| 木原 尚（きはら ひさし） | データ更新日：2024.04.23 |
助教 ／
工学研究院
航空宇宙工学部門
航空宇宙熱・流体力学
| 1. | 馬田勝一郎，木原尚，安倍賢一, 非等方RANSモデルの高次化における機械学習を利用した係数最適化, 日本機械学会西部支部講演会, 2023.12. |
| 2. | 二宮公一，木原尚，安倍賢一, 機械学習を利用したLESのSGS応力の予測精度向上に関する研究, 日本航空宇宙学会西部支部講演会, 2023.12. |
| 3. | 宮下 岳士, 杉原 祐二, 高橋 裕介, 永田 靖典, 木原 尚, ISAS 1MWアーク加熱風洞でガス噴射による通信ブラックアウト低減化研究, 日本機械学会2023年度年次大会, 2023.09. |
| 4. | 宮下 岳士，杉原 祐二，高橋 祐介，永田 靖典，木原 尚, 1MWアーク加熱風洞におけるガス噴射を用いた通信ブラックアウト低減化実験, 令和4年度宇宙航行の力学シンポジウム, 2022.12. |
| 5. | 西尾 利輝，木原 尚，安倍 賢一, アーク風洞流れにおける電子数密度の解析精度向上に関する研究, 日本航空宇宙学会西部支部講演会(2022）, 2022.11. |
| 6. | 秋山 早穂，木原 尚，安倍 賢一, 移動格子を用いた回転翼周りの流れの数値解析とそのモデルに関する研究, 日本航空宇宙学会西部支部講演会(2022）, 2022.11. |
| 7. | 吉田 信貴，木原 尚，安倍 賢一, 機械学習の特徴量がRNASモデルの性能向上に与える影響に関する研究, 日本航空宇宙学会西部支部講演会(2022）, 2022.11. |
| 8. | 宮下 岳士，高澤 秀人，杉原 祐二，高橋 裕介, 木原 尚, 1MWアーク加熱風洞におけるエアフィルム効果による通信ブラックアウト低減化通信試験, 令和3年宇宙航行の力学シンポジウム, 2021.12, The radio-frequency blackout, which is the communication cutoff between a reentry vehicle and ground station during the atmospheric reentry, has been observed for many missions. Aerodynamic heating caused by a strong shock wave in front of the reentry vehicle dissociates and ionizes the gas. This plasma can block the propagation of electromagnetic waves emitted from the antenna on the vehicle. To mitigate the communication blackout, it is significant to reduce the electron number density near the reentry vehicle. We focused on a new mitigation scheme by film cooling approach. Cold gas injected from the vehicle’s surface forms a thin heat-insulating air film layer where electromagnetic waves can propagate because of the low degree of ionization. In this study, we investigated the effects of the air film for the blackout mitigation using a communication test and computational fluid dynamics (CFD) approach for flow field in the large-scale arc-heated wind tunnel. The communication test results and the computed results indicated that gas the air film forms a propagation path of the electromagnetic waves.. |
| 9. | 木原 尚, 通信ブラックアウトの地上試験における模型表面の観察と分析, 令和3年宇宙航行の力学シンポジウム, 2021.12. |
| 10. | 田中 絋生、木原 尚、安倍 賢一, 縦渦の相互干渉を利用した空力特性制御に関する研究, 第35回数値流体力学シンポジウム, 2021.12, A longitudinal vortex appears in many kinds of flow fields of engineering interest and is known to give large influence on the performance of fluid machinery. Therefore, it is important to study how vortex structures interact with each other. In this study, the interaction of unsteady longitudinal vortices under various conditions was investigated numerically. We considered a wing tip vortex generated on an airfoil, and made it interact with a longitudinal vortex generated from a flat plate with several patterns of unsteady motions. From the computational results, we investigated how the introduced vortex from the flat plate affected the wing tip vortex, and consequently the lift and drag coefficients.. |
| 11. | 沖本 和貴，木原 尚、安倍 賢一, 機械学習を利用した非等方RANSモデルの予測精度向上に関する研究, 第35回数値流体力学シンポジウム, 2021.12. |
| 12. | 蔵原 幹弥、木原 尚、安倍 賢一, モード内周波数特性を考慮した固有直交分解による簡易車体周り流れの詳細考察, 第 35 回数値流体力学シンポジウム, 2021.12, Recently, from a viewpoint of CO2 reduction and energy saving, further reduction of fuel consumption for automobiles has become more and more important. For this purpose, reducing the air resistance of a vehicle body is essential because it is much larger than the other road resistances in high-speed driving. Around a vehicle body, various unsteady vortex structures are generated, and their control is known to be important for the aerodynamic performance. In this study, to investigate the vortex structures in more detail, we analyzed simulation results of a flow field around the Ahmed body using Snapshot Proper Orthogonal Decomposition (SPOD) considering frequency characteristics in each mode. Particularly, we adopted two types of flow variables, i.e., velocity and vorticity, in creating the expansion coefficients of POD, and the obtained results were compared to find difference in their features.. |
