A New Rapid Vortex-Based Aerodynamic Model for Propeller-Wing Interaction

This paper presents a rapid, multi-fidelity modelling framework for propeller aerodynamic analysis, with emphasis on methods suitable for industrial deployment under tight turnaround constraints. A hierarchy of approaches is considered, ranging from classical Blade Element Momentum Theory (BEMT) to lifting-line formulations coupled with blade-element aerodynamics and vortex-based induced-velocity models derived from the Biot--Savart law. The framework is designed to support iterative design and integration within industrial aero-data workflows, where numerical robustness, traceable modelling assumptions and controllable computational cost are critical. The governing formulations, coupling strategy and numerical implementation choices are described in detail. Representative results are provided to illustrate the behaviour of the model hierarchy and to highlight current limitations related to wake modelling and induced-velocity representation. The study motivates the use of mid-fidelity solvers as a practical compromise between physical fidelity and computational efficiency for propeller analysis in early design and integration contexts.