| 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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| 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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