| 13. | 吉田 海人，木原 尚，安倍 賢一, 通信ブラックアウト予測のための数値解析技術の高精度化に関する研究, 第 35 回数値流体力学シンポジウム, 2021.12, The radio frequency blackout that occurs during a spacecraft re-entry is a complicated phenomenon that is not well understood, and more detailed studies are thus neccesary. In this paper, a numerical study of flow fields around a test model in an arc-heated wind tunnel was performed. Furthermore, the electromagnetic field simulation using a frequency dependent finite difference time domain (FD2TD) method was also performed to clarify the behavior of radio waves. To discuss the validity and further improvement of the simulation, the model was placed with an inclined angle from the nozzle exit, as well as in a straight line. The obtained results are compared with some experimental data.. |
| 14. | 岸本 尚貴, 木原 尚, 安倍 賢一, Sweeping Jet Actuator による遷音速乱流層剥離場の制御に関する数値解析的研究, 2020年度衝撃波シンポジウム, 2021.03, Sweeping jet (SWJ) actuator was introduced to an axisymmetric bump model with the aim to control transonic turbulent boundary-layer separation. Three-dimensional unsteady Reynolds-averaged Navier-Stokes (RANS) simulation was used to investigate the flow control performance of SWJ Actuator with different momentum coefficient. Furthermore, we conducted numerical analysis of a steady jet actuator as another flow control device, and then discussed advantage of SWJ Actuator.. |
| 15. | 三浦 健太郎, 木原 尚, 安倍 賢一, アーク加熱風洞内流れにおける電子数密度の予測精度向上に関する数値解析的研究, 2020年度衝撃波シンポジウム, 2021.03, To predict the radio-frequency blackout precisely, an accurate estimation of the electron number density is indispensable. However, its prediction in our numerical analysis system had been considerably overestimated. In this study, we tried to improve the prediction accuracy of the electron number density of a plasma flow in an arc-heated wind tunnel. In particular, we investigated the sensitivity of several simulation factors on the prediction of the electron number density, e.g., chemical-reaction parameters and Joule-heating conditions. . |
| 16. | 渡部 峻祐, 木原 尚, 安倍 健一, モード内周波数特性を考慮した固有直交分解によるチャンネル乱流内速度場の詳細考察, 第34回数値流体力学シンポジウム, 2020.12, Recently, from a viewpoint of CO2 reduction and energy saving, further reduction of fuel consumption for automobiles has become more and more important. For this purpose, reducing the air resistance of a vehicle body is essential because it is much larger than the other road resistances in high-speed driving. Around a vehicle body, various unsteady vortex structures are generated, and their control is known to be important for the aerodynamic performance. However, these structures are very complex and thus it is difficult to elucidate their essential features. In this study, to investigate the vortex structures in more detail, we performed flow computations of a channel flow and the obtained results were analyzed using Snapshot Proper Orthogonal Decomposition (SPOD) considering frequency characteristics in each mode.. |
