Aerodynamic Modelling of Unmanned Aerial System through Nonlinear Vortex Lattice Method, Computational Fluid Dynamics and Experimental Validation - Application to the UAS-S45 Bàlaam: Part 2.

This paper presents a comparison of a new non-linear formulation of the classical Vortex Lattice Method and a Computation Fluid Dynamics analysis in predicting the aerodynamic behaviour of an Unmanned Aerial System. The Computation Fluid Dynamics analysis used structured grid, for the airfoil, study and unstructured grid obtained from a grid convergence study, for the entire Unmanned Aerial System, that are needed to predict the aerodynamic coefficients. The Spalart-Allmaras and the k-ω models were used as turbulence models. The results have shown a close agreement between the methods presents and have indicated that the new formulation is adequate for aerodynamic model estimation.

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Introducción a la teoría VLM (Vortex Lattice Theory)

Ciencia y Poder Aéreo ◽

10.18667/cienciaypoderaereo.433 ◽

2015 ◽

Vol 10 (1) ◽

pp. 39 ◽

Cited By ~ 1

Author(s):

Santiago Pinzón

Keyword(s):

Fluid Dynamics ◽

Computational Fluid Dynamics ◽

Lattice Theory ◽

Vortex Lattice ◽

Lattice Method ◽

Vortex Lattice Method

<p>Los métodos de panel han sido ampliamente utilizados en la industria y se han establecido desde la década de 1970 en el cálculo y el análisis aerodinámico. Este artículo tiene como objetivo presentar una introducción a un método numérico en aerodinámica altamente utilizado en CFD (Computational Fluid Dynamics) para el cálculo de coeficientes aerodinámicos en una superficie alar. El artículo se enfoca en presentar un resumen detallado de este método conocido como VLM o Vortex Lattice Method. Es importante anotar, que este estudio se presenta como un artículo de reflexión y hace parte de un capítulo de una tesis de maestría en Ingenieria Aeroespacial. Por ende, no realiza ninguna prueba o derivación teórica, su enfoque primario es realizar una aproximación analítica de un método computacional utilizado ampliamente en aerodinámica con el fin de presentarle al lector una breve introducción matemática del método VLM y su importancia en el campo aeronáutico.</p>

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Aerodynamic Modelling of Unmanned Aerial System through Nonlinear Vortex Lattice Method, Computational Fluid Dynamics and Experimental Validation - Application to the UAS-S45 Bàlaam: Part 1.

INCAS BULLETIN ◽

10.13111/2066-8201.2020.12.1.9 ◽

2020 ◽

Vol 12 (1) ◽

pp. 91-103

Author(s):

Maxime Alex Junior KUITCHE ◽

Ruxandra Mihaela BOTEZ ◽

Arthur GUILLEMIN ◽

David COMMUNIER

Keyword(s):

Experimental Analysis ◽

Vortex Lattice ◽

Flight Dynamics ◽

Aircraft Design ◽

Unmanned Aerial System ◽

Lattice Method ◽

Vortex Lattice Method ◽

Viscous Forces ◽

Strip Theory ◽

Non Linear

This paper describes a methodology to predict the aerodynamic behaviour of an Unmanned Aerial System. Aircraft design and flight dynamics modelling are mainly concerned with aerodynamics, and thus its estimation requires a high level of accuracy. The work presented here shows a new non-linear formulation of the classical Vortex Lattice Method and a comparison between this methodology and an experimental analysis. The new non-linear Vortex Lattice Method was performed by calculating the viscous forces from the strip theory, and the forces generated by the vortex rings from the vortex lifting law. The experimental analysis was performed on a reduced scale wing in a low speed wind tunnel. The obtained results were also compared to those obtained from semi-empirical methods programmed using DATCOM and our Fderivatives new in-house codes. The results have indicated the accuracy of the new formulation and showed that an aerodynamic model obtained with the aerodynamic coefficients predicted with this method could be useful for flight dynamics estimation.

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Generalized vortex lattice method for planar supersonic flow

AIAA Journal ◽

10.2514/3.13655 ◽

1997 ◽

Vol 35 ◽

pp. 1230-1233

Author(s):

Paulo A. O. Soviero ◽

Hugo B. Resende

Keyword(s):

Supersonic Flow ◽

Vortex Lattice ◽

Lattice Method ◽

Vortex Lattice Method

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Static Aeroelastic Characteristics of Morphing Trailing-Edge Wing Using Geometrically Exact Vortex Lattice Method

International Journal of Aerospace Engineering ◽

10.1155/2019/5847627 ◽

2019 ◽

Vol 2019 ◽

pp. 1-15

Author(s):

Sen Mao ◽

Changchuan Xie ◽

Lan Yang ◽

Chao Yang

Keyword(s):

Vortex Lattice ◽

Deflection Angle ◽

Aircraft Design ◽

Analysis Method ◽

Lattice Method ◽

Trailing Edge ◽

Vortex Lattice Method ◽

Analysis And Design ◽

Aeroelastic Analysis ◽

Typical Model

A morphing trailing-edge (TE) wing is an important morphing mode in aircraft design. In order to explore the static aeroelastic characteristics of a morphing TE wing, an efficient and feasible method for static aeroelastic analysis has been developed in this paper. A geometrically exact vortex lattice method (VLM) is applied to calculate the aerodynamic forces. Firstly, a typical model of a morphing TE wing is chosen and built which has an active morphing trailing edge driven by a piezoelectric patch. Then, the paper carries out the static aeroelastic analysis of the morphing TE wing and corresponding simulations were carried out. Finally, the analysis results are compared with those of a traditional wing with a rigid trailing edge using the traditional linearized VLM. The results indicate that the geometrically exact VLM can better describe the aerodynamic nonlinearity of a morphing TE wing in consideration of geometrical deformation in aeroelastic analysis. Moreover, out of consideration of the angle of attack, the deflection angle of the trailing edge, among others, the wing system does not show divergence but bifurcation. Consequently, the aeroelastic analysis method proposed in this paper is more applicable to the analysis and design of a morphing TE wing.

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