Aerodynamic Investigation of Hover using Vortex Ring Wake Model and Free Vortex Wake Model

Date

2025-01-01

Author

Öztürk, İldeniz
Sezer Uzol, Nilay

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This work is licensed under a Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

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Modeling rotor inflow and wake dynamics is fundamental to understanding and improving rotorcraft performance. Especially, hover modeling plays an important role in aircraft design, aerodynamic assessments, and the development of control systems for helicopters and eVTOLs. To investigate the complexity of rotor aerodynamics, various methodologies with different levels of fidelity can be utilized, ranging from Blade Element Momentum Theory (BEMT) to high-fidelity Computational Fluid Dynamics (CFD). In this study, AeroROTOR, a fast in-house C code developed for rotor aerodynamics, is used to investigate the hover condition. AeroROTOR consists of two rotor wake analysis models: the Vortex Ring Wake (VRW) model and the Free Vortex Wake (FVW) model, coupled with the Blade Element Theory (BET). Rotor simulations with these wake models provide detailed investigations of the wake dynamics and blade aerodynamic forces. The HVAB rotor is used as a validation case and the free wake analyses are performed to investigate the hover condition and assess the capabilities of the wake analysis models by comparing the results for the rotor aerodynamic loads and wake characteristics with the experimental data.

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https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=105001267276&origin=inward
https://hdl.handle.net/11511/114362

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Department of Aerospace Engineering, Conference / Seminar