工学修士, 東京大学

工学博士, 東京大学

Velocity/Temerature Fluctuation, Pressure/Acustics measurement

Low-Turbulence Wind Tunnel Test

Compact Schemes for Compressible Turbulence

圧縮性乱流、幾何学

Aerospace, marine, and maritime Engineering, Aerospace engineering

Manufacturing technology (mechanical, electrical/electronic, chemical engineering), Fluid engineering

01 Mar. 2013 - 30 Sep. 2015
電気通信大学, 知能機械工学科, 就職委員長

01 Apr. 2011 - 31 Mar. 2012
電気通信大学大学院, 情報理工学研究科、知能機械工学専攻, 専攻長、学科長

01 Apr. 2009 - 31 Mar. 2010
電気通信大学, 電気通信学部、知能機械工学科, 専攻主任

01 Mar. 2008
電気通信大学電気通信学部, 教授

01 Nov. 2002 - 28 Feb. 2008
広島大学, 教授

Mar. 1981
The University of Tokyo, Graduate School, Division of Engineering, 舶用機械工学専攻

Mar. 1978
The University of Tokyo, Graduate School, Division of Engineering, 舶用機械工学専攻

Mar. 1975
Kyoto University, Faculty of Engineering, 精密工学科

01 Apr. 2017 - 31 Mar. 2018
東京都高度研究等外部評価委員, 東京都高度研究等外部評価委員委員会, Autonomy

Mar. 2009 - Feb. 2011
理事, 日本流体力学会, Society

Apr. 2006 - Mar. 2007
評議員, 日本機械学会, Society

Apr. 2004 - Mar. 2006
機械学会論文集編集委員, 日本機械学会, Society

2000 - 2001
評議員, 日本流体力学会, Society

1999 - 2001
第二出版部会校閲委員, 日本機械学会, Society

1999 - 1999
計算流体シンポジウムオーガナイザー, 日本流体力学会, Society

1998 - 1999
乱流シンポジウムオーガナイザー, 日本流体力学会, Society

1997 - 1997
計算流体シンポジウム幹事, 日本流体力学会, Society

1994 - 1995
分科会委員, 日本機械学会, Society

1993 - 1994
第二出版部会校閲委員, 日本機械学会, Society

1992 - 1993
分科会委員, 日本機械学会, Society

Jun. 2012
日本伝熱学会
日本伝熱学会貢献賞
Japan society

Feb. 2010
日本流体力学会
日本流体力学会フェロー

Apr. 2009
日本機械学会
日本機械学会賞(論文）
Japan

Oct. 2008
日本機械学会
日本機械学会流体部門貢献表彰

Mar. 2003
日本機械学会
日本機械学会フェロー

Mar. 2003
日本機械学会
日本機会学会教育賞
Japan

Oct. 1998
ターボ機械協会
畠山研究賞

May 1994
ターボ機械協会論文賞

Numerical Simulation of the Develpment of Linear Unstable Modes in a Supersonic Boundary Layer
M.Yoshino; K.Suda; H.Maekawa; Y.Inoue
Proceedings of 13TH Inte$rnational Conference on Flow Dynamics, 1, 1, 98-100, 11 Oct. 2016
International conference proceedings, English

A Study of Supercritical Transitional Structures of a Boundary Layer
S.Takahashi; I.Jimbo; Y.Inoue; H.Maekawa
Proceedings of 27th International Symposium on Transport Phenomena, 1, 1, 101-111, 20 Sep. 2016, Peer-reviwed
International conference proceedings, English

Turbulent Boundary Layer with a linear velocity profile far from a wall generated by fuctional Riblets
Y.Toriumi; Y.Inoue; M.Maekawa
Proceedings of Fluid Dynamics of Near-Wall Turbulence, 2, 2, 1-2, 22 Jun. 2016, Peer-reviwed
International conference proceedings, English

Effects of near-boundary filters on computations of aerodyanmic sound genarated by vortical flows near a wall
Yuki WAKAMATSU; Hiroaki WATANABE; Yohei INOUE; Hiroshi MAEKAWA
ながれ, 日本流体力学会, 34, 6, 433-444, 25 Dec. 2015, Peer-reviwed, 本研究は,境界近傍におけるフィルタの取り扱いが空力音の数値計算に与える影響を渦と壁面との干渉によって発生する空力音を用いて明らかにした.Visbal and Gaitonde(AIAA Paper,(1998))の低次精度コンパクトフィルタおよびGaitonde and Visbal(AIAA Journal,(2000))の6次精度以上の境界コンパクトフィルタを境界近傍のフィルタに適用した場合の空力音計算での問題点を示し,適切と考えられる境界近傍のフィルタリング手法を示した.Compact schemes combined with compact filters are widely used for computational aeroacoustics. As compact filters require special treatment near the boundaries, near boundary filters were proposed by Visbal and Gaitonde (AIAA Paper, (1998)) and Gaitonde and Visbal (AIAA Journal, (2000)). However, these proposed near-boundary filter formulas have several drawbacks, the influence on computations of aerodynamic sound has not been uncovered. In this paper, we focus on the effects of these filters at the near-boundary points on the accurate calculation of aerodynamic sound generated by vortical flows near a wall. The results reveal that the appropriate filtering at the near-boundary nodes with no adverse impact on stability is essential to compute aerodynamic sound. The application of high-order boundary formulas such as 6^ order boundary compact filtering is not appropriate because of an incorrect vortex motion and resultant spurious sound fields. A higher order boundary compact filter is not necessarily suitable for computations of aerodynamic sound due to its spectral function. In the case of using lower order centered filtering formulas approach, the value of a free parameter of the filter and the grid resolution have a serious influence on the computation of aerodynamic sound. Two appropriate filters at the near-boundary are presented.
International conference proceedings, Japanese

Effects of boundary schemes on computations of acoustic waves generated by vortical flows near a wll
Yuki Wakamatsu; Hiroaki Watanabe; Yohei Inoue; Hiroshi Maekawa
Transactions of the JSME, 日本機械学会, 81, 823, 1-20, 01 Mar. 2015, Peer-reviwed
Scientific journal, Japanese

The effect of upstream disturbance on the angle of sound emission in a supersonic round jet
Daisuke Watanabe; Hiroshi Maekawa
Journal of Fluid Science and Technology, 日本機械学会, 9, 3, 1-12, 01 Oct. 2014, Peer-reviwed
Scientific journal, English

Fluid-Structure Interaction Analysis of a Soft Robotic Fish Using Piezoelectric Fiber Composite
W.Zhao; A.Ming, M; Shimojo; Y.Inoue; H.Maekawa
Journal of Robotics and Mechatronics, 日本ロボット学会, 26, 5, 638-648, 01 Oct. 2014, Peer-reviwed
Scientific journal, English

Computational study of the interaction between a shock and a near-wall vortex using a weighted compact nonlinear scheme
Zhiefen Zuo; Hiroshi Maekawa
Fluid Dynamics Research, 46, 015508, 01 Feb. 2014, Peer-reviwed
Scientific journal, English

Direct Numerical Simulation of Impinging Shock Wave/Transitional Boundary Interaction with Separation Flow
Yusuke Tokura; Hiroshi Maekawa
Journal of Fluid Science and Technology, The Japan Society of Mechanical Engineers, 6, 5, 765-779, Jul. 2011, Peer-reviwed, The interaction of a spatially transitional boundary layer flow at freestream Mach number M = 2.0 with an impinging oblique shock wave (β = 35.56) is studied by means of direct numerical simulation (DNS). High amplitude (5%) three-dimensional isotropic disturbances are superimposed on the laminar profile for a Reynolds number based on the boundary layer displacement thickness of Re_δ*0 = 1000 at the inlet plane of the computational box. Under the selected flow conditions, the interaction of the boundary layers with the incident shock wave produces three-dimensional separation, thus inducing a shock system (reflected waves and expansion fan). Linear-stability theory and DNS indicate that Λ-shaped vortices are generated in the separated shear layer due to the most unstable oblique mode, which can trigger the breakdown mechanism around the reattachment line. Energy spectral density of the wall-pressure indicates broadband spectra that are observed in the experimental result on shock/turbulent boundary layer interaction.
Scientific journal, English

