研究者業績
基本情報
- 所属
- 国立研究開発法人宇宙航空研究開発機構 宇宙科学研究所 名誉教授東京理科大学 客員教授
- 学位
- 工学博士(航空学)(東京大学)
- 連絡先
- fujii
rs.tus.ac.jp
- 通称等の別名
- Ko Fujii
- J-GLOBAL ID
- 200901042342169670
- researchmap会員ID
- 1000144496
- 外部リンク
経歴
19-
2023年10月 - 現在
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2015年4月 - 現在
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2015年4月 - 2023年9月
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2013年4月 - 2015年3月
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2003年10月 - 2015年3月
学歴
2-
- 1980年
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- 1974年
委員歴
14-
2020年10月 - 2026年9月
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2011年4月 - 2026年3月
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1991年4月 - 2026年3月
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2021年1月 - 2023年3月
受賞
32-
2024年7月
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2023年6月
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2023年3月
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2023年2月
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2022年9月
論文
433-
Flow, Turbulence and Combustion 2025年7月2日 査読有り招待有り筆頭著者<jats:title>Abstract</jats:title> <jats:p>Scale-resolving simulations possess considerable benefits over modeled approaches because of their ability to access the underlying nonlinear fluid dynamics, and thus to predict not only the correct phenomenology, but also to generate insights on strategies to mitigate or eliminate undesirable features. The expense of resolving all pertinent turbulent scales becomes prohibitive however, as the size of the problem, typically measured by the Reynolds number based on a suitable set of reference parameters, becomes large, as is the case with flows of industrial interest such as full aircraft or their complex subsystems. This paper provides an assessment of scale-resolving methods, including some of the main benefits as well as barriers for use on large problems, together with a perspective on historical and recent trends that appear promising in the quest for routine industrial use. The factors that constitute the biggest hurdles to achieving acceptable wall-clock times and costs include meshing of complicated geometries, numerical schemes that are robust as well as accurate, suitable initial and boundary conditions, economical yet appropriate representation of near-wall turbulence, code parallelism, scalability and portability, and post-processing of the resulting big datasets. Considerations for these interrelated aspects are highlighted in the context of several 3D problems of increasing complexity, from wing sections without and with sweep, to aircraft wakes, propulsion subsystems, scramjet flowpaths and finally, full aircraft including empennages. Collectively, these examples feature the benefits of scale-resolving simulations. An illustrative approach that has reached a relatively high level of maturity using automatic mesh generation, a non-dissipative yet robust scheme, wall-modeling of turbulence, superior scalability and requiring little user intervention beyond providing the surface model, is used to demonstrate the potential of scale-resolving simulations for industry, achievable at modest cost and in reasonable wall-clock time.</jats:p>
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IEEE Access 13 39631-39649 2025年 査読有り
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Proceedings of the Cambridge Unsteady Flow Symposium 2024 257-271 2024年12月3日 査読有り招待有り
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Aerospace 11(11) 866-866 2024年10月22日 査読有りThe advancement of Arrival MANager (AMAN) is crucial for addressing the increasing complexity and demand of modern airspace. This study evaluates the operational feasibility and effectiveness of an innovative AMAN designed for en route airspace, the so-called En Route AMAN. The En Route AMAN functions as a controller support system, facilitating the sharing of information between en route air traffic controllers (ATCos), approach controllers (current AMAN), and airport controllers (Departure Managers) in airports with multiple runways. The En Route AMAN aims to support upstream ATCos by sequencing and spacing of incoming streams via speed control and runway assignment, thereby enhancing overall air traffic efficiency. Human-In-The-Loop simulations involving rated ATCos are performed under scenarios that replicate real-world traffic and weather conditions. These simulations focus on upstream airspace to assess the impact of En Route AMAN on delay mitigation and ATCos’ performance. Unlike previous studies that solely relied on theoretical models and fast-time simulation for operational feasibility evaluation, this approach incorporates ATCos’ real-time decision-making, situational awareness, and task management, addressing critical operationalization challenges. The results demonstrated that the En Route AMAN could reduce the average flight duration by up to 25.6 s and decrease the total number of ATCo instructions by up to 20% during peak traffic volume. These findings support that the En Route AMAN is both operationally viable and effective in mitigating arrival delays, highlighting the importance of Human-In-The-Loop for practical validation.
