Convergence Acceleration of High Reynolds Number Transonic Flow based on Hyperbolic Navier-Stokes Equations
| Project/Area Number |
15K18286
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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
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| Research Institution | Japan Aerospace EXploration Agency |
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Principal Investigator |
Hashimoto Atsushi 国立研究開発法人宇宙航空研究開発機構, 航空技術部門, 主任研究開発員 (30462899)
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| Research Collaborator |
NAGAO Tsukasa
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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: ¥780,000 (Direct Cost: ¥600,000、Indirect Cost: ¥180,000)
Fiscal Year 2016: ¥1,170,000 (Direct Cost: ¥900,000、Indirect Cost: ¥270,000)
Fiscal Year 2015: ¥2,080,000 (Direct Cost: ¥1,600,000、Indirect Cost: ¥480,000)
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| Keywords | CFD / 数値流体力学 / 圧縮性流体力学 / 収束加速 / 非構造格子 / 双曲型 / 圧縮成流体力学 |
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| Outline of Final Research Achievements |
We applied a numerical method based on hyperbolic Navier-Stokes equations to computational fluid dynamics (CFD) on aircraft. We extended the method for three-dimensional problems and implemented it with an unstructured-grid flow solver FaSTAR. The original Navier-Stokes equations are five equations, whereas the hyperbolic equations are 20 equations since the equations of derivative values are added. When we solve the equations with an implicit time-evolution method, we need to solve the 20×20 matrix problems. In this research, we proposed an approximation method of the matrix. We showed that the approximation method can reduce the computational time remarkably and it is faster than the conventional CFD method.
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Report
(4 results)
Research Products
(3 results)