Application of a High-Resolution Compact Finite Difference Method to Computational Aeroacoustics in Compressible Flows
Z.Zuo; H.Maekawa
Proceedings of ASME-JSME-KSME Fluid Engineering Conference, 1, 1, 11, Jul. 2011, Peer-reviwed
International conference proceedings, English

Spatial DNS of an Isothermal Flat Plate Supersonic Turbulent Boundary Layer with/out Impinring Shock Wave
Yusuke Tokura; Hiroshi Maekawa
Journal of Fluid Science and Technology, The Japan Society of Mechanical Engineers, 6, 1, 30-43, Jan. 2011, Peer-reviwed, Spatial direct numerical simulation results are presented for transitional/turbulent supersonic isothermal flat plate boundary layers at M = 2.0 and impinging shock wave-boundary layer interactions. The numerical results show the formation and development of three-dimensional vortical structures such as hairpin packets and streak-breakdown, and secondary and tertiary hairpins as well. These characteristic vortical structures create a significant fraction of the supersonic turbulent boundary layer structure. An incident shock wave impinging upon the transitional boundary layer with streaks and hairpins, and unsteady reflected waves from the mildly separation boundary layer are observed. Expansion waves after the impinging point and compression waves due to the boundary layer reattachment are also identified. Across the interacting shock, turbulence is enhanced with finer hairpins generated inside, and it undergoes a relaxation process to higher Reynolds turbulent boundary layers far downstream.
Scientific journal, English

DNS of a Spatially Evolving Transitional/Turbulent Boundary Layer Impinging Shock Wave
Yusuke Tokura; Hiroshi Maekawa
AIAA Aerospace Science, 2011, 729, 1-16, Jan. 2011, Peer-reviwed
International conference proceedings, English

Effects of Oblique Unstable Modes on the Development of a Turbulent Mixing Layer at High Convective Mach Numbers
Daisuke Watanabe; Kensuke Akita; Hiroshi Maekawa
AIAA Aerospace Science, 1-12, Jan. 2011, Peer-reviwed
International conference proceedings, English

DNS of a spatially evolving transitional/turbulent boundary layer at M=2.0
Y.Tokura; H.Maekawa; Y.Ogata; D.Watanabe
Proc. of Aerospace Science, vol.1, no.1, 1-17, Jan. 2010, Peer-reviwed
International conference proceedings, English

DNS of a Spatially Evolving Transitional/Turbulent Boundary Layer at M=2.0
Tokura Yousuke; Hiroshi MAEKAWA
48th Aerospace Science Meeting, 2010, 355, 2010, Peer-reviwed
International conference proceedings, English

Pressure waves generated when a train passes through a structure
H.Takami; K.Kikuchi; M.Iida; H.Maekawa
Journal of Environment and Engineering, The Japan Society of Mechanical Engineers, 3, 2, 385-396, Nov. 2008, Peer-reviwed, When a high-speed train passes through a hood-shaped short structure (the length along the railway is typically several times as long as the diameter of its cross section), such as an overpass or a snow shelter, "structure-passing waves (SPW)," which are a type of low-frequency noise, radiate from both openings of the structure toward the outside area. The SPW could create an environmental problem of a low-frequency noise along the tracks as train speeds increase, for it steeply grows in proportion to the third or fourth power of the train speed. In this study, model experiments and acoustic analyses were conducted to investigate the generation mechanism of SPW. The run-time required for the present method of analyses is a few seconds, as opposed to the several hours typically required for an entirely numerical approach. The results of the acoustic analyses, based on a method for predicting a compression wave within a hood-shaped structure generated by a passing train, generally agree well with the experimental results of SPW with some exceptions. This implies that SPW can be modeled as a superposition of the pressure waves radiating from both openings of the structure. In addition, our model experiment and acoustic analysis show that the magnitude of SPW tends to depend on train nose/tail profile.
Scientific journal, English

Low-Frequency Aerodynamic Noise from a High-Speed Train
H.Takami; K.Kikuchi; H.Maekawa; T.Kurita; Y.Wakabayashi
Theoretical and Applied Mechanics, 56, 196-205, Feb. 2008, Peer-reviwed
Scientific journal, English

Acoustic noise generation in a compressible turbulent cylindrical boundary layer
Daisuke Watanabe; Hajime Takami; Hiroshi Maekawa
Theoretical and Applied Mechanics Japan, Science Council of Japan, 56, 317-324, 2008, Spatial direct numerical simulations are performed to study the development of turbulent structures and the associated sound emission in a compressible boundary layer, in order to compare with corresponding high-speed train model experiments conducted in a moving model facility, where the free stream velocity is 500km/h (corresponding Mach number is 0.41). In the simulation, finite difference upwind-biased compact schemes (spectral-like resolution) are employed. Boundary conditions based on characteristic analysis for the Navier-Stokes equations are used so that acoustic waves are not reflected back into the domain. Disturbances of compressible isotropic turbulence are superimposed on the laminar profile at the inlet boundary layer in the computational box. The Reynolds number based on the displacement thickness at the inlet is 1640, which corresponds the measurement of the boundary layer undergoing transition. Simulation results present the complex development of the hairpin vortices leading to turbulent boundary layer structures and the associated sound generation. The numerical aerodynamic noise frequency range and the attenuation of sound are in good agreement with the experimental results.
Scientific journal, English

Study of Transition Mechanism in a Wake Behind an Airfoil with a Small Angle of Attack by Using a Towing Wind Tunnel
T.Morita; H.Maekawa
Journal of Fluid Science and Technology, The Japan Society of Mechanical Engineers, 2, 3, 679-690, Dec. 2007, Peer-reviwed, This paper describes an experimental investigation of the transitional mechanism of a wake generated behind a thin airfoil with a small angle of attack in a towing wind tunnel. A linear stability analysis shows that the wake is characterized by a region of absolute instability in the near wake (x=30mm) and one of convective instability further downstream. When the airfoil starts to run in the tunnel, boundary layers develop on the upper/lower airfoil surfaces with different thickness. Since the asymmetric wake is generated, starting vortices of a single row are observed first in the wake, which is different from the Karman vortex street. The experimental results show that time-harmonic fluctuations of the starting vortex sustain in the natural transition process due to a self sustained resonance in the absolutely unstable region behind the trailing edge. The wake profile in the saturation steady state yields the vortex street structure, where the fluctuation frequency defined as the fundamental unstable mode is found in the final saturation steady state. The growth of the fundamental unstable mode in the convectively unstable region suppresses the high frequency fluctuations associated with the starting vortex generation. On the other hand, low-frequency fluctuations in the quasi-steady state sustaining in the saturation state grow gradually during the vortex street formation, which lead to the vortex deformation downstream.
Scientific journal, English

Study of Transition to Turbulence in a Supersonic Boundary Layer Using DNS and Transition Prediction (Subjected to Bypass Transition)
Hiroshi Maekawa
Journal of Fluid Science and Technology, The Japan Society of Mechanical Engineers, 2, 3, 535-546, Dec. 2007, Peer-reviwed, The current understanding of supersonic boundary layer transition is reviewed in this paper. The material focuses on bypass transition in a plane supersonic boundary layer. Recent advances in DNS and engineering prediction of transition are discussed. It is shown that streaky structures appear in supersonic boundary layers and that the fluctuation energy growth is proportional to the downstream distance. Spatial DNS studies indicate a bypass transition scenario, breakdown mechanisms to turbulence, and turbulent boundary layer structures.
Scientific journal, English

高速列車が明かり区間を走行する際に生じる低周波音
H.Takami; K.Kikuchi; H.Maekawa
Trans, JSME, 73, 735, 1-8, Nov. 2007, Peer-reviwed
Scientific journal, Japanese

Direct numerical simulation of a spatially evolving supersonic transitional/turbulent boundary layer
H.Maekawa; D.Watanabe; K.Ozaki; H.Takami
Proc. of Turbulent Shear Flow Phenomena, 15, Aug. 2007, Peer-reviwed
International conference proceedings, English

