Application of data assimilation to integration wind tunnel experiment and CFD toward for unceratinty reduction
| Project/Area Number |
15K21676
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| Research Category |
Grant-in-Aid for Young Scientists (B)
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| Allocation Type | Multi-year Fund |
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| Research Field |
Aerospace engineering
Statistical science
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| Research Institution | Japan Aerospace EXploration Agency |
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Principal Investigator |
Hiroshi Kato 国立研究開発法人宇宙航空研究開発機構, 研究開発部門, 研究開発員 (70722536)
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| Project Period (FY) |
2015-04-01 – 2018-03-31
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| Project Status |
Completed (Fiscal Year 2017)
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| Budget Amount *help |
¥4,030,000 (Direct Cost: ¥3,100,000、Indirect Cost: ¥930,000)
Fiscal Year 2017: ¥1,300,000 (Direct Cost: ¥1,000,000、Indirect Cost: ¥300,000)
Fiscal Year 2016: ¥1,300,000 (Direct Cost: ¥1,000,000、Indirect Cost: ¥300,000)
Fiscal Year 2015: ¥1,430,000 (Direct Cost: ¥1,100,000、Indirect Cost: ¥330,000)
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| Keywords | データ同化 / CFD / 風洞実験 / 剥離流れ / 遷移流れ / 疎情報 / 感度解析 / 流入乱れ度 / 遷移 / 逐次型データ同化 / 乱流モデル / 不確かさ |
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| Outline of Final Research Achievements |
In this study, we proposed a method to integrate experiment and numerical simulation in the aeronautical engineering field. The integration method was constructed by data assimilation, which is a statistical method. The purpose of this study is to address issues related to uncertainties of the experiments and numerical simulations. The effectiveness of the proposed method was investigated in the separate and transition flow problems. As for the separate flow problem, we successfully predicted the separated flow around wing-root section accurate by optimizing the model parameter value in the turbulence model. As for the transition flow problem, we developed the method to estimate the friction coefficient around the airfoil with the surface temperature information. And, we conducted the sensitivity analysis of the observation type. Then, we conducted the experiment to estimate the turbulent intensity for future accurate analysis for transition flows.
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Report
(4 results)
Research Products
(9 results)