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AIAA SCITECH 2024 Forum 2024年1月4日
MISC
191-
設計工学 = JOURNAL OF JAPAN SOCIETY FOR DESIGN ENGINEERING 43(4) 203-210 2008年4月5日
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日本流体力学会年会講演論文集 2008 135-135 2008年PARSEC airfoil parameters often used for transonic airfoil design are re-examined by data-mining Pareto-optimal airfoil designs. The Pareto-optimal airfoils are obtained by using a multiobjective evolutionary algorithm. For data mining, scatter plot matrix coupled with correlation coefficient is used. The present result shows that the PARSEC airfoil parameters may not be the best choice for transonic airfoil design. The result also indicates that data mining from Pareto-optimal airfoils may give more information than data mining from all feasible airfoils.
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ISAS Research Note (840) 2008年
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503 非平衡プラズマによる気流制御(第1報) : プラズマ誘起噴流による翼面剥離抑制効果(2)(OS5-1 機能性流体工学の先端融合化,OS5 機能性流体工学の先端融合化,オーガナイズドセッション)流体工学部門講演会講演論文集 2007 "503-1"-"503-4" 2007年11月17日The performance of the surface air-flow induced by non-thermal plasma is studied experimentally. The non-thermal plasma is generated by atmospheric dielectric-barrier discharge. The input discharge power was 1.8W. At first, flow induced by the discharge on a flat plate is investigated. Velocity profile is measured by a hot-wire anemometer. The maximum value 1.1 m/sec was observed on the plate surface. Secondary, separation control for wing surface flow is investigated using a 9cm chord NACA0015 in a wind tunnel at 20m/s of air stream velocity (Re〜1.2x10^5). Barrier discharge electrode is set on the leading edge of the wing. Separation angle is increased by 3.5 degrees and the maximum of the lift coefficient is improved by 12%.
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日本機械学會論文集. B編 = Transactions of the Japan Society of Mechanical Engineers. B 73(727) 649-649 2007年3月25日
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日本機械学会 第17回設計工学 システム部門講演会論文集, 2007 201-204 2007年This paper describes recent activity in JAXA aiming reformation of design and development (D & D) process by introduction of information technology, simulation technology, reliability engineering, etc for rocket valve reliability improvement. In this activity, JAXA's information system for rocket valve D & D will be developed by the end of FY2007. This information system consists of detailed FMEA/FTA utilization support tool, QFD utilization support tool, and material database system and material database utilization support tool. This information system will help to improve efficiency and reliability of D & D process of JAXA's rocket valves and other JAXA's products.
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第17回日本機械学会設計工学 システム部門講演会論文集, 2007 205-208 2007年In order to improve an efficiency of failure analysis process by using failure mode and effect analysis (FMEA) and failure tree analysis (FTA), detailed FMEA/FTA support tool is developed. By using this tool, failure mechanisms can be analyzed with FMEA approach as well as FTA approach. In order to improve coverage of the extracted failure modes, new failure analysis approach is proposed, which is based on the interface N2 chart. Interface N2 chart is N2 chart which is extended to express the interface of mechanical system. Interface N2 chart can also be used to visualize the failure analysis result to describe system structure based on the knowledge obtained in failure analysis such as causal relationship of fault propagation. New schematic visualization method is discussed to realize useful visualization tool which promotes comprehensive understanding of failure mechanism.
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http://www.jsme-fed.org/newsletters/2007_12/no2.html 2007 2007年
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計算力学講演会講演論文集 2006(19) 189-190 2006年11月2日
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流体工学部門講演会講演論文集 2006 "910-a" 2006年10月28日
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流体工学部門講演会講演論文集 2006 "910-1"-"910-4" 2006年10月28日Flow fields of the supersonic jets impinging on an inclined flat plate at high plate-angles are experimentally investigated using surface pressure measurement with pressure sensitive paint and Schlieren flow visualization. While Type I flow type is dominant at high plate angles, the present research found a new flow type "TYPE I with bubble" at plate angle between 60 and 80 degrees. The flow classification according to L/L_s' and plate angle indicated that the constant x/L'_s curve doesn't represent the boundary of Type I and Type II anymore at high plate angles between 60 and 90 probably because Type II flows at low plate angles and high plate angles is different phenomena. This study also indicates that the curve dividing Type I and Type I with bubble regions is same as the curve dividing Type II and Type II with bubble regions.