Turbulent Hierarchic Structures and Scalar Mixing in a Supersonic Mixing Layer at High Convective Mach Numbers
H.Maekawa; D.Watanabe
Proc. of Thermal Engineering Summer Heat Transfer Conference, 212, Jul. 2007, Peer-reviwed
International conference proceedings, English

Acoustic wave generation in a compressible wake
Hiroshi Maekawa; Takashi Takiguchi; Daisuke Watanabe
JSME International Journal, Series B: Fluids and Thermal Engineering, 49, 4, 1086-1091, 21 May 2007, Peer-reviwed, The compressible Navier-Stokes equations are numerically solved to study the acoustic generation mechanism associated with the evolution of the structure in a compressible plane wake undergoing transition to turbulence. High-order compact finite difference schemes are used for spatial derivatives and a 4th-order Runge-Kutta scheme is employed for time advancement. Navier-Stokes characteristic boundary conditions are used in the vertical direction and periodic boundary conditions in the streamwise and spanwise directions. Three-dimensional structures of the wake are studied by means of temporally evolving plane wakes forced with a combination of unstable modes obtained from linear stability theory using a mapped Fourier method for the viscous compressible equations. Forcing with a pair of oblique subharmonic unstable modes yields streamwise/vertical counter-rotating vortices in the saddle region. As the streamwise/vertical vortices evolve outside, their self-induction causes inclined braidlike structures to form in the wake, which are similar to observations in the experimental supersonic flat wake transition. The oblique subharmonic unstable modes also cause the spanwise variations in the core that lead to roller distortion. Acoustic waves of plane wakes are generated when two-dimensional rollup structures appear and rotate in such wakes. Near-field sound wave pressure decreases downstream due to the three-dimensional evolution of the wake.
Scientific journal, English

TURBULENT HIERARCHIC STRUCTURE AND SCALAR MIXING IN A SUPERSONIC MIXING LAYER AT HIGH MACH NUMBERS
Hiroshi MAEKAWA; Daisuke WATANABE
ASME Annual Meeting, 1, 2, 1-16, 2007, Peer-reviwed
International conference proceedings, English

曳航風洞を用いた迎角をもつ翼後流の乱流遷移機構の研究
守田俊之; 前川 博
日本機械学会論文集B1編, 72, 724, 2924-2932, Dec. 2006, Peer-reviwed
Scientific journal, English

DNSを用いた超音速境界層における乱流遷移機構の研究と遷移予測法の展望（バイパス遷移に関連して）
前川 博
日本機械学会論文集B1編, 72, 724, 2845-2850, Dec. 2006, Peer-reviwed
Scientific journal, Japanese

コンパクトスキームの圧縮性流れの高解像度シミュレーションへの応用
滝口貴志; 渡辺大輔; 前川 博
日本機械学会論文集B1編, 72, 721, 2186-2194, Nov. 2006, Peer-reviwed
Scientific journal, Japanese

Acoustic wave generation in a compressible wake
Hiroshi Maekawa; Takashi Takiguchi; Daisuke Watanabe
JSME INTERNATIONAL JOURNAL SERIES B-FLUIDS AND THERMAL ENGINEERING, JAPAN SOC MECHANICAL ENGINEERS, 49, 4, 1086-1091, Nov. 2006, Peer-reviwed, The compressible Navier-Stokes equations are numerically solved to study the acoustic generation mechanism associated with the evolution of the structure in a compressible plane wake undergoing transition to turbulence. High-order compact finite difference schemes are used for spatial derivatives and a 4th-order Runge-Kutta scheme is employed for time advancement. Navier-Stokes characteristic boundary conditions are used in the vertical direction and periodic boundary conditions in the streamwise and spanwise directions. Three-dimensional structures of the wake are studied by means of temporally evolving plane wakes forced with a combination of unstable modes obtained from linear stability theory using a mapped Fourier method for the viscous compressible equations. Forcing with a pair of oblique subharmonic unstable modes yields streamwise/vertical counter- rotating vortices in the saddle region. As the streamwise/vertical vortices evolve outside, their self-induction causes inclined braidlike structures to form in the wake, which are similar to observations in the experimental supersonic flat wake transition. The oblique subharmonic unstable modes also cause the spanwise variations in the core that lead to roller distortion. Acoustic waves of plane wakes are generated when two-dimensional rollup structures appear and rotate in such wakes. Near-field sound wave pressure decreases downstream due to the three-dimensional evolution of the wake.
Scientific journal, English

Low-frequency noise radiated from a high-speed train running in an open section
H.Takami; K.Kikuchi; M.Iida; H.Maekawa; T.Kurita; Y.Wakabayashi
Proc. of The 13th International Congress on Sound and Vibration, CD-ROM, Jun. 2006, Peer-reviwed
International conference proceedings, English

超音速平面乱流ジェットの音響場に対する斜め不安定モードの影響
渡辺大輔; 前川 博; 松尾裕一
日本機械学会論文集B1編, 72, 724, 2924-2932, 2006, Peer-reviwed
Scientific journal, Japanese

曲がりダクト助走区間の圧縮性粘性流れ構造
尾崎幸玄; 前川 博; 渡辺大輔
ながれ, The Japan Society of Fluid Mechanics, 25, 4, 345-355, 2006, Peer-reviwed, Developing compressible viscous fluid flow in a curved duct, especially mechanism of the voritical flow field due to the curvature, is studied numerically by means of DNS. The Dean number of Dn=271 and the Mach number of M=0.7 are chosen to investigate the curvature effects on the compressible viscous flow. The secondary flow is defined as the helicity density structure, which leads to a clear relationship between the secondary flow pattern and the three-dimensional structure downstream. Higher Mach number flow yields more complicated secondary flows, a pair or two pairs of Dean vortices are generated downstream at the same Dean number. DNS results show a developing helicity density flow of the herical structure. Convection terms in the Navier-Stokes equations are visualized as vector plots, as well as the pressure gradient. This visualization leads a clear understanding of the role of viscous terms near the outer wall. Numerical unsteady motions responding to random disturbances show temporal periodic oscillation of the spanwise velocity component near the outer wall of z=0.
Scientific journal, Japanese

列車が沿線近傍構造物を通過する際に発生する圧力波
高見創; 菊地勝浩; 飯田雅宣; 前川 博
機械学会論文集B1編, The Japan Society of Mechanical Engineers, 72, 715, 612-619, 2006, Peer-reviwed, When a high-speed train enters or leaves a tunnel, impulsive pressure waves are radiated from the entrance/exit portal toward the outside of the tunnel. The waves are called a "micro-pressure wave," a "tunnel entry wave" and a "tunnel exit wave." A similar phenomenon occurs when a train passes a short structure in axial length in an open section (such as an over-bridge). We call it a "structure-passing wave." The length of the structure along the railway is several times or less the diameter of the structure cross-section. Although the structure-passing wave is weak at present, it could cause an environmental noise problem of a low-frequency (which has become public concern) as the train speed increases. This paper describes the characteristics of the structure-passing wave based on the results of model experiments and acoustic analyses. The results obtained from the acoustic analyses were in good agreement with the result of the experiment except for the very short length structures. This implies that the structure-passing wave can be modeled on a superposition of the pressure waves radiating from both sides of the structure.
Scientific journal, Japanese

Acoustic waves emanating from transitional structures in a compressible boundary-layer for High-speed Train
D.Watanabe; H.Takami; H.Maekawa; K.Kikuchi; M.Iida; H.Suzuki
The 13th International Congress on Sound and Vibration, CD-ROM, 2006, Peer-reviwed
International conference proceedings, English

Acoustic wave radiation due to coherent vortex motions in a supersonic wake
T.Takiguchi; D.Watanabe; H.Maekawa
Proc. of 12th CFD Symposium, 1, 1, 12-16, Dec. 2005
International conference proceedings, English

Supersonic plane jet at high convective Mach number, International Congress of Jets
D.Watanabe; H.Maekawa; Y.Matsuo
International Congress of Jets, Wakes and Separated Flows, 2, 1, 110-118, Oct. 2005, Peer-reviwed
International conference proceedings, English