| 17. | 廣渡 翔太, 木原 尚, 安倍 賢一, 機械学習を利用したSGS応力の予測精度向上に関する一考察, 第34回数値流体力学シンポシウム, 2020.12, The consideration of turbulence is essential for investigating a high Reynolds number flow field, such as that around an aircraft or a automobile. Owing to the development of super computers, computational fluid dynamics (CFD) has become more and more useful for understanding such complex flow phenomena. Although large eddy simulation (LES) is promising among CFD strategies, its computational cost is still problematic. To reduce the computational cost of LES, the development of a sub-grid scale (SGS) model is indispensable. In this study, a regression of SGS stresses is performed using machine learning (ML). For the present ML, highly-resolved LES data of a plane channel flow are adopted as a teacher dataset, and the results obtained from the regression are carefully investigated by comparison with the target data. . |
| 18. | 高澤 秀人, 高橋 祐介, 大島 伸行, 木原 尚, 1MW アーク加熱風洞における触媒性再結合反応を用いた通信ブラックアウト低減化の通信試験およびメカニズム解明, 2020 年度日本機械学会年次大会 特別企画プログラム, 2020.09, Reentry blackout during the atmospheric reentry interrupts communication between the reentry vehicle and ground stations. To improve safety during reentry, a mitigation method using the surface catalysis effect was proposed. An experimental test of this method using the arc-heated wind tunnel was performed. However, its mechanism is not clear. In this study, we numerically simulated plasma flows in the ISAS 1MW arc-heated wind tunnel and around the atmospheric reentry demonstrator (ARD). Computed results for the non-catalytic and finite-catalytic wall conditions were compared with each analysis. The results showed that the dominant chemical reaction to reentry blackout was the electron-impact ionization. The mitigation mechanism was clarified as follows: 1) the amount of nitrogen and oxygen atoms decreased because of the catalyst; 2) reverse reactions of the electron impact ionization occurred to increase the number of nitrogen and oxygen atoms due to the decrease in atoms; 3) These reverse reactions consumed electrons and thus the reentry blackout was mitigated. It was found that these mechanisms were in common, despite the different airflow conditions between the arc-heated wind tunnel and atmospheric reentry.. |
| 19. | 松下 海渡, 木原 尚, 安倍 賢一, 大流量Radio-Frequencyプラズマスラスタに関する数値解析的研究, 2019年度衝撃波シンポジウム, 2020.03, [URL]. |
| 20. | 橋本 翔吾, 安倍 賢一, 木原 尚, モーフィング宇宙輸送システムにおいて機体形状変化が空力特性に及ぼす影響に関する研究, 2019年度衝撃波シンポジウム, 2020.03, [URL]. |
| 21. | Hideto TAKASAWA, Yusuke TAKAHASHI, Nobuyuki OSHIMA, Hisashi KIHARA, Study on Mitigation of Reentry Blackout by Surface Catalysis Effects in Arc-Heated Wind Tunnel , Aerospace Europe Conference 2020, 2020.02, [URL], Reentry blackout is one of the most important problems during the atmospheric reentry. In this study, we demonstrated a new mitigation method for the reentry blackout using surface catalysis effects, conducting an experiment using arc-heated wind tunnel. Firstly, for a feasibility study, we carried out plasma flow and electromagnetic waves analyses to reproduce blackout environment for non-catalysis and finite catalysis cases in the JAXA/ISAS 1MW arc-heated flow. In the numerical analysis, the electromagnetic wave was completely blocked due to reentry blackout for the case of the non-catalytic wall. On the other hand, for the case of finite catalytic wall, it was confirmed that the electromagnetic wave propagates. From the experimental results, reentry blackout occurred when using alumina as a low catalytic material. On the other hand, for the case of copper as a high catalytic material, it was found that reentry blackout is avoided.. |
| 22. | 高澤 秀人, 高橋 裕介, 大島 伸行, 木原 尚, 1MWアーク加熱風洞における触媒再結合反応を用いた通信ブラックアウト低減化通信実験, 宇宙航行の力学シンポジウム, 2020.12, 触媒性再結合反応による通信ブラックアウトの低減化が数値的に実証されている．アーク加熱風洞を用いて低減化を実験的に実証するため，ISAS 1MWアーク加熱風洞において通信実験を実施した.低触媒材料であるセラミックのケースでは通信ブラックアウトが生じたのに対し，高触媒材料である銅のケースでは生じなかった．この結果は触媒効果による通信ブラックアウト低減化実証を示唆するものである．. |
