Bifurcation Analysis with Aerodynamic-Structure Uncertainties by the Nonintrusive PCE Method
An aeroelastic model for airfoil with a third-order stiffness in both pitch and plunge degree of freedom (DOF) and the modified Leishman–Beddoes (LB) model were built and validated. The nonintrusive polynomial chaos expansion (PCE) based on tensor product is applied to quantify the uncertainty of ae...
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| Format: | Article |
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Wiley
2017-01-01
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| Series: | International Journal of Aerospace Engineering |
| Online Access: | http://dx.doi.org/10.1155/2017/2571253 |
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| author | Linpeng Wang Yuting Dai Chao Yang |
| author_facet | Linpeng Wang Yuting Dai Chao Yang |
| author_sort | Linpeng Wang |
| collection | DOAJ |
| description | An aeroelastic model for airfoil with a third-order stiffness in both pitch and plunge degree of freedom (DOF) and the modified Leishman–Beddoes (LB) model were built and validated. The nonintrusive polynomial chaos expansion (PCE) based on tensor product is applied to quantify the uncertainty of aerodynamic and structure parameters on the aerodynamic force and aeroelastic behavior. The uncertain limit cycle oscillation (LCO) and bifurcation are simulated in the time domain with the stochastic PCE method. Bifurcation diagrams with uncertainties were quantified. The Monte Carlo simulation (MCS) is also applied for comparison. From the current work, it can be concluded that the nonintrusive polynomial chaos expansion can give an acceptable accuracy and have a much higher calculation efficiency than MCS. For aerodynamic model, uncertainties of aerodynamic parameters affect the aerodynamic force significantly at the stage from separation to stall at upstroke and at the stage from stall to reattach at return. For aeroelastic model, both uncertainties of aerodynamic parameters and structure parameters impact bifurcation position. Structure uncertainty of parameters is more sensitive for bifurcation. When the nonlinear stall flutter and bifurcation are concerned, more attention should be paid to the separation process of aerodynamics and parameters about pitch DOF in structure. |
| format | Article |
| id | doaj-art-b97ff61cdb9f43fca81cbc08c6d4bc9d |
| institution | Kabale University |
| issn | 1687-5966 1687-5974 |
| language | English |
| publishDate | 2017-01-01 |
| publisher | Wiley |
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| series | International Journal of Aerospace Engineering |
| spelling | doaj-art-b97ff61cdb9f43fca81cbc08c6d4bc9d2025-02-03T06:42:03ZengWileyInternational Journal of Aerospace Engineering1687-59661687-59742017-01-01201710.1155/2017/25712532571253Bifurcation Analysis with Aerodynamic-Structure Uncertainties by the Nonintrusive PCE MethodLinpeng Wang0Yuting Dai1Chao Yang2School of Aeronautic Science and Engineering, Beihang University, Beijing 100191, ChinaSchool of Aeronautic Science and Engineering, Beihang University, Beijing 100191, ChinaSchool of Aeronautic Science and Engineering, Beihang University, Beijing 100191, ChinaAn aeroelastic model for airfoil with a third-order stiffness in both pitch and plunge degree of freedom (DOF) and the modified Leishman–Beddoes (LB) model were built and validated. The nonintrusive polynomial chaos expansion (PCE) based on tensor product is applied to quantify the uncertainty of aerodynamic and structure parameters on the aerodynamic force and aeroelastic behavior. The uncertain limit cycle oscillation (LCO) and bifurcation are simulated in the time domain with the stochastic PCE method. Bifurcation diagrams with uncertainties were quantified. The Monte Carlo simulation (MCS) is also applied for comparison. From the current work, it can be concluded that the nonintrusive polynomial chaos expansion can give an acceptable accuracy and have a much higher calculation efficiency than MCS. For aerodynamic model, uncertainties of aerodynamic parameters affect the aerodynamic force significantly at the stage from separation to stall at upstroke and at the stage from stall to reattach at return. For aeroelastic model, both uncertainties of aerodynamic parameters and structure parameters impact bifurcation position. Structure uncertainty of parameters is more sensitive for bifurcation. When the nonlinear stall flutter and bifurcation are concerned, more attention should be paid to the separation process of aerodynamics and parameters about pitch DOF in structure.http://dx.doi.org/10.1155/2017/2571253 |
| spellingShingle | Linpeng Wang Yuting Dai Chao Yang Bifurcation Analysis with Aerodynamic-Structure Uncertainties by the Nonintrusive PCE Method International Journal of Aerospace Engineering |
| title | Bifurcation Analysis with Aerodynamic-Structure Uncertainties by the Nonintrusive PCE Method |
| title_full | Bifurcation Analysis with Aerodynamic-Structure Uncertainties by the Nonintrusive PCE Method |
| title_fullStr | Bifurcation Analysis with Aerodynamic-Structure Uncertainties by the Nonintrusive PCE Method |
| title_full_unstemmed | Bifurcation Analysis with Aerodynamic-Structure Uncertainties by the Nonintrusive PCE Method |
| title_short | Bifurcation Analysis with Aerodynamic-Structure Uncertainties by the Nonintrusive PCE Method |
| title_sort | bifurcation analysis with aerodynamic structure uncertainties by the nonintrusive pce method |
| url | http://dx.doi.org/10.1155/2017/2571253 |
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