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計算工学 = Journal of The Japan Society for Computational Engineering and Science (JSCES) 11(3) 1389-1390 2006年7月31日
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計算工学 = Journal of The Japan Society for Computational Engineering and Science (JSCES) 11(1) 1284-1289 2006年2月28日
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流体工学部門講演会講演論文集 2005 313-313 2005年10月28日
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流体工学部門講演会講演論文集 2005 45-45 2005年10月28日
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流体工学部門講演会講演論文集 2005 144-144 2005年10月28日
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設計工学・システム部門講演会講演論文集 2005(15) 237-240 2005年8月2日An efficient and useful robust optimization approach, design for multi-objective six sigma (DFMOSS), has been developed. The DFMOSS couples the ideas of design for six sigma (DFSS) and multi-objective genetic algorithm (MOGA) to solve drawbacks of DFSS. DFMOSS obtains trade-off solutions between optimality and robustness in one optimization. In addition, it does not need careful parameter tuning. Robust optimizations of a test function and welded beam design problem demonstrated that DFMOSS is more effective and more useful than DFSS.
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日本流体力学会年会講演論文集 2005 205-205 2005年In this study, the acoustic wave propagations as a part of feedback-loop of The EDGETONE mechanism are verified. EDGEONE under various jet Reynolds and Mach numbers are computationally investigated. Two-dimensional compressible Navier-Stokes equations are solved by the 6^<th> order Pade type compact difference schemes and the 2^<nd> order Runge-Kutta time integration scheme. The computational results show following three patterns. When Mach number becomes higher, 1) EDGETONE phenomenon tends to disappear, 2) stage number becomes higher and 3) Strohal number of peak frequency becomes lower. The last pattern strongly show that the acoustic wave propagations as a part of feedback-loop exists.
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流体工学部門講演会講演論文集 2004 232-232 2004年11月24日
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日本流体力学会年会講演論文集 2004 660-661 2004年The edgetone mechanism is numerically simulated. Two-dimensional compressible Navier-Stokes equations are solved by the 6^<th> order Pade type compact difference schemes and the LU-ADI implicit time integration algorism. Present results are compared to that of the research in the past. It is revealed that grid resolution and scheme accuracy are important for the quantitative prediction of the edgetone. Also, computational results of present study are compared to the Brown's empirical formula. The frequency of the edgetone of present study is basically corresponding to that of the Brown's empirical formula.
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日本流体力学会年会講演論文集 2004 84-85 2004年Low Reynolds number airfoil design optimization is demonstrated. A two-dimensional Navier-Stokes solver is used for aerodynamic performance estimation of the airfoil design candidates because the viscosity effect is not negligible at low Reynolds number flight condition. An evolutionary computation is used for robust airfoil design optimization. The result demonstrated that the optimized airfoil is a very thin airfoil with significant camber. The result also showed that the low Reynolds number airfoil has time variation in its lift and drag.
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計算力学講演会講演論文集 2003(16) 741-742 2003年11月22日Flow-fields around basic SSTO-rocket configurations are numerically simulated by the Navier-Stokes computations. The study starts with the simulations of the Apollo-type configuration, in which the simulated results are comparing with NASA's experiments and the capability of CFD approach is discussed. Computed aerodynamic coefficients of Apollo configuration agree well with the experiments at subsonic, transonic and supersonic regime at all angles of attack. Dependencies of the computed results on the grid resolution is investigated.
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計算力学講演会講演論文集 2003(16) 743-744 2003年11月22日LES/RANS hybrid, LES and MILES simulations are applied to an axi-symmetric base flow for the supersonic flows at high Reynolds number. The idea of LES/RANS hybrid methodology is that RANS model is used in the boundary layer because of its low computational costs than LES, and LES is used in massively separated regions where unsteady flow structures are correctly captured. The subgrid-scale stresses are computed using the compressible form of Smagorinsky's model. Baldwin-Lomax model is applied to the RANS region. The LES/RANS hybrid simulations accurately capture the physics of turbulent flows. The reverse flow behind the base shows satisfactory agreement with the experimental data. The base pressure distributions, which is the primary parameter from the engineering interest, is in good agreement with the experimental results.
