Assessment of Propeller Modeling Approaches for Aerodynamic Simulations

Abstract

Accurate modeling of propeller performance is crucial for the reliable aero-propulsive analysis of emerging aircraft configurations, particularly those employing distributed propulsion for improved efficiency and reduced emissions. This study evaluates the performance of propeller models - actuator disk and virtual blade - embedded within the DLR’s TAU and CODA CFD codes, comparing results to URANS simulations and wind tunnel experiments using the TU Delft ProWim propeller test case. The accuracy of both global performance parameters and propeller slipstream characteristics was assessed. Results indicate that while lower-fidelity models generally predict higher thrust and power coefficients, they demonstrate acceptable agreement with URANS and experimental data at low advance ratios. Discrepancies increase significantly at higher advance ratios, and both models exhibit inaccuracies in representing the propeller slipstream, particularly regarding blade tip loading and flow separation. The investigation confirms that incorporating modeling details, such as tangential induced velocities, significantly improves accuracy, especially at low advance ratios. These findings highlight the importance of careful model selection and parameter tuning for reliable aero-propulsive simulations of future propeller-driven aircraft.