微小板対を用いた渦運動操作による噴流制御に関する研究
近藤大海; 前川 博
日本機械学会論文集B1編, 71, 702, 442-449, 2005, Peer-reviwed
Scientific journal, Japanese

曳航風洞を用いた翼後流の層流乱流遷移に関する研究
麻生力; 前川 博; 西村英樹; 渡辺大輔
日本機械学会論文集, 70, 700, 3106-3113, Dec. 2004
Scientific journal, Japanese

Mach wave emission in a plane supersonic jet at high convective Mach numbers
D.Watanabe; H.Maekawa
Proc. of 24th ICAS Congress, CD-Rom, Aug. 2004, Peer-reviwed
International conference proceedings, English

Curvature effects in the curved duct for the compressible viscous flow
K.Ozaki; H.Maekawa
Proc. of 24th ICAS Congress,, CD-ROM, Aug. 2004, Peer-reviwed
International conference proceedings, English

Three-dimensional evolution of structure and acoustic wave generation in a compressible plane wake
D Watanabe; H Maekawa
FLUID DYNAMICS RESEARCH, ELSEVIER SCIENCE BV, 34, 3, 145-165, Mar. 2004, Peer-reviwed, The compressible Navier-Stokes equations are numerically solved to study three-dimensional structures of a compressible plane wake undergoing transition to turbulence. High-order compact finite difference schemes are used for spatial derivatives and a fourth-order Runge-Kutta scheme is employed for time advancement. Navier-Stokes characteristic boundary conditions are used in the vertical direction and periodic boundary conditions in the streamwise and spanwise directions. Unstable disturbances are obtained from linear stability theory using a mapped Fourier method for the viscous compressible equations. Three-dimensional structures of the wake are studied by means of temporally evolving plane wakes forced with random disturbances and a combination of unstable modes. Forcing with a pair of oblique unstable modes yields streamwise/vertical counter-rotating vortices in the saddle region. As the streamwise/vertical vortices evolve outside, their self-induction causes inclined braidlike structures to form in the wake. The effect of the oblique unstable modes is also to cause the spanwise roller breakdown. Acoustic waves of the plane wake are generated when roughly two-dimensional rollup structures appear and rotate in the wake. The three-dimensional evolution of the wake reduces the near-field sound pressure. (C) 2003 Published by The Japan Society of Fluid Mechanics and Elsevier B.V. All rights reserved.
Scientific journal, English

TS波と斜行波によって励起された圧縮性境界層の遷移機構に関する研究
前川 博; 渡辺大輔; 尾崎幸玄
ながれ, The Japan Society of Fluid Mechanics, 24, 5, 543-551, 2004, Peer-reviwed, Spatial direct numerical simulations are performed to study the formation and development of three-dimensional structures in a compressible flat plate boundary layer, where the freestream Mach number is 0.5 and the Reynolds number at the inlet based on the displacement thickness 1000. A pair of neutral/stable oblique modes and a TS wave are superimposed on the laminar profile at the inlet plane of the boundary layer computational box. The magnitudes of the TS and oblique waves are chosen to be 1% of the freestream velocity, respectively. After saturation of the T-S wave, the growth of the oblique modes produces peak-valley splitting downstream and hairpin vortices (hairpin packets) on the low speed streak are observed further downstream. The oblique subharmonic mode leads to sooner transition to turbulence downstream in the boundary layer. Numerical results show the evolution of hairpin vortices into a large-scale structure, in which fine-scale vortical structures with low-/high-speed streaks develop near the wall.
Scientific journal, Japanese

DNS of supersonic transitional and turbulent flows
H.Maekawa; D.Watanabe; K.Yamashita
Proc. of International Workshops on Advances in Computational Mechanics, 1, 2, 12-13, 2004, Peer-reviwed
International conference proceedings, English

Curvature effects in the curved duct for the compressible viscous flow with heat transfer
K.Ozaki; H.Maekawa
Proc. of FEDSM’03, ASME-JSME Joint Fluid Engineering Conference, FEDSM2003-45634, Jul. 2003, Peer-reviwed
International conference proceedings, English

Study of vortex dislocations in the wake of a flat plate with finite thickness
Hiroshi Maekawa; So Abe
JSME International Journal, Series B: Fluids and Thermal Engineering, 45, 4, 843-849, Nov. 2002, Peer-reviwed, Wake structures of a flat plate with finite thickness are studied using the rake of X-wires techniques. Parallel and oblique shedding modes in the wake flow are investigated. These modes depend on the flat plate end conditions. In the present paper, we demonstrate that manipulation of the end conditions yields vortex dislocations that appear at the same location. By manipulating the end conditions, vortex chain structures branching inside the dislocations are analyzed by means of pseudoflow visualization of the X-wire rake data. The appearance of branching vortex chains is due to misfit between two oblique vortex shedding cells. Power spectra of velocity fluctuations show growth of the low-frequency mode due to subtraction of the two fundamental shedding modes of different frequency across the span. The small difference between the two fundamental shedding modes explains the large intermittent velocity irregularities in the large-scale structure downstream that occur in natural transition.
Scientific journal, English

Actuator with a pair of Wings for Manipulation of Hairpin Vortices
Y. Kamikuchi; H. Maekawa
Proc. of Fifth JSME-KSME Fluids Engineering Conference, CD-ROM, Nov. 2002
International conference proceedings, English

Simulations of Bypass Transition for Spatially Evolving Disturbances in Compressible Wall-Bounded Flows
Al Moez Yahyaoui; Hiroshi Maekawa
Computational Fluid Dynamics Journal, 11, 2, 195-207, Jun. 2002, Peer-reviwed
English

Transition of Supersonic Plane Jet due to Symmetric/Antisymmetric Unstable Modes
Watanabe, D; Maekawa, H
Journal of Turbulence, 11, 3, 1-16, Dec. 2001, Peer-reviwed
Scientific journal, English

Simulations of Bypass Transition for Spatially Evolving Disturbances in Compressible Wall-Bounded Flows
Maekawa,H; Yayhaoui Al M
Proc. Japan-Russia International CFD Workshop on Turbulence, Instabilities and Parallel Computing. Osaka, Oct. 2001, Peer-reviwed
International conference proceedings, English

超音速後流の音波放出
渡邊大輔; 前川 博
日本流体力学会年会2001講演論文集, Jul. 2001
Japanese

圧縮性乱流におけるSGSモデルぼア・プリオリテスト
竹原 洋三; 渡邊大輔; 前川 博
日本流体力学会年会2001講演論文集, Jul. 2001
Japanese

Transition of Supersonic Plane Jet due to Symmetric/Antisymmetric Unstabel Modes
Watanabe,D; Maekawa,H
Proc. of Turbulent Shear Flow Phenomena, 2, Jun. 2001, Peer-reviwed
International conference proceedings, English

Direct Numerical Simulations of Hypersonic Boundary Layer Receptivity Using Compact Convex Combined Schemes
Yamashita K; Maekawa,H
AIAA, 2002-1798, Apr. 2001, Peer-reviwed
International conference proceedings, English

Convex Combined Compact Schemes for Turbulence Simulations with Discontinuities
H. Maekawa; K. Yamashita; X. Deng
Proc. of 16th Numerical Simulation of Turbulence Symposium, Mar. 2001, Peer-reviwed
International conference proceedings, English

圧縮性乱流局所解の分類と統計
鈴木智明; 前川 博; 渡辺大輔
日本機械学会，関東支部講演会講演論文集, Mar. 2001
Japanese

マイクロ波励起によるガスレーザーの数値電磁流体力学的基礎研究
竹本広文; 前川 博
日本機械学会，関東支部講演会講演論文集, Mar. 2001
Japanese