| 23. | 山口 幹太, 安倍 賢一, 木原 尚, 簡易車体まわりの流れ構造が空力性能に及ぼす影響に関する数値解析的研究, 第33回数値流体力学シンポジウム, 2019.11, [URL]. |
| 24. | 奥 浩希, 安倍 賢一, 木原 尚, 固有直交分解を用いた簡易車体形状周りの非定常流れの構造解析に関する研究, 第33回数値流体力学シンポジウム, 2019.11, [URL]. |
| 25. | 遠藤 拓実, 安倍 賢一, 木原 尚, 空力性能向上に向けたTSTO型宇宙往還機の母機形状の設計手法に関する研究, 第33回数値流体力学シンポジウム, 2019.11, [URL]. |
| 26. | 橋本 翔吾, 安倍 賢一, 木原尚, モーフィング宇宙輸送システムにおいて機体形状変化が空力特性に及ぼす影響に関する研究, 第33回数値流体力学シンポジウム, 2019.11, [URL]. |
| 27. | 松下 海渡, 安倍 賢一, 木原 尚, 大流量RFスラスタに関する数値解析的研究, 第33回数値流体力学シンポジウム, 2019.11, [URL]. |
| 28. | 河野 有哉, Lee ChaeHyun, 木原 尚, 安倍 賢一, アーク加熱風洞内の模型周りのプラズマ流れによる通信ブラックアウト現象に関する数値解析的研究, 第33回数値流体力学シンポジウム, 2019.11, [URL]. |
| 29. | 小森 一矢, 木原 尚, 安倍 賢一, アーク加熱風洞内の模型周りの流れ場・電磁波解析, 平成30年度衝撃波シンポジウム, 2019.03, Numerical simulation of plasma flow around a probe in an arc-heated wind tunnel was performed by using flow field simulation. Plasma parameters necessary for electromagnetic wave analysis were obtained. Electromagnetic wave analysis was performed using frequency dependent finite difference time domain (FD2TD) method. Compared with the experimental results, it was found that the analysis result greatly estimates the attenuation of electromagnetic waves. Parametric study on diffusion coefficient of electrons showed that diffusion coefficient of electrons greatly affects communication possibility . |
| 30. | 亀田 博礼, 木原 尚, 安倍 賢一, Sweeping Jet Actuatorの流れ場とその応用に関する数値解析的研究, 第32回数値流体力学シンポジウム, 2018.12, [URL]. |
| 31. | 鈴木 義久, 木原 尚, 安倍 賢一, LESデータを用いたアプリオリテストによるRANS用壁関数の性能評価, 第32回数値流体力学シンポジウム, 2018.12, [URL]. |
| 32. | 小森 一矢, 木原 尚, 安倍 賢一, アーク加熱風洞内の模型周りの流れ場・電磁波解析, 第32回数値流体力学シンポジウム, 2018.12, [URL]. |
| 33. | 平井 直人, 木原 尚, 安倍 賢一, 縦渦の相互干渉が空力特性に与える影響に関する数値解析的研究 , 第32回数値流体力学シンポジウム, 2018.12, [URL]. |
| 34. | 河野有哉，小森一矢，木原尚，安倍賢一, アークプルームと通信電波発信源の位置関係が通信に及ぼす影響に関する基礎的研究, 日本航空宇宙学会西部支部講演会(2018), 2018.11. |
| 35. | 河野有哉，小森一矢，木原尚，安倍賢一, 通信ブラックアウトの地上試験の試みとその数値シミュレーション, 宇宙科学技術連合講演会, 2018.10, [URL], The radio frequency blackout that occurs when a spacecraft reentry was reproduced in experiments using an arc heated wind tunnel. A ϕ50 probe that is cooled by water and a radio transmitter installed was setting in the arc heated flow, and a radio receiver was setting up outside of tunnel chamber. The blackout was confirmed as the communication stoppage between the transmitter and the receiver. Additionally, Three dimensional flow field around the probe with radio transmitter located in the arc heated wind tunnel was simulated by numerical simulation. The result of numerical simulation agrees with the experimental result that showed radio frequency blackout. Comparing the results of experiments and simulation makes it possible to improve the accuracy of numerical simulation of the radio frequency blackout.. |
| 36. | Soomin Park, Hisashi Kihara, Ken-Ichi Abe, Numerical study on the condensed and frozen water vapor on a flat plate using an open source code, 10th AIAA Atmospheric and Space Environments Conference, 2018, 2018.06, [URL], Numerical study on the condensed and frozen vapor on a flat plate was performed to estimate the trends of the freezing of water vapor and its thickness. For the simulation of the phase change of water vapor for the freezing, VOF(Volume of Fluid) method was used. As the freezing area growth, we investigated the flow-velocity variation in the wall-normal direction. Zero-velocity region in the frozen layer was calculated using the Carman-Kozeny equation deriving from the Darcy law in the momentum equation. The phase change rate was assumed to be mainly related the