Computational aerodynamic analysis of UiTM's Hawkeye UAV aircraft
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 se...
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| Main Authors: | , , , , |
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| Format: | Article |
| Published: |
The Aeronautical and Astronautical Society of the Republic of China
2021
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| Subjects: | |
| Online Access: | http://eprints.utm.my/id/eprint/95245/ http://dx.doi.org/10.6125/JoAAA.202106_53(2).23 |
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| Institution: | Universiti Teknologi Malaysia |
| Summary: | 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. |
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