Direct numerical simulations of subsonic plane Poiseuille flows undergoing transition
AM Yahyaoui; H Maekawa; K Yamamoto
JSME INTERNATIONAL JOURNAL SERIES B-FLUIDS AND THERMAL ENGINEERING, JAPAN SOC MECHANICAL ENGINEERS, 44, 1, 72-80, Feb. 2001, Compressible Navier-Stokes equations are numerically solved to study spatially developing plane Poiseuille flows undergoing transition to turbulence. Navier-Stokes Characteristic Boundary Conditions and Compact Finite Difference Scheme are used in the streamwise (x) and the vertical (y) directions, however a classical Fourier method is employed in the periodic (z) direction. Several subsonic simulations, with isothermal walls, for different Mach numbers and forced with different random-disturbances are carried out to study the effects of compressibility and disturbances on the transition mechanism. Some of the simulations in their early transitional state, (i.e. DNS of Re = 2 500 and M = 0.5 plane Poiseuille flow perturbed at the inlet with 5% of the streamwise velocity amplitude) show the appearance of omega (y) vorticity component in the vicinity of the walls. This near wall vertical vorticity along with the generated streaks, located between the counter rotating vortices, evolve downstream with a longitudinal elongation.
Scientific journal, English

High Level Noise-Induced Bypass Transition in Compressible Plane Poisueille Flow
Yahyaoui Al M; Maekawa, H
JSME International Journal, 44, 1, 72-80, Feb. 2001, Peer-reviwed
Scientific journal, English

Study of the Geometry of Flow Patterns in a Geometry and Statistics of Turbulence
Hiroshi MAEKAWA
FLUID MECHANICS AND ITS APPLICATIONS, 59, 223-228, Jan. 2001, Peer-reviwed
English

圧縮性自由せん断流の構造
渡辺大輔; 鈴木智明; 前川 博
数理解析研究所「乱流構造の数理」, Jan. 2001
Japanese

Near wall structures in wall bounded flows（case of Compressible Plane Poiseuille Flow）
M. Yahyaoui; H. Maekawa
数理解析研究所「乱流構造の数理」, Jan. 2001
English

Simulations of Bypass Transition for Spatially Evolving Disturbances in Compressible Wall-Bonded Flows
Maekawa,H; Yahyaoui,M.A
CFD Jornal(特集号:数値流体力学会）, 201, 120-128, 2001, Peer-reviwed
Scientific journal, English

非線型コンパクトスキームの改良と圧縮性DNS への応用
山下建志; 前川
第14回数値流体力学シンポジウム講演論文集, E09-4, Dec. 2000
Japanese

水素空気噴流火炎の直接数値シュミレーション
相澤寛朗; 前川 博
第14回数値流体力学シンポジウム講演論文集, A04-3, Dec. 2000
Japanese

曲がり管における縦渦構造の不安定性
渡辺大輔; 小泉博義; 前川 博
第14回数値流体力学シンポジウム講演論文集, B03-2, 1, 1, Dec. 2000
Research society, Japanese

非線型コンパクトスキームの改良と圧縮性DNS への応用
山下建志; 前川 博
第14回数値流体力学シンポジウム講演論文集，E09-4, Dec. 2000
Japanese

Applications of fifth-order weighted compact nonlinear schemes to Euler and Navier-Stokes equations
X. Deng; H. Maekawa
Proc. of 4th Asian CFD Conference, Sep. 2000, Peer-reviwed
International conference proceedings, English

Structures in a Supersonic Plane Jet due to Symmetric/Antisymmetric Unstable Modes at High Mach Numbers
D. Watanabe; H. Maekawa
Proc. of International Workshop on Prediction of Laminar-Turbulent Transition in Boundary Layers, Sep. 2000, Peer-reviwed
International conference proceedings, English

空間開発DNSによる超音速境界層（M=4.5）に受容されたsecond mode 不安定波の解析
山下建志; 前川 博
流体工学部門講演会（OS圧縮性流れの基礎と応用）, Sep. 2000
Japanese

Direct Numerical Simulation of By-pass Transition in Compressible Plane Poiseuille Flows
M. Yahyaoui; H. Maekawa
流体工学部門講演会（OS圧縮性流れの基礎と応用）, Sep. 2000
English

微小翼を用い噴流中の渦運動の制御
砂岡明子; 前川 博
日本機械学会年次大会講演論文集（OS噴流・はく離流れの特性とその制御）, Aug. 2000
Japanese

不変量空間における圧縮性乱流の統計数理
前川 博; 鈴木智明; 渡辺大輔
日本流体力学年会2000，講演論文集，（OS圧縮性乱流）, Jul. 2000
Japanese

DNSによる超音速ジェットの乱流遷移に関する研究
渡辺大輔; 前川 博
日本流体力学年会2000，講演論文集, Jul. 2000
Japanese

Effects of Compressiblity and disturbances on the Tranision in Poiseuille Flows
Moez YAHAOUI; Hiroshi MAEKAWA; Kiyoshi YAMAMOTO
Proc. of 8th European Turbulence Conference, Jun. 2000, Peer-reviwed
International conference proceedings, English

乱流制御に向けた微小翼アクチュエータの開発
前川 博; 上口洋一; 砂岡明子
第44回ターボ機械総会講演会講演論文集, May 2000
Japanese

DNS of Subsomc Plane Porsenille Flows Undergoing Transition
Moez YAHAOUI; Hiroshi MAEKAWA; Kiyoshi YAMAMOTO
Proc.of International Synposium on Turbulence, Heat and Mass Transfer, Apr. 2000
English

渦転移と乱流遷移
前川 博; 阿部 想
第49回理論応用力学講演会講演論文集, 127-128, Jan. 2000
Japanese

Study of vortex dislocations in the wake of a flat plate with finite thickness
So Abe; Hiroshi Maekawa
Nihon Kikai Gakkai Ronbunshu, B Hen/Transactions of the Japan Society of Mechanical Engineers, Part B, Japan Society of Mechanical Engineers, 66, 649, 2343-2349, 2000, Peer-reviwed, Wake structures of a flat plate with finite thickness are studied using the rake of X-wires techniques. Parallel and oblique shedding modes in the wake flow are investigated. These modes depend on the flat plate end conditions. In the present paper, we demonstrate that manipulation of the end conditions yields a vortex dislocation that appears periodically at the same location. Vortex linkup dynamics phenomena in the dislocations are observed with smoke-wire flow visualization. Flow patterns of dislocation are analyzed by mean of the pseudo-flow visualization of the rake data. The linkup structure due to a misfit of two oblique shedding vortices appears periodically in the flow patterns. Evolutions of the power spectra of velocity fluctuations explain the generation of large-scale turbulent structure downstream due to the growth of a low-frequency mode and the cascade process of low/high frequency components.
Scientific journal, Japanese

Study of the geometry of flow patterns in compressible isotropic turbulence
H Maekawa; T Hiyama; Y Matsuo
JSME INTERNATIONAL JOURNAL SERIES B-FLUIDS AND THERMAL ENGINEERING, JAPAN SOC MECHANICAL ENGINEERS, 42, 3, 336-343, Aug. 1999, The geometry of flow patterns in numerically simulated compressible isotropic turbulent flows for high r.m.s. Mach numbers was studied using three-dimensional critical point theory. The solution trajectories for three first-order linear differential equations are used to classify the elementary three-dimensional flow patterns defined by instantaneous streamlines. Fluid motions characterized by high rates of kinetic energy dissipation and/or high enstrophy are of particular interest. It is found that motions corresponding to high rates of dissipation are characterized by a 3-D rate-of-strain topology which is of the saddle-saddle-unstable node type, similar to the compressible mixing layer. Fluid motions corresponding to a high rate of dilatation dissipation are characterized by a topology of the node-node-node type in particular. The influences of Mach number on the geometry of flow patterns are described.
Scientific journal, English

正方形断面曲がり管におけるDean渦の不安定性
渡辺大輔; 小泉博義; 前川 博
日本流体力学会年会99，講演論文集, 295-296, Jul. 1999
Japanese

DNS of Compressible Plane Poiseuille Flows undergoing Transition
Proc.of ASME Flnid Engineening Conference FEDSM99, 1999
English

圧縮性平面Poiseuille流れの乱流遷移のDNS
前川 博; 尾添靖通; 山本稀義
境界層遷移の解明と制御研究会講演論文集，（航空宇宙技術研究所SP-40）, 59-62, 1999
Japanese

翼端間隙をもつ３次元翼列性能に及ぼす圧縮性の影響
前川 博; 浜田紀昭
第43回ターボ機械総会講演会講演論文集, 12-17, 1999
International conference proceedings, Japanese

