Computational aerodynamic analysis of UiTM's Hawkeye UAV aircraft

• Main Authors: Johari, M. Syazwan, M. Ali, Zurriati, Wisnoe, Wirachman, Ismail, Noriswadi, Ishak, Iskandar S.
• Format: Article
• Published: The Aeronautical and Astronautical Society of the Republic of China 2021
• Subjects: TJ Mechanical engineering and machinery
• Online Access: http://eprints.utm.my/id/eprint/95245/; http://dx.doi.org/10.6125/JoAAA.202106_53(2).23

This paper discusses the aerodynamic characteristics of Hawkeye UAV aircraft with a forward-swept wing configuration. The unconventional wing design on Hawkeye allows for better maneuverability and stability during a field test but there were no prior studies on its aerodynamic characteristics. A series of CFD simulations were conducted using ANSYS Fluent to obtain the aerodynamic characteristic of Hawkeye; lift, drag and moment coefficient. A full-size model and Reynolds-averaged Navier-Stokes (RANS) numerical method-based equations, Spalart-Allmaras turbulence model was used for the simulation. The angle of attack of the aircraft differs from -10° to 30° with an interval of 2° at a flight condition of Mach number 0.1 (~35 m/s). The CFD results obtained will be used to calculate the aircraft performance in a real field test and for future improvement of the UAV.