Vortex Loops Based Method for Subsonic Aerodynamic Loads Calculation

Georgy A Shcheglov,Sergey A Dergachev,L.H Chen,Y Kondo

doi:10.1051/matecconf/201822105004

Georgy A Shcheglov, Sergey A Dergachev + Show 2 more

Open Access

https://doi.org/10.1051/matecconf/201822105004

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Abstract

The new modification of vortex method is considered. It is based on closed vortex loops that can be considered as the separate vortex “superelement”. It is shown that such approach has number of advantages for vortex wakes evolution simulation. The loops generation algorithm permits to simulate the separation zone due to the self-organization of the loops. In this case, there is no need to determine the location of the vortex sheet separation zones. The developed software package can be used in the calculation of aerodynamic loads on unmanned aerial vehicles, as well as in solving the aeroelasticity problems of structural elements of these aircraft.

Highlights

Vortex elements methods are highly efficient for calculation of unsteady aerodynamic loads acting on aircraft moving at low subsonic speed, because they require significantly less computational resources in comparison with grid-based methods [1, 2]
In “classical” vortex element methods, for example, in the discrete vortex method [3], vorticity is concentrated in vortex framework segments and it is absent outside them in the flow
In case of vortex methods with separated vortex particles flow separation zones are formed “naturally” due to vorticity flux approach – vortex elements are generated on the whole body surface and these elements self-organization in the flow [4, 5]

Summary

Introduction

Vortex elements methods are highly efficient for calculation of unsteady aerodynamic loads acting on aircraft moving at low subsonic speed, because they require significantly less computational resources in comparison with grid-based methods [1, 2]. In these methods Lagrangian particles for vorticity transportation are used. In “classical” vortex element methods, for example, in the discrete vortex method [3], vorticity is concentrated in vortex framework segments and it is absent outside them in the flow This method requires number of empirical models to determine the location of the vortex sheet separation lines. This additional vorticity may cause significant errors at computing aerodynamic loads, acting the body

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