VLM–2.5D RANS coupled solver for conceptual wing design

Abstract

In this study, a nonlinear formulation of the vortex lattice method is presented as an aerodynamic analysis approach that is both computationally efficient and of high fidelity. This method integrates viscous effects into the vortex lattice method by proposing a coupling with viscous airfoil data at selected spanwise wing sections. The viscous airfoil data is obtained via Reynolds–Averaged Navier–Stokes equations with the infinite swept wing assumption to capture cross-flow effects known as the 2.5D method. Since a nonlinear formulation of the vortex lattice method proposes a balance between speed and accuracy, it is suitable for conceptual wing design and optimization. Validation and verification studies demonstrate that the proposed VLM–2.5D RANS coupled solver achieves good agreement with theoretical predictions, experimental measurements, and high-fidelity CFD results across a range of wing geometries. By reducing the analysis time from several hours required by full 3D CFD simulations to only a few seconds, the method combines computational efficiency with improved accuracy compared to classical inviscid approaches. This makes it particularly suitable for use in conceptual wing design and optimization.