Experimental and numerical investigation of low Reynolds number aerodynamic phenomena on a representative UAV configuration

Date

2026-3-27

Author

Günday, Yusuf

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This thesis presents a comprehensive investigation into low Reynolds number aerodynamics, focusing on the characterization of aerodynamic forces and flow phenomena affecting mini-class Unmanned Aerial Vehicles (UAVs). The study primarily aims to describe the complex nature of the Laminar Separation Bubble (LSB) and its decisive influence on lift, drag, and pitching moment characteristics. Unlike many studies in the literature limited to two-dimensional airfoils, this research utilizes a representative UAV configuration specifically developed with an FX-63137 wing profile and a cylindrical fuselage to provide a holistic understanding of full-scale UAV performance. Extensive experimental campaigns were conducted in the Ankara Wind Tunnel to capture the fundamental physics of the flow, including the observation of the hysteresis effect and the precise determination of separation and reattachment points. These experimental findings serve as a critical benchmark to evaluate the predictive accuracy of numerical methodologies used in the UAV design process. By analyzing the discrepancies between experimental data and CFD (Computational Fluid Dynamics) predictions, the thesis discusses the significance of low Reynolds effects in aerodynamic design. The results provide detailed experimental insights into the transitional flow regimes of small-scale UAVs, offering a validation test case and database for the development of more reliable design workflows.

Subject Keywords

Low Reynolds number aerodynamics, Experimental fluid dynamics, Laminar separation bubble (LSB), Hysteresis effect, BCM transition model

URI

https://hdl.handle.net/11511/119099

Collections

Graduate School of Natural and Applied Sciences, Thesis