Hot-Wier Rakeを用いた平板後流における渦転移構造の研究
前川 博; 阿部 想
日本機械学会年次大会99講演論文集, 1999
Japanese

微小翼を用いた渦運動の操作
砂岡朋子; 前川 博
日本機械学会年次大会99講演論文集, 1999
Japanese

DNS of a Subsonic Plane Poiseuille Flows Undergoing Transition
M. Yahyaoui; H. Maekawa; K. Yamamoto
日本流体力学会年会99，講演論文集, 277-278, 1999
English

非線型コンパクト差分スキームによるCFDの信頼性評価
山下健志; 前川 博
日本機械学会計算力学部門講演会論文集, 9-5, 671-672, 1999
Japanese

曳航風洞を用いた後流の乱流遷移の研究
前川 博; 西村秀樹
境界層遷移の解明と制御研究会講演論文集，（航空宇宙技術研究所SP-43）, 83-86, 1999
Japanese

非線型コンパクト差分スキームを用いた圧縮性境界層のDNS
山下健志; X. Deng; 前川 博
第13回数値流体力学シンポジウム講演論文集, F07-3, 1999
Japanese

Simulation of Compressle Plane Poiseuille Flows Undergoing Transition
M. Yahyaoui; H. Maekawa; K. Yamamoto
第13回数値流体力学シンポジウム講演論文集, F03-2, 1999
English

Study of the Geometry of Flow Patternsin Compressible Turbulence
Hiroshi Maekawa; Yuichi Matsuo
Proc. of 13th U. S. National Congress of Applied Machanics, Jun. 1998
English

The Interaction of a Shock with a Compressible Vortex.
前川 博; 渡辺大輔
Trans of JSME, 64, 625, 2836-2843, 1998
Scientific journal, English

圧縮性乱流の位相幾何学的構造
前川 博
日本流体力学会「ながれ」, The Japan Society of Fluid Mechanics, 17, 6, 411-416, 1998, Peer-reviwed
Scientific journal, Japanese

DNSによる超音速後流の遷移構造の研究
前川 博; 渡辺大輔
日本流体力学会年会98講演論文集, 149-150, 1998
Japanese

曳航風洞を用いた後流の乱流遷移実験
西村英樹; 前川 博
日本流体力学会年会98講演論文集, 151-152, 1998
Japanese

走行台車を用いた後流構造の計測
西村英樹; 前川 博
日本機械学会流体工学部門講演論文集, 98-15, 259-260, 1998
Japanese

Simulation of Compressible Plane Posiuille Flows Undergong Transition
Moez Yahyaoui; Hiroshi Maekawa; Kiyoshi Yamamoto
第12回数値流体力学シンポジウム講演論文集, 429-430, 1998
English

火炎面と圧縮性粘性渦の非線形相互作用
富田晋平; 前川 博
第12回数値流体力学シンポジウム講演論文集, 63-64, 1998
Japanese

渦列と衝撃波の干渉
渡辺大輔; 前川 博
第12回数値流体力学シンポジウム講演論文集, 43-44, 1998
Japanese

Hot-wire Rakeを用いた有限厚さ平板後流の構造に関する研究
阿部 想; 前川 博
日本機械学会総会講演会論文集, 98-1, 323-324, 1998
Japanese

Compact high-order accurate nonlinear schemes
XG Deng; H Maekawa
JOURNAL OF COMPUTATIONAL PHYSICS, ACADEMIC PRESS INC JNL-COMP SUBSCRIPTIONS, 130, 1, 77-91, Jan. 1997, Peer-reviwed, We develop here compact high-order accurate nonlinear schemes for discontinuities capturing. Such schemes achieve high-order spatial accuracy by the cell-centered compact schemes. Compact adaptive interpolations of variables at cell edges are designed which automatically ''jump'' to local ones as discontinuities being encountered. This is the key to make the overall compact schemes capture discontinuities in a nonoscillatory manner. The analysis shows that the basic principle to design a compact interpolation of variables at the cell edges is to prevent it from crossing the discontinuous data, such that the accuracy analysis based on Taylor series expanding is valid over all grid points. A high-order Runge-Kutta method is employed for the time integration. The conservative property, as well as the boundary schemes, is discussed. We also extend the schemes to a system of conservation laws. The extensions to multidimensional problems are straightforward. Some typical one-dimensional numerical examples, including the shock tube problem, strong shock waves with complex wave interactions, and ''shock/turbulence'' interaction, are presented. (C) 1997 Academic Press
Scientific journal, English

Study of the Geometry of Flow Patterns in Compressible Isotropic Turbulence
H.Maekawa; T.Hiyama; Y.Matsuo
Transactions of the Japan Society of Mechanical Engineers, 63, 605, 167, 1997, Peer-reviwed
Scientific journal, English

Experimental Investigation of Turbulent Structures in a Two-Dimensional Momentumless Wake
H.Maekawa; S.Abe
Transactions of the Japan Society of Mechanical Engineers, 63, 608, 1145, 1997, Peer-reviwed
Scientific journal, English

POD and Wavelet Analysis of Coherent Structures in a Turbulant Mixing Layer
H.Takahasi; S.Takami; H.Maekawa
Trans. of JSME, 63, 10, 2001, 1997, Peer-reviwed
Scientific journal, English

Study of the Intermittent Structures in a 2-D Turbulent Momentumless Wake
S.Takami; H.Maekawa
Trans. of JSME, 63, 616, 3843, 1997, Peer-reviwed
Scientific journal, English

圧縮性混合層の位相幾何学(トポロジー)的構造
前川博
日本機械学会論文集 B編, 61, 586, 1995
Scientific journal, Japanese

高響加振を受けた混合層に関する研究(第2報,渦の合体に伴う三次元攪乱の発達過程)
日本機械学会論文集 B編, 61, 586, 1995
Japanese

高レイノルズ数乱流混合層の大規模構造
日本機械学会論文集,B編, 61, 588, 1995
Japanese

A STUDY OF THE GEOMETRY OF FLOW PATTERNS IN COMPRESSIBLE ISOTROPIC TURBULENCE
H.Maekawa
Proc. of 10th Symposium on Turbulent Shear Flows, 3, 13-18, 1995, Peer-reviwed
Scientific journal, English

Control of Structues and Time-Averaged Flow Properties of a Plane Wabe by Subharmonic Insenbility Modes
JSME International Journal, B, 37,4, 1994
English

Coherent Structures of a Supersonic Mixing Layer by Direct Numerical Simulations
H.Maekawa
Trans, JSME, The Japan Society of Mechanical Engineers, 60, 60, 574-2057, 1994, Peer-reviwed, In the present paper, coherent structures of the supersonic mixing layer are investigated by direct numerical simulations of a spatialy developing free shear layer, We examined numerical results of the velocity components, u, v, w simulated by Fouillet and Lesieur : Reynolds number Re=δ_ω0ΔU/ν=1500, Mach number =1(M₁=1 and M_c=0.3), (U₁+U₂)/2=0.7, U₁-U₂=0.6, and the hyperbolic-tangent velocity profile is perturbed by weak three-dimensional white noise. We find that the coherent structures in the supersonic mixing layer at M_c=0.3 are three dimensional and have rib structures with strong vorticities of ω_y and ω_x similar to those in the incompressible mixing layer. The helical pairing structures found in the rib structure generate a coherent 'upwash' and 'downwash' fluid motion in the supersonic mixing layer. The regions corresponding to high rates of dissipation are found in the rib structures.
Scientific journal, Japanese

Instability and Compressitible Turbulence
日本機械学会分科会RC104報告書(分担), 1994
English

音響加振を受けた混合層に関する研究(第1報.混合層の乱流統計量に及ぼす音響加振の影響)
前川博; 馬場信行
Trans. of JSME, 60, 579, 1994, Peer-reviwed
Scientific journal, Japanese

空間発達する混合層の成長に及ぼす圧縮性の影響
前川博; 米沢久範
Trans. of JSME, 60, 579, 1994, Peer-reviwed
Scientific journal, Japanese

