Implementation of an Actuator Disc Model Using Blade Element Theory for Propellers into SU2 Software

Date

2023-9-11

Author

Yenipazar, Kaan

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The aim of the current study is to develop an actuator disc model in the SU2 (Stanford University Unstructured) CFD Solver using the blade element theory (BET) approach. The primary objective is to reduce computational costs and save time with accurate results. The integrated model has applications in optimizing rotating components such as propellers as well as accurately predicting wake structures, which is important for understanding slipstream effects in aircraft and wake interactions. The available methodologies in SU2 for simulating rotating blades include the steady-state rotating frame, unsteady sliding mesh, and the existing actuator disc model. The new actuator disc model proposed in this study is a steady-state model that assumes an infinite number of blades within the disc domain, making it applicable to varying flow conditions, such as the forward flight of helicopters or aircraft experiencing an angle of attack. In this model, the rotating parts are not physically represented in the numerical domain; instead, they are replaced by a disc, and their effects are implemented using momentum sources. The new model was validated by comparing it with experimental data and another CFD solver that is the rotating frame approach. These comparisons demonstrated that the new model is performs accurately and can be a fast alternative approach with enough accuracy compared to the expensive full rotor solutions with the rotating frame.

Subject Keywords

SU2, Blade Element, CFD, Actuator Disc, Propeller

URI

https://hdl.handle.net/11511/105617

Collections

Graduate School of Natural and Applied Sciences, Thesis