Design Optimization of eVTOL Propellers using a Viscous-Extension Discrete Vortex Method

TL;DR

This paper introduces a viscous extension to the discrete vortex method, enabling efficient and accurate modeling of unsteady viscous flows for eVTOL propeller design optimization.

Contribution

It develops a hybrid viscous vortex method incorporating boundary layer theory, validated against CFD data, and applies it to optimize eVTOL rotor blade geometry for improved efficiency.

Findings

Validated the VDVM against experimental and CFD data with excellent agreement.

Optimized rotor geometry increased efficiency by 8.99%.

Demonstrated the method's effectiveness for unsteady viscous flow analysis.

Abstract

Potential flow theory remains a cornerstone of unsteady aerodynamics due to its computational efficiency in modeling complex flow phenomena. This study presents a significant advancement by integrating a viscous unsteady theory with established numerical vortex methods, creating a hybrid computational tool for low-to-moderate Reynolds number flows. We develop a Viscous Discrete Vortex Method (VDVM) by replacing the classical inviscid Kutta condition with a closure derived from triple-deck boundary layer theory, allowing the model to account for Reynolds number dependencies and unsteady viscous effects. The framework utilizes a three-dimensional vortex ring scheme and an unsteady Bernoulli formulation for load calculation. The model is validated against experimental and high-fidelity CFD data, showing excellent agreement in thrust and torque across a wide operational envelope. Using this validated framework, we conduct a systematic parametric investigation into rotor blade design for electric vertical take-off and landing (eVTOL). A sophisticated optimization of the spanwise geometry was performed: twist distributions were calculated by iteratively solving for axial and tangential induction factors to maintain optimal local angles of attack, while chord distributions were derived using the Adkins and Liebeck framework to satisfy the Betz condition for maximum efficiency. Results demonstrate that this tapered chord and nonlinear twist profile significantly mitigate tip losses and manage spanwise loading. The optimized geometry achieved an 8.99% increase in the efficiency compared to the baseline. This work bridges the gap between high-fidelity viscous analysis and fast vortex methods, providing a versatile tool for the performance-driven design of lifting surfaces in unsteady flight regimes.