Stuart解を使った非圧縮性ナビエ・ストークス方程式の高精度計算スキームの開発
平田昭彦; 前川博
Trans. of JSME, The Japan Society of Mechanical Engineers, 60, 576, 2997-3001, 1994, Peer-reviwed, A numerical scheme has been developed for solving tho two-dimensional incompressible Navier -Stokes equations on a domain that is infinite in the vertical (y) direction and finite in the streamwise (x) direction. The fourth-order equation for the streamwise velocity (u) is advanced in time explicitly using a compact third-order Runge-Kutta scheme. A standard Fourier method is used in the x direction and a mapped spectral method in the y direction. The various parts of the code are tested by solving two problems with analytical or independently-established known solutions. The nonlinear Stuart solution is employed to test the convective parts, the Poisson part of the code and the time advancement. Finally, we find that the disturbance obtained from linear stability theory grows in the linear regime of a free shear flow and that the nonlinear growth of the amplitude corresponds to the vortex roll-up.
Scientific journal, Japanese

Instability Modes of the Compressible Mixing Layer
前川 博; 荒川 忠一; 藤原 仁志
Trans, JSME, The Japan Society of Mechanical Engineers, 59, 566, 2997-3002, 1993, Peer-reviwed, The effect of compressibility on the growth of instability modes in a plane free shear flow was studied in this work. The linear disturbance equations of compressible plane free shear layers are solved using a direct spectral method. The mapped spectral method (mapped Fourier method) for the free shear flow of the unbounded boundary conditions was employed. The eigenfunctions satisfy the homogeneous Dirichlet boundary conditions at infinity. Numerical results reveal that oblique modes (3-D modes) are significant in the mixing layer as the convective Mach number M_c increases. Above M_c=0.6, the most unstable mode and also its two subharmonic modes are oblique waves. The fundamental and subharmonic eigenfunctions at M_c=0.8 are presented in this paper. The eigenfunctions structures are affected by the convective Mach number.
Scientific journal, Japanese

Three-Dimensional Evolution of a Plane Wake
H. Maekawa; R. D. Moser; N. N. Mansour
Proc. of Turbulent Slear Flows, 9, 3-2-1-3-2-6, 1993, Peer-reviwed
Scientific journal, English

Three-Dimensional Evolution of a Plane Wake
H.Maekawa; N.N.Mansou; J.C.Buel
Annual Research Briefs (NASA Stamford Univ. ), 325-334, 1993
Research institution, English

Study on the Topology of Compressitible Turbulence
Proc, of CFD Symposium, 7, 347-350, 1993
English

Instability mode interactions in a spatially developing plane Wake
H.Maekawa; N.N.Mansour; J.C.Buel
Journal of Fluid Mechanics, 235, 1992, Peer-reviwed
Scientific journal, English

Direct Numerical Simulations of a Spatially Developing Plane Wake
JSME Internatinal Journal, B, 35,4, 1992
English

渦輪による混合層の発達構造の制御
前川 博; 西岡 卓宏
日本機械学会論文集(B編), The Japan Society of Mechanical Engineers, 58, 553, 553-2666, 1992, Peer-reviwed, In the present paper, the evolution process of the mixing layer manipulated by a vortex ring was studied using a novel experimental technique. Mixing layers were generated downstream from a splitter plate towed in a straight long channel. The vortex ring was made to collided with the mixing layer large-scale structures in the transitional region. The interactions between the mixing layer and the vortex ring were investigated by means of the flow visualization and the flying hot-wire technique associated with the collision. The topology of the vortices effective for pairings of the mixing layer is presented in this paper. The experimental results reveal that the vortex ring deforms the mixing layer vortices and causes the deformed vortices to merge sooner than they do in the case forced by the subharmonic instability modes.
Scientific journal, Japanese

翼端隙間を有するタービン翼列の三次元性能予測法
前川博
ターボ機械, 20, 12, 1992, Peer-reviwed
Scientific journal, Japanese

混合層における時間成長と空間成長不安定モード
前川 博; 長友 健一郎
日本機械学会論文集(B編), 57, 542, 1991, Peer-reviwed
Scientific journal, Japanese

伴流空間発展間題の直接シミユレ-ション
日本機械学会論文学(B編), 57, 540, 1991
Japanese

水平軸風車における揚力面理論と数値解析
前川博
日本機械学会論文集B編, The Japan Society of Mechanical Engineers, 52, 480, 480-2989, 1988, The purpose of this investigation is to develop the lifting surface theory of horizontal-axis wind turbines and devise the numerical method to solve the theory. The velocity potential is derived by the vortex theory. The integral equation that relates an upwash distribution to an unknown lift distribution is the same as that of a screw propeller. With the boundary condition pertinent to a wind turbine, the integral equation is solved by the method of Hanaoka. Furthermore, the pressure distributions of two kinds of rotor are measured. One is designed by means of the design method based on the lifting line theory, the other has rectangular blades of expanded shape with a constant geometric pitch. The pressure distributions on the blades of various working conditions are calculated using the concept of equivalent two-dimensional wing, and compared with the experimental ones. It is concluded that the presented lifting surface theory and the numerical method are applicable to wind turbines.
Scientific journal, Japanese

Optimum Design Method of Horizontal-Axis Wind Turbine Blades based on Liffing-Line theory
H.Maekawa
Bulletin of the Japan Soc. Mech. Engrs., 29, 256, 1986
Scientific journal, English

Study on the Performance of Two-dimensional Hydrofoils in Dylute Polymer Solutions
H.Maekawa
Bulletin of the Japan Society of Mechanical Engineers, 27, 224, 1984
Scientific journal, English

Application of the Vortex theory to High-Speed Horizontal-Axts Wind Turbine
H.Maekawa
Bulletin of the Japan Soc, Mech Engrs., 27, 229, 1984
Scientific journal, English

乱流工学ハンドブック
乱流工学ハンドブック編集委員会
Dictionary or encycropedia, Japanese, 朝倉書店, 2009

物理学辞典（三訂版）
物理学辞典編集委員会
Japanese, Joint work, 混合層、再層流化、旋回流, 培風館, Apr. 2006

機械工学便覧 基礎編α４「流体工学」
日本機械学会
Dictionary or encycropedia, Japanese, 日本機械学会, 2006

例題でわかる基礎・演習
前川 博; 山本 誠; 石川 仁
Japanese, Editor, 共立出版, Sep. 2005

対話とシミュレーションムービーで学ぶ流体力学
前川博
Japanese, Editor, 共立出版, Sep. 2002

物理学辞典（３訂版）：混合層，再層流化，旋回流，渦崩壊
前川 博
Japanese, Joint work, 培風館（物理学辞典編集委員会編）分担執筆, 2000

機械工学便覧、日本機械学会編、 分担執筆（流体実験計測法） 流体力学
前川 博
Japanese, Joint work, 日本機械学会, 2000

流体力学ハンドブック(第2版)
流体力学ハンドブック編集委員会
Japanese, Joint work, 乱流伴流, 丸善, 1998

Vortex Dynamics of a Vortex Ring introduced in a Laminer Boundary
Rhyoji Kobayashi
English, Joint work, Laminar-Turbulent Transition(Springer-Verlag), 1995

GROWTH OF RANDOMNESS IN A SPAIIPLLY DEVELOPING WAKE
Kambe Tsutomu
English, Joint work, NUMERICAL METHOD IN FLUID DYNAMICS, 1989

A study of subcritical and supercritical transitional structures of a boundary layer tripped by finite height obstacles periodically arrayed in span
高橋彩恵; 神保郁充; 井上洋平; 前川博
Oral presentation, Japanese, 日本流体力学会年会, Domestic conference
25 Sep. 2015

重み付非線形コンパクトスキームとSLAU2による高解像度計算
佐藤翔平; Zhiheng ZUO; 井上洋平; 前川博
Oral presentation, Japanese, 第2７回数値流体力学シンポジウム, Domestic conference
18 Dec. 2013

壁面近傍における可動平板翼と渦流れとの相互作用
井上洋平; 藤田翔; 前川博
Oral presentation, Japanese, 第2７回数値流体力学シンポジウム, 日本流体力学会, 名古屋大学, Domestic conference
17 Dec. 2013

