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-
ながれ : 日本流体力学会誌 = Nagare : journal of Japan Society of Fluid Mechanics 41(3) 151-155 2022年6月
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流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 51st-37th 2019年
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計算工学講演会論文集 Proceedings of the Conference on Computational Engineering and Science 22 5p 2017年5月
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流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 48th-34th 2016年
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流体工学部門講演会講演論文集 2015 "0615-1"-"0615-2" 2015年11月7日In this study, AC DBD plasma actuator is applied to control the flow around NACA0015 and Ishii airfoils in a low Reynolds number condition (Re = 63,000). Here, the Ishii airfoil is a high performance airfoil at the low Reynolds number condition. The DBD plasma actuator is located at x/c = 5% and is actuated in burst mode with the nondimensional burst frequency F+ from 0.1 to 20. Maximum control authority is achieved with Vpp = 6kV and F+higher than 6 for both airfoils. Results show that different effect of separation control between NACA0015 airfoil and Ishii airfoil.
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流体工学部門講演会講演論文集 2015 "0806-1"-"0806-4" 2015年11月7日The convective Mach number and density ratio dependences of sound sources and flow structures in a compressible mixing layer are investigated by direct numerical simulations. Characteristics of sound sources are analyzed using the source terms of Lighthill equation. As the Mach number increases sound source strength decreases, because vortex motion is weakened by compressibility. For density ratio dependence, the emission angle of Mach waves becomes shallower and vortices show sparse structures as density ratio increases. In addition, larger vortex structures appear at lower density side for higher density case.
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流体工学部門講演会講演論文集 2015 "0801-1"-"0801-3" 2015年11月7日The effects of nozzle geometry on the acoustic waves from Mach 1.9 supersonic jet are experimentally investigated. PIV and microphone measurements are conducted to analyze the relationship between flows and acoustic waves. In this study, three different nozzles of conical nozzle, convergent-divergent nozzle (C-D) nozzle, and tab C-D nozzle in which tab is attached in nozzle inlet to generate disturbance are considered. Three noise sources are identified. Conical nozzle case shows screech and broad band shock noise spectra because of the existence of strong shock train in flow. For the other two cases (C-D nozzle and tab nozzle), there are not clear shock associated noise spectra due to nearly ideally expanded condition by the nozzle geometries so that turbulent mixing noise should be dominant. Tab nozzle case shows higher frequency acoustic spectra than that of C-D case. This is because inflow become turbulent flow from the very beginning by the existence of tab so that smaller scale turbulence is generated.
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年次大会 : Mechanical Engineering Congress, Japan 2015 "S0530305-1"-"S0530305-5" 2015年9月13日Large-eddy simulations of the separated flow over an NACA0015 airfoil controlled by the DBD plasma actuator are conducted and the flow fields and the aerodynamic performances are compared with the Ishii airfoil, one of the high performance airfoil at the low Reynolds number. The DBD plasma actuator is set at the 5% chord length from the leading edge of NACA0015 airfoil and operated in burst mode at the Reynolds number Re=63,000. In both cruise and post stall angle of attack, Ishii airfoil show higher aerodynamic performance than NACA0015 airfoil when DBD plasma actuator is OFF. However, when the DBD plasma actuator is activated, NACA0015 show higher aerodynamic performance.
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流体工学部門講演会講演論文集 2014 "1401-1"-"1401-4" 2014年10月25日The characteristics of sound sources are analyzed by Lighthill equation based on the direct numerical simulations of compressible isotropic turbulence to investigate the physical mechanisms of the noise from fine scale turbulence and their interactions with shocklets. We study mainly on the compressibility effects on the sound source terms in Lighthill equation by comparing various turbulent Mach numbers (M_<t0> = 0.1 to M_<t0> = 1.0), where the sound source terms are decomposed into the Reynolds stress, entropy, and viscous term. We show that the Reynolds stress term is the most contributer to the overall sound sources for all Mach number cases, on the other hand, the sound level of viscosity term is very small. Also the characteristics of sound sources are changed due to the generation of shocklets for high Mach number cases. For low Mach number flows, the Reynolds stress term and entropy term has positive correlation so that the overall sound level is intensified. However, for high Mach number flows, the overall sound level is weakened because the negative correlation between the Reynolds stress term and entropy term becomes stronger and they partially cancels out each other.
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流体工学部門講演会講演論文集 2014 "1405-1"-"1405-3" 2014年10月25日In this presentation, first, the high-order upwind finite difference scheme is considered for the gas-particle multi-phase shock containing flows. We used an alternative weighted essentially non oscillation scheme (AWENO) which is the numerical flux formulation of a kind of weighted compact nonlinear scheme and the use of a positive preserving limiter proposed recently which can be used with numerical flux formulation. AN AWENO scheme with a positivity preserving limiter for the density of solid particles are implemented to the gas-particle multiphase flow solver. With an AWENO scheme, we conducted 2-dimensional numerical test problem. As a result, higher resolution is obtained without blowing up of the computation by using an AWENO scheme.
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年次大会 : Mechanical Engineering Congress, Japan 2014 "S0550303-1"-"S0550303-5" 2014年9月7日This paper investigates effective and robust feedback control of dynamic separation around the NACA0015 airfoil using a dielectric barrier discharge plasma actuator. A chord-based Reynolds number is 23,000, and an angle of attack varies from 7 to 15 degrees. The feedback control is based on the pressure coefficient on the airfoil surface (i.e., 0.4-chord location). Although the aerodynamic performance using the feedback control is comparable with that using the continuous mode, the input energy of the feedback control is significantly (approximately by 50%) reduced from that of the continuous mode.
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日本機械学会年次大会講演論文集(CD-ROM) 2014 ROMBUNNO.S0550404 2014年9月6日
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