A fast correction method of model deformation effects in wind tunnel tests
A fast correction method of model deformation effects in wind tunnel tests
The influence of model deformation needs to be corrected before the aerodynamic force data measured in wind tunnel is applied to aircraft design. In order to obtain the aerodynamic forces on rigid model shape, this paper presents a fast correction method by establishing a mathematical modelling between aerodynamic forces and wing section torsion. Then the aerodynamic force coefficients on rigid model shape can be calculated quickly just by setting section torsion to zero. A 25-point simulation dataset of HIRENASD model generated by CFD and Static CAE approach is used to investigate the influence of section locations, basis function type, support radius and deformation perturbation on the prediction accuracy. Finally, the present correction method is applied to predict the aerodynamic forces on the rigid shape of a NASA common research model. The results of parametric analysis and application show that the present correction method with theWendland’s C6 function and a support radius of 1.0 can provide a reasonable prediction of aerodynamic forces on the rigid model shape.
fast correction method, model deformation, aerodynamic force modelling, radial basis function, wing section torsion
Sun, Y.
bbae09f1-8a43-414c-b0d6-409f3bf568dc
Wang, Y.
adc6c787-e577-46bf-bda7-740d56e7d554
Da Ronch, A.
a2f36b97-b881-44e9-8a78-dd76fdf82f1a
Meng, D.
4a4b696f-1879-4498-b16c-c8960a79d5be
Sun, Y.
bbae09f1-8a43-414c-b0d6-409f3bf568dc
Wang, Y.
adc6c787-e577-46bf-bda7-740d56e7d554
Da Ronch, A.
a2f36b97-b881-44e9-8a78-dd76fdf82f1a
Meng, D.
4a4b696f-1879-4498-b16c-c8960a79d5be
Sun, Y., Wang, Y., Da Ronch, A. and Meng, D.
(2018)
A fast correction method of model deformation effects in wind tunnel tests.
Aerospace, 5 (4), [125].
(doi:10.3390/aerospace5040125).
Abstract
The influence of model deformation needs to be corrected before the aerodynamic force data measured in wind tunnel is applied to aircraft design. In order to obtain the aerodynamic forces on rigid model shape, this paper presents a fast correction method by establishing a mathematical modelling between aerodynamic forces and wing section torsion. Then the aerodynamic force coefficients on rigid model shape can be calculated quickly just by setting section torsion to zero. A 25-point simulation dataset of HIRENASD model generated by CFD and Static CAE approach is used to investigate the influence of section locations, basis function type, support radius and deformation perturbation on the prediction accuracy. Finally, the present correction method is applied to predict the aerodynamic forces on the rigid shape of a NASA common research model. The results of parametric analysis and application show that the present correction method with theWendland’s C6 function and a support radius of 1.0 can provide a reasonable prediction of aerodynamic forces on the rigid model shape.
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Accepted/In Press date: 22 November 2018
e-pub ahead of print date: 30 November 2018
Keywords:
fast correction method, model deformation, aerodynamic force modelling, radial basis function, wing section torsion
Identifiers
Local EPrints ID: 427950
URI: http://eprints.soton.ac.uk/id/eprint/427950
ISSN: 2226-4310
PURE UUID: 142332ce-14e0-47f0-b404-bc78c7eb87d6
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Date deposited: 05 Feb 2019 17:30
Last modified: 16 Mar 2024 04:15
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Author:
Y. Sun
Author:
Y. Wang
Author:
D. Meng
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