Aerothermodynamic Optimization of Aerospace Plane Airfoil Leading Edge
Aiming to mitigate the aerodynamic heating during hypersonic re-entry, the aerothermodynamic optimization of aerospace plane airfoil leading edge is conducted. Lift-todrag ratio at landing condition is taken as a constraint to ensure the landing aerodynamic performance. First, airfoil profile is par...
| Main Authors: | , , , |
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| Format: | Article |
| Language: | English |
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Instituto de Aeronáutica e Espaço (IAE)
2017-10-01
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| Series: | Journal of Aerospace Technology and Management |
| Subjects: | |
| Online Access: | https://www.jatm.com.br/jatm/article/view/820 |
| _version_ | 1811287678559191040 |
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| author | Chen Zhou Zhijin Wang Jiaoyang Zhi Anatolii Kretov |
| author_facet | Chen Zhou Zhijin Wang Jiaoyang Zhi Anatolii Kretov |
| author_sort | Chen Zhou |
| collection | DOAJ |
| description | Aiming to mitigate the aerodynamic heating during hypersonic re-entry, the aerothermodynamic optimization of aerospace plane airfoil leading edge is conducted. Lift-todrag ratio at landing condition is taken as a constraint to ensure the landing aerodynamic performance. First, airfoil profile is parametrically described to be more advantageous during the optimization process, and the Hicks-Henne type function is improved considering its application on the airfoil leading edge. Computational Fluid Dynamics models at hypersonic as well as landing conditions are then established and discussed. Design of Experiment technique is utilized to establish the surrogate model. Afterwards, the previously mentioned surrogate model is employed in combination with the Multi-Island Genetic Algorithm to perform the optimization procedure. NACA 0012 is taken as the baseline airfoil for case study. The results show that the peak heat flux of the optimal airfoil during hypersonic flight is reduced by 7.61% at the stagnation point, while the lift-to-drag remains almost unchanged under landing condition. |
| first_indexed | 2024-04-13T03:22:37Z |
| format | Article |
| id | doaj.art-4d0242f7261d4a258514eaef4c0c9b9f |
| institution | Directory Open Access Journal |
| issn | 2175-9146 |
| language | English |
| last_indexed | 2024-04-13T03:22:37Z |
| publishDate | 2017-10-01 |
| publisher | Instituto de Aeronáutica e Espaço (IAE) |
| record_format | Article |
| series | Journal of Aerospace Technology and Management |
| spelling | doaj.art-4d0242f7261d4a258514eaef4c0c9b9f2022-12-22T03:04:44ZengInstituto de Aeronáutica e Espaço (IAE)Journal of Aerospace Technology and Management2175-91462017-10-0194Aerothermodynamic Optimization of Aerospace Plane Airfoil Leading EdgeChen Zhou0Zhijin Wang1Jiaoyang Zhi2Anatolii Kretov3Nanjing University of Aeronautics and AstronauticsNanjing University of Aeronautics and AstronauticsNanjing University of Aeronautics and AstronauticsNanjing University of Aeronautics and AstronauticsAiming to mitigate the aerodynamic heating during hypersonic re-entry, the aerothermodynamic optimization of aerospace plane airfoil leading edge is conducted. Lift-todrag ratio at landing condition is taken as a constraint to ensure the landing aerodynamic performance. First, airfoil profile is parametrically described to be more advantageous during the optimization process, and the Hicks-Henne type function is improved considering its application on the airfoil leading edge. Computational Fluid Dynamics models at hypersonic as well as landing conditions are then established and discussed. Design of Experiment technique is utilized to establish the surrogate model. Afterwards, the previously mentioned surrogate model is employed in combination with the Multi-Island Genetic Algorithm to perform the optimization procedure. NACA 0012 is taken as the baseline airfoil for case study. The results show that the peak heat flux of the optimal airfoil during hypersonic flight is reduced by 7.61% at the stagnation point, while the lift-to-drag remains almost unchanged under landing condition.https://www.jatm.com.br/jatm/article/view/820Airfoil optimizationAerodynamic heatingHicks-Henne type functionAirfoil parameterizationSurrogate model. |
| spellingShingle | Chen Zhou Zhijin Wang Jiaoyang Zhi Anatolii Kretov Aerothermodynamic Optimization of Aerospace Plane Airfoil Leading Edge Journal of Aerospace Technology and Management Airfoil optimization Aerodynamic heating Hicks-Henne type function Airfoil parameterization Surrogate model. |
| title | Aerothermodynamic Optimization of Aerospace Plane Airfoil Leading Edge |
| title_full | Aerothermodynamic Optimization of Aerospace Plane Airfoil Leading Edge |
| title_fullStr | Aerothermodynamic Optimization of Aerospace Plane Airfoil Leading Edge |
| title_full_unstemmed | Aerothermodynamic Optimization of Aerospace Plane Airfoil Leading Edge |
| title_short | Aerothermodynamic Optimization of Aerospace Plane Airfoil Leading Edge |
| title_sort | aerothermodynamic optimization of aerospace plane airfoil leading edge |
| topic | Airfoil optimization Aerodynamic heating Hicks-Henne type function Airfoil parameterization Surrogate model. |
| url | https://www.jatm.com.br/jatm/article/view/820 |
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