超音速境界層における主流乱れの遷移構造に及ぼす影響
渡辺大輔; 前川博
Oral presentation, Japanese, 第2７回数値流体力学シンポジウム, 日本流体力学会, 名古屋大学, Domestic conference
17 Dec. 2013

TheEffect of Upstream Disturbance on The Angle of Sound Emission in a Supersonic Round Jet
Daisuke Watanabe; Hiroshi Maekawa
Oral presentation, Japanese, Proceedings of 4th ICJWSF2013, Invited, 4th ICJWSF2013 Conference Committee, International conference
22 Sep. 2013

乱流境界層からの放射音に及ぼす粗さの影響
芦澤一眞; 前川博; 井上洋平; 高見創
Oral presentation, Japanese, 日本流体力学会年会2013, Domestic conference
11 Sep. 2013

超音速境界層の遷移における流入撹乱スペクトルの影響
渡辺大輔; 前川博
Oral presentation, Japanese, 日本流体力学会年会2013, 日本流体力学会, 東京農工大, Domestic conference
11 Sep. 2013

Computational Aeroacoustics of the Near-Wall Vortex-Shock Interactions Using WCNS
Zhiheng ZUO; H.Maekawa
Oral presentation, English, Proceedings of 52th International Workshop on Investigation and Control to Turbulence, Committee of 52th International Workshop on Investigation and Control to Turbulence, UEC, Domestic conference
28 Mar. 2013

Computational Aeroacoustics of the Near Wall Vortex-Shock Interactions using WCNS
Zhifeng ZOU; Hiroshi Maekawa
Public symposium, English, International Workshop In UEC, UEC, Tokyo
Mar. 2013

重み付き非線形コンパクトスキームを用いた衝撃波と壁近傍渦の干渉の数値シミュレーション
Zhiheng ZUO; H.Maekawa
Public symposium, Japanese, 第26回数値流体力学シンポジウム, Domestic conference
16 Sep. 2012

円筒境界層における低周波圧力変動に及ぼす流入撹乱の影響
渡辺大輔; 前川博
Oral presentation, Japanese, 日本流体力学会年会2010講演集,日本流体力学会年次大会
Sep. 2010

圧縮性境界層の遷移構造から発生する音波の研究
渡辺大輔; 前川博
Oral presentation, Japanese, 日本機械学会2010年次大会講演集,日本機械学会年次大会
Sep. 2010

空間発展DNSによる超音速乱流境界層のストリーク構造について
戸倉裕介; 前川博
Oral presentation, Japanese, 日本流体力学会2010年次大会講演集,日本流体力学会
Sep. 2010

超音速境界層におけるTransient－Growthモードによる遷移について
戸倉裕介; 前川博
Oral presentation, Japanese, 日本機械学会年次大会講演集,日本機械学会２０１０年次大会
Sep. 2010

DNS Study of Supersonic Turbulent Flows
Hiroshi Maekawa; Yusuke Tokura
Invited oral presentation, English, IWACOM II, IWACOM, Yokohama, International conference
Mar. 2010

Acoustic Fields emanating from the pair vortices with a near wall secondary vortex induced by the primary vortices on the wall
KazuyaHironaka; HiroshiMaekawa; SoTakami; TomohiroDeagawa
Oral presentation, Japanese, Yamanashi District Conference
Oct. 2009

超音速乱流遷移境界層の空間構造発展の研究
戸倉 裕介; 前川 博; 渡辺 大輔; 尾形 陽一
Oral presentation, Japanese, 第58回理論応用力学講演会,第58回理論応用力学講演会
Jun. 2009

高速列車から生じる低周波数の空力音
高見創; 菊地勝浩; 前川博; 栗田健; 若林雄介
Oral presentation, Japanese, 日本機械学会流体工学部門講演会講演概要集,日本機械学会流体工学部門講演会
2007

円筒境界層における低周波音発生機構
渡辺大輔; 前川博; 高見創; 尾崎幸玄
Oral presentation, Japanese, 日本流体力学会年会2007講演論文集,日本流体力学会年会2007
2007

圧縮性乱流遷移境界層からの音波発生について
前川博; 渡辺大輔; 高見創
Oral presentation, Japanese, 第5６回理論応用力学講演会講演論文集,第5６回理論応用力学講演会
2007

高速列車から生じる空力的な要因による低周波音
高見創; 菊地勝浩; 前川博; 栗田健; 若林雄介
Oral presentation, Japanese, 第5６回理論応用力学講演会講演論文集,第5６回理論応用力学講演会
2007

DNSによる圧縮性円筒境界層における乱流遷移機構の研究
渡辺大輔; 前川博; 高見創; 尾崎幸玄
Oral presentation, Japanese, 日本流体力学会年会2006講演論文集,日本流体力学会年会2006
2006

高速列車が明かり区間を通過する際に発生する低周波音
高見創; 菊地勝浩; 飯田雅宣; 前川博; 栗田健; 若林雄介
Oral presentation, Japanese, 日本機械学会第１6回環境工学総合シンポジウム講演論文集,日本機械学会第１6回環境工学総合シンポジウム
2006

圧縮性境界層の遷移に伴う音波発生機構の研究、
滝口貴; 渡辺大輔; 前川博; 松尾裕一
Oral presentation, Japanese, 航空宇宙数値シミュレーション技術シンポジウム2006,航空宇宙数値シミュレーション技術シンポジウム2006
2006

曳航風洞を用いた迎角を持つ翼後流の研究
守田俊之; 前川博
Oral presentation, Japanese, 日本機械学中国四国支部第44期総会・講演会講演論文集,日本機械学中国四国支部第44期総会・講演会講演論文集
2006

DNSによる超音速円形ジェットの音波発生機構の研究
明瀬剛樹; 前川博; 渡辺大輔
Oral presentation, Japanese, 日本機械学中国四国支部第44期総会・講演会講演論文集,日本機械学中国四国支部第44期総会・講演会講演論文集
2006

圧縮性平面チャネル流れの遷移機構に対するマッハ数の影響
上原敦; 前川博; 渡辺大輔
Oral presentation, Japanese, 日本機械学中国四国支部第44期総会・講演会講演論文集,日本機械学中国四国支部第44期総会・講演会講演論文集
2006

Acoustic wave radiation due to coherent vortex motions in a supersonic wake
T.Takiguchi; D.Watanabe; H.Maekawa
Invited oral presentation, English, 19th CFD Symposium, Japan-Korea Special Session, 19th CFD Symposium, Japan-Korea Committee, Tokyo, International conference
2005

DNS of supersonic transitional and turbulent flows
H.Maekawa; D.Watanabe; K.Yamashita
Invited oral presentation, English, International Workshops on Advances in Computational Mechanics, International Workshops on Advances in Computational Mechanics, Tokyo, International conference
2004

Study of Mach Wave Emission Mechanism in a Turbulent Jet at High Convective Mach Numbers using DNS
H.Maekawa; D. Watanabe
Invited oral presentation, English, Russian Japanese Symposium on Actual Problems of Computational Mechanics, Russian Japanese Symposium on Actual Problems of Computational Mechanics, S-Petersburg, International conference
Aug. 2002

DNSによる水素/空気噴流火炎の燃焼音に関する研究
相澤 寛朗; 前川 博
Oral presentation, Japanese, 第39回燃焼シンポジウム講演論文集
Nov. 2001

Simulations of Bypass Transition for Spatially Evolving Disturbances in Compressible Wall-Bounded Flows
Maekawa,H; Yayhaoui Al M
Invited oral presentation, English, Proc. Japan-Russia International CFD Workshop on Turbulence, Instabilities and Parallel Computing. Osaka, International conference
Oct. 2001

流体力学及び演習
The University of Electro-Communications

流体力学及び演習
電気通信大学

流体工学基礎
The University of Electro-Communications

流体工学基礎
電気通信大学

物理学概論第一
The University of Electro-Communications

物理学概論第一
電気通信大学

日本機械学会

日本流体力学会

日本造船学会

可視情報学会

ターボ機械協会

AIAA

緩慢な遷移状態を使ったAttached-Eddyの起源の解明と応用
前川 博
Principal investigator
01 Apr. 2017 - 31 Mar. 2020