (Re) 270,886 was applied at angles of attacks (α) of −10°, 0°, 15°, and 20°. Experimental results show the characteristics of pressure coefficient (CP) and flow separation at the same angle α, forming the same pattern at various angles Fu and angle Fk. Furthermore, the computational results of velocity contours show the configuration of using Fu with Fk, resulting in an increase in pressure on the lower surface of the airfoil at positive Fu angles and a decrease in pressure on the upper surface of the airfoil, resulting in higher vortices or turbulence in the area behind Fu and around Fk.Keywords—NACA 23012 airfoil, Fu and Fk flap angle configurations, pressure coefficient (CP). flow separation, Computational Fluid Dynamics (CFD) computation Cite: Nasaruddin Salam, Rustan Tarakka, Lukman Kasim, and Kristiana Pasau, "Aerodynamic Performance of Swayasa Aircraft Wing Model against the Effect of Airfoil Flap Angle Configuration," International Journal of Mechanical Engineering and Robotics Research, Vol. 14, No. 1, pp. 48-58, 2025. doi: 10.18178/ijmerr.14.1.48-58Copyright © 2025 by the authors. This is an open access article distributed under the Creative Commons Attribution License which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited (CC BY 4.0).
