2003 Fiscal Year Final Research Report Summary
Evolution of the Unstructured Mesh CFD for Multi-Disciplinary Problems
| Project/Area Number |
13555043
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| Research Category |
Grant-in-Aid for Scientific Research (B)
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| Allocation Type | Single-year Grants |
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| Section | 展開研究 |
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| Research Field |
Fluid engineering
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| Research Institution | Tohoku University |
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Principal Investigator |
NAKAHASHI Kazuhiro Tohoku University, Gradate School of Engineering, Professor, 大学院・工学研究科, 教授 (00207854)
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| Co-Investigator(Kenkyū-buntansha) |
MATSUSHIMA Kisa Tohoku University, Gradate School of Engineering, Associate Professor, 大学院・工学研究科, 助教授 (40332514)
FUKUNISHI Yu Tohoku University, Gradate School of Engineering, Professor, 大学院・工学研究科, 教授 (60189967)
FUKUNAGA Hisao Tohoku University, Gradate School of Engineering, Professor, 大学院・工学研究科, 教授 (50134664)
KODERA Masatoshi Japan Aerospace Exploration Agency, Researcher, 研究員
KATO Takuma Tohoku University, Institute of Fluid Sciences, Lecturer, 流体科学研究所, 講師 (60292231)
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| Project Period (FY) |
2001 – 2003
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| Keywords | Unstructured grid / Navier-Stokes equations / CFD / Parallel Computation |
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| Research Abstract |
In the developments of the unstructured-mesh CFD, several algorisms to improve the capability and the reliability of the surface meshing and the hybrid meshing were proposed. The flow solver was improved in its computational efficiency by utilizing the parallel computers. The accuracy was also improved by employing new turbulence models. The capability of the unstructured-mesh CFD code was demonstrated for flows around airplanes, golf balls, insects, and so on. For the simulation of insects, a new code for flow-structured coupling problems is under developing.
The developed CFD code was applied to multi-element airfoils for the validation of the code. It was also extended to the shape optimizations. In this study, the moving mesh method man developed to treat the shape change of the target. This dynamic mesh method can treat the airplanes with movable control surfaces as well.
For the design, the inverse method was coupled with the unstructured-mesh CFD. This was effective to design a supersonic airplane with natural laminar wings which had been developed under the Japan aerospace exploration agency. An airplane that flies at near-sonic velocity was investigated by using the unstructured-mesh CFD. The computed result showed that there was an optimum point to cruise at near-sonic velocity. Moreover, the CFD was utilized to optimize the shape of near-sonic airplane to improve the lift-to-drag ratio.
The unstructured mesh CFD was applied to simulate the combusting flows inside a supersonic combustion ramjet engine. This demonstrated the capability of the unstructured mesh CFD code developed in the present study. Flow inside a micro-gas turbine was also investigated by the present code.
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