<abstract xmlns="http://www.w3.org/1999/xhtml">

<p>The article presents the validation of two methods for analyzing the aerodynamic properties of the aircraft wing concerning aeroelastic effects. The first method is based on low-cost computational models (Euler–Bernoulli Beam Model and Vortex Lattice Method [VLM]). Its primary objective is to estimate the wing’s deformation early in the design stages and during the automatic optimization process. The second one is a method that uses solutions of unsteady Navier–Stokes equations (URANS). This method suits early design, particularly for unconventional designs or flight conditions exceeding lowfidelity method limits. The coupling of the flow and structural models was done by Radial Basis Functions implemented as a user-defined module in the ANSYS Fluent solver. The structural model has variants for linear and nonlinear wing deformations. Features enhancing applicability for real-life applications, such as the definition of deformable and nondeformable mesh zones with smooth transition between them, have been included in this method. A rectangular wing of a high-altitude long-endurance (HALE) aeroplane, built based on the NACA 0012 profile, was used to validate both methods. The resulting deflections and twists of the wing have been compared with reference data for the linear and nonlinear variants of the model.</p>
</abstract>

The article presents the validation of two methods for analyzing the aerodynamic properties of the aircraft wing concerning aeroelastic effects. The first method is based on low-cost computational models (Euler–Bernoulli Beam Model and Vortex Lattice Method [VLM]). Its primary objective is to estimate the wing’s deformation early in the design stages and during the automatic optimization process. The second one is a method that uses solutions of unsteady Navier–Stokes equations (URANS). This method suits early design, particularly for unconventional designs or flight conditions exceeding lowfidelity method limits. The coupling of the flow and structural models was done by Radial Basis Functions implemented as a user-defined module in the ANSYS Fluent solver. The structural model has variants for linear and nonlinear wing deformations. Features enhancing applicability for real-life applications, such as the definition of deformable and nondeformable mesh zones with smooth transition between them, have been included in this method. A rectangular wing of a high-altitude long-endurance (HALE) aeroplane, built based on the NACA 0012 profile, was used to validate both methods. The resulting deflections and twists of the wing have been compared with reference data for the linear and nonlinear variants of the model.

Numerical Modelling of Static Aeroelastic Deformations of Slender Wing in Aerodynamic Design

Transactions on Aerospace Research

This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

The article presents the validation of two methods for analyzing the aerodynamic properties of the aircraft wing concerning aeroelastic effects. The first...

Numerical Modelling of Static Aeroelastic Deformations of Slender Wing in Aerodynamic Design

Article Category: research article

Pubblicato online: 08 dic 2023

Pagine: 52 - 70

Ricevuto: 03 ott 2022

Accettato: 03 nov 2023

DOI: https://doi.org/10.2478/tar-2023-0023

Parole chiave
aeroelasticity, static analysis, beam model, radial basis functions

© 2023 Pamela Bugała et al., published by Sciendo

This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Numerical Modelling of Static Aeroelastic Deformations of Slender Wing in Aerodynamic Design

Article Category: research article

Pubblicato online: 08 dic 2023

Pagine: 52 - 70

Ricevuto: 03 ott 2022

Accettato: 03 nov 2023

DOI: https://doi.org/10.2478/tar-2023-0023

Parole chiaveaeroelasticity, static analysis, beam model, radial basis functions

© 2023 Pamela Bugała et al., published by Sciendo

This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Parole chiave
aeroelasticity, static analysis, beam model, radial basis functions