Abstract

Numerical solvers using potential flow theory have become popular for fast and simple aerodynamic modelling in many applications. These include preliminary studies and budget-stringent small UAV design. Although there are several well-known solutions that have shown good agreement with experimental data, VSPAERO is a relatively recent alternative which is available within the NASA-developed OpenVSP aircraft design software. In this article a validation of the VSPAERO vortex-lattice method solver is carried out through a series of case studies. In particular, reference values obtained by empirical relations, other similar aerodynamic solvers, and experimental measurements are considered. The results of this assessment allow for the proposition of a series of recommendations regarding the meshing parameters, acceptable geometries, and valid flow conditions, which can be valuable reference for subsequent simulation studies using this software.

Abstract

Potential flow theory-based numerical solvers have gained popularity for rapid and straightforward aerodynamic modeling across various applications, particularly in the early stages of design and in resource-limited projects such as small unmanned aerial vehicles (UAVs). These solvers offer a cost-effective solution for analyzing aerodynamic performance, and several well-established methods have demonstrated strong alignment with experimental data. Among these solvers is VSPAERO, a relatively recent addition integrated within the National Aeronautics and Space Administration’s (NASA) OpenVSP aircraft design software. Despite its growing use, a comprehensive validation of the VSPAERO solver remains necessary to ensure its reliability in diverse scenarios. This article presents a validation of the VSPAERO solver by conducting a series of case studies. The assessment includes comparisons against reference values obtained through empirical relationships, results from other established aerodynamic solvers and experimental data from wind tunnel testing. The assessment covers a range of geometries and flow conditions, highlighting areas where the solver performs well and identifying any limitations in its application. The findings provide insights into the meshing parameters required for accurate simulations, as well as the types of geometries and flow conditions for which VSPAERO can be considered a reliable tool. As a conclusion, the article presents a series of best practices and guidelines that are recommended to improve the accuracy and efficiency of future erodynamic simulations conducted using this software. These recommendations are intended to serve as a valuable reference for both researchers and engineers involved in aerodynamic modeling, particularly those working on projects with tight budgets or in the preliminary stages of aircraft design.