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宇宙科学研究所報告. 特集 46 191-202 2003年3月Flow fields over annular plug nozzles of the air breathing engines are computationally simulated and the boat-tail drag characteristics are clarified and discussed based on the simulation results. First, the simulations are carried out for the axi-symmetric nozzle configuration using compressible Navier-Stokes equations. The result shows that primary cause of the boat-tail drag turns out to be the low pressure region downstream of the Prandtl-Meyer expansion. Next, the flow field with the axisymmetric slit injection is simulated. The computed result shows that the secondary flow injection successfully reduces the boat-tail drag. The effect of the secondary flow injection through the clustered slots with the sonic condition given at the slot exits on the boat-tail surface is next investigated and the result is compared to that of the axisymmetric slit injection. The result for the clustered slot injection shows that the boat-tail drag is reduced by about 40%. Effect of the secondary flow injection demonstrated by the simplified axisymmetric simulations is still larger for the clustered slot injection. The flow field with the secondary-flow injected directly from the inner nozzle is next investigated. Comparison of the results for the secondary flow injected directly from the inner nozzle and for the secondary flow given as a sonic condition at the exit shows that there is little difference in the flow structure and the pressure distributions over the boat-tail region.
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可視化情報学会誌 = Journal of the Visualization Society of Japan 22(87) 252-253 2002年10月1日
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可視化情報学会誌 = Journal of the Visualization Society of Japan 22 343-346 2002年7月1日
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可視化情報学会誌 = Journal of the Visualization Society of Japan 22 443-446 2002年7月1日
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航空宇宙技術研究所特別資料: 航空宇宙数値シミュレーション技術シンポジウム2001論文集 = Special Publication of National Aerospace Laboratory: Proceedings of Aerospace Numerical Simulation Symposium 2001 53 285-290 2002年1月Transonic flows over the NACA64A010 airfoil oscillating in pitch about its one-quarter chord are numerically investigated for the assessment of the flow solver to predict the accurate unsteady aerodynamics forces. The effect of the outer boundary region and time accuracy in the implicit method such as LU-SGS time integration method is also described in this paper. Results at Mach number 0.8 over the airfoil oscillating with the reduced frequency of about 0.2 are compared with experimental data, respectively. The computed results with aft-shock attached flow show the importance of the computational domain and the implementation of the inner iteration method to the implicit time integration algorithm. For the case of shock induced separation flows, the computed results disagree with the experimental results due to the effect of the turbulence modeling, even with the increased time accuracy. 資料番号: AA0032819049 レポート番号: NAL SP-53
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流体工学部門講演会講演論文集 2001 283-283 2001年9月28日
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流体工学部門講演会講演論文集 2001 100-100 2001年9月28日CFD simulations using three-dimensional compressible Navier-Stokes equations are carried out for the establishment of the reliability of the CFD tools for the aerodynamic evaluation of space transportation systems. Simulations for Apollo-type capsule show that the simulations with typical number of grid points can give us reasonable result and CFD analysis can be a useful tool for the initial estimation of aerodynamic characteristics. Simulations for the FTB configuration show the dependency of the aerodynamic data on the order of accuracy of the simulations. The flow field near the base alters the characteristics. The example for the delta and double-delta wings which may be a candidate for the future TSTO systems shows that the success of the CFD simulations for delta wings does not necessarily justify the CFD results for similar configurations.
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日本流体力学会年会講演論文集 2001 253-254 2001年CFD has made great progress since early 70's, and now even three-dimensional problems, if not too large, can be solved using PC's. At the same time, large-scale simulations can be easily conducted under the computer environment available. People have been concentrated on the numerical algorithms and solutions methods until recently. We have to re-consider the strategy for the CFD methods under such environment. In this invited paper, three items are shown. One is re-consideration of the simulation process with a new idea of computer memory usage. This allows us to conduct much detailed and rational analysis of the unsteady flow field data. Second one is how to extend the users of CFD. We propose the WEB-CFD system as an example. Third one is the education of CFD. As CFD went into matured stage, the contents of the CFD lectures should also be changed. There may be much more that we should discuss, but the key message is that now is the time to consider the CFD methodology for the further development of CFD.
書籍等出版物
31-
Cambridge University Press 2015年4月
講演・口頭発表等
1066-
AJK FED2023(ASME-JSME-KSME Joint Fluids Engineering Conference) 2023年7月9日
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AJK FED2023(ASME-JSME-KSME Joint Fluids Engineering Conference) 2023年7月9日
所属学協会
11Works(作品等)
20共同研究・競争的資金等の研究課題
28-
日本学術振興会 科学研究費助成事業 2018年4月 - 2021年3月
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日本学術振興会 科学研究費助成事業 2017年11月 - 2019年3月
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ポスト「京」で重点的に取り組むべき社会的・科学的課題に関するアプリケーション開発・研究開発 萌芽的課題研究 2016年8月 - 2019年3月
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日本学術振興会 科学研究費補助金基盤A 2015年4月 - 2018年3月
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日本学術振興会 科学研究費助成事業 2012年4月 - 2015年3月