temperature difference between a plate and atmosphere. Basic concept of the freezing phenomenon was combined with the condensation vapor schematics. The calculation for the volumetric generation rate and the freezing rate of water-vapor was controlled by the thermophysical approaches and the enthalpy-porosity method to model the condensation and the freezing, respectively. The numerical simulation was conducted using an open source code, named OpenFOAM®. The obtained results were compared to the corresponding references for the variation of the frozen thickness by the phase change. The comparison of the prediction results with the reference data showed god agreement. Also, positive possibilities of the performance for obtaining better results are expected by using additional complements in further studies.. |
| 37. | ジョンミンソク,木原尚,安倍賢一,高橋裕介, Atmospheric Reentry Demonstrator (ARD) ミッションにおける通信ブラックアウトシミュレーション (表面触媒性の影響) , 平成29年度衝撃波シンポジウム, 2018.03, Using a three-dimensional model considering an angle of attack and catalytic reaction of surface, numerical simulations of plasma flow and electromagnetic waves around an atmospheric reentry demonstrator (ARD) were performed. The comparison of the distributions of flow-field properties was obtained between the non-catalytic wall and the finite-catalytic wall model. The comparison of the results of two models, it was shown that wall condition has strong influence on the distribution of electron number density in the wake region of a vehicle. A frequency-dependent finite-difference time-domain (FD2TD) method was adopted as numerical simulation method of electromagnetic waves, and properties of plasma around a vehicle, which were obtained by the simulation of flows around the vehicle with strong shock wave. The behaviors of electromagnetic waves around a vehicle were evaluated. Moreover, the numerical results of plasma attenuation were compared with those of an experiment between the ARD and a data relay satellite to evaluate the predictive performance of surface catalytic models.. |
| 38. | 鳥居裕規 木原尚 安倍賢一, 固有直交分解を用いた円柱まわりの非定常流れの構造解析, 第31回数値流体力学シンポジウム, 2017.12. |
| 39. | 山本英貴 木原尚 安倍賢一 李曄 岡本哲, 実走行条件における簡易車体形状周り流れのLarge Eddy Simulation, 第31回数値流体力学シンポジウム, 2017.12. |
| 40. | 岡崎一真 安倍賢一 ＠木原尚 ジョン・ミンソク, アーク加熱風洞内に設置された模型周りの流体・電磁波解析, 第31回数値流体力学シンポジウム, 2017.12. |
| 41. | S. Nozawa, T. Kanzaka, Hisashi Kihara, Ken-Ichi Abe, Experimental and numerical studies of spallation particles ejected from a light-weight ablator, 61st International Astronautical Congress 2010, IAC 2010, 2010, During atmospheric entry, thermal protection material (ablator) is strongly heated by aerodynamic heating. Due to this fact, micro-order particles are generated and ejected from an ablator surface, which is called 'Spallation'. In the previous ground experiments in an arc-heated facility, the presence of spalled solid particles has been confirmed upstream of a detached shock wave or a stagnation-point boundary layer. Spallation phenomena are considered to be a possible cause of increasing heat-transfer rates on an ablator surface in the downstream region. To estimate the effect of a spalled particle on an ablator, correct values of particle parameters (e.g., size, flight velocity, position) are needed. Therefore, we carried out the heating experiment for a trial manufactured light-weight ablator, and then detailed parameters for each particle were analyzed directly from the visualized pictures. As for the visualization method, the in-line holography method, that uses a recorded hologram pattern appearing behind of an illuminated particle by a collimated laser beam, was applied to evaluate the particle parameters. Moreover, the flight path of a single spallation particle was also numerically analyzed in the present study. As a result, some particles ejected from an ablator surface were visualized in the upstream region and their parameters were evaluated successfully. This fact indicates the availability of the in-line holography method for evaluation of spallation-particle parameters. By using the obtained particle parameters, the effect of a spalled particle on an ablator surface was estimated.. |
| 42. | 金子 澄人, ジョン ミンソク, Hisashi KIHARA, 安倍 賢一, アーク加熱風洞気流の熱流束分布計測とそのプローブ周りの3Dシミュレーション, 平成28年度衝撃波シンポジウム, 2017.03, [URL], Three-dimensional simulation for flow fields in an arc-heated wind tunnel was developed and numerical simulation of a flow field around a columnar test piece was performed. The results were compared with those by an axisymmetric calculation. Comparison of these two cases enabled us to investigate the detailed distributions of the flow-field properties. It was clarified that the calculation of the three-dimensional model provided predictions quite similar to those of the axisymmetric calculation and thus the present code worked reasonably. In addition, it measured heat flux using the probe to have made it have an angle of attack to the arc flow to emphasize a three-dimensional effect and compered with the simulation. . |
| 43. | Minseok Jung, Hisashi Kihara, Ken-Ichi Abe, Yusuke Takahashi, Numerical simulation of plasma flows and radio-frequency blackout in atmospheric reentry demonstrator mission, 47th AIAA Fluid Dynamics Conference, 2017, 2017.01, Numerical simulations of plasma flows and electromagnetic waves around a reentry vehicle were performed to estimate the radio-frequency blackout. The plasma flows in the shock layer and wake region were calculated using computational fluid dynamics technique. The simulation of electromagnetic waves around a reentry vehicle was conducted using a frequency-dependent finite-difference time-domain method with the plasma properties obtained by computational fluid dynamics. The numerical simulations were performed for the atmospheric reentry demonstrator at various altitudes based on the reentry orbit data. Three cases of the numerical simulations, i.e., an axisymmetric model, a three-dimensional model with non-catalytic wall and finite-catalytic wall, were performed for evaluating the effects of angle of attack and catalytic wall on the radio-frequency blackout. The formations for the number density of electrons that is an important parameter in evaluating the radio-frequency blackout were greatly changed by these three cases. The simulation model was validated based on the signal loss history of the experimental flight data. The simulation results using a three-dimensional model with finite-catalytic wall showed better agreement with the measured results compared to other two cases.. |
| 44. | 島中 大輝, Hisashi KIHARA, 安倍 賢一, 李 曄, 岡本 哲, 非等方SGSモデルを導入した簡易車体形状周り流れのLarge Eddy Simulation, 第30回数値流体力学シンポジウム, 2016.12, These days it is important to protect environmental by global warming. Since the low mileage becomes important to car development. The other hand, in late years, computational fluid dynamics (CFD) become used for car development by the progress of the computer engineering. However, a cost reduction to get enough predictability is still problem. Also we need the lattice point of hundreds of millions for CFD. Therefore, in this study, it applies an anisotropy resolving SGS model that developed by Abe in 2005. We took good agreement in Cd between CFD and Experiment by using fillet tire. However, disagreement of flow under floor and side wall flow were seen in distributions of total Cp.. |
| 45. | 金子 澄人, ジョン ミンソク, Hisashi KIHARA, 安倍 賢一, アーク風洞内部に設置された模型周りの3次元流れ解析, 第30回数値流体力学シンポジウム, 2016.12, Three-dimensional simulation for flow field in an arc-heated wind tunnel was developed and numerical simulation of the flow field around a columnar test piece was performed with axisymmetric and three-dimensional model. Using the flow field simulation of two models, the detailed distributions of flow field properties were obtained. From comparing the results of two models, it was clarified that three-dimensional model secure about the same accuracy as axisymmetric model.. |
| 46. | ジョン ミンソク, Hisashi KIHARA, 安倍 賢一, 高橋 裕介, 迎角を考慮したAtmospheric Reentry Demonstrator周りのプラズマ流・通信ブラックアウト解析, 平成27年度衝撃波シンポジウム, 2016.03, [URL], Using an axisymmetric model and a three-dimensional model considering an angle of attack, numerical simulations of plasma flow and electromagnetic waves around an atmospheric reentry demonstrator (ARD) were performed.. |
| 47. | 林 隼也, Hisashi KIHARA, Ken-ichi ABE, 球周り流れのLESにおいて非等方SGSモデルが予測精度に与える影響に関する研究, 第29回数値流体力学シンポジウム, 2015.12. |
| 48. | ジョン ミンソク, 高橋 裕介, Hisashi KIHARA, Ken-ichi ABE, 3次元流体・電磁波連成解析システムを用いたAtmospheric reentry demonstrator 周りのプラズマ流解析, 第29回数値流体力学シンポジウム, 2015.12. |
| 49. | チョウ ヤンロン, Hisashi KIHARA, 安倍 賢一, Performance of an anisotropy-resolving subgrid-scale model for predicting turbulent channel flow with wall roughness, 8th International Symposium on Turbulence, Heat and Mass Transfer 8th, 2015.09, Large eddy simulation (LES) of a turbulent channel flow with wall roughness on one side was performed by adopting an anisotropy-resolving subgrid-scale (SGS) model at a shear Reynolds number Reτ=395. . |
| 50. | Y. Zhang, H. Kihara, K. Abe, Performance of an anisotropy-resolving subgrid-scale model for predicting turbulent channel flow with wall roughness, 8th International Symposium on Turbulence, Heat and Mass Transfer, THMT 2015, 2015.01, Large eddy simulation (LES) of a turbulent channel flow with wall roughness on one side was performed by adopting an anisotropy-resolving subgrid-scale (SGS) model at a shear Reynolds number = 395. To investigate the grid dependency of the LES results caused by the SGS model, three grid resolutions were tested under the same definition of a roughness shape by using the immersed boundary method. The obtained results were compared with the direct numerical simulation data without roughness (flat wall) and discussed using general knowledge in this kind of flow fields as reference. The primary concern was focused on how the present SGS model could reduce the grid dependency as well as the affects of roughness on the mean velocity and turbulent stresses.. |
| 51. | 高橋 正隆, Hisashi KIHARA, Ken-ichi ABE, 高レイノルズ数乱流境界層に対するLESの予測性能向上に関する研究, 日本航空宇宙学会西部支部講演会（2014）, 2014.11, 本研究室にて開発した乱流の異方性を考慮した付加項をLESのサブグリッドスケールモデルに付加することによりより負荷の小さい方法で高い予測精度を保つ計算ができることを示した．. |
| 52. | Yu Minghao, Yusuke Takahashi, Hisashi KIHARA, Ken-ichi ABE, Kazuhiko Yamada, Takashi ABE, Satoshi Miyatani, Thermal Nonequilibrium Modeling of an Air Inductively Coupled Plasma Flow, 飛行機シンポジウム, 2014.10, Numerical investigation of thermal nonequilibrium inductively coupled plasma (ICP) flow was carried out to study the physical properties of the flow inside a 10-kW ICP wind tunnel with the working gas being air. The flow field was described by two-dimensional compressible axisymmetric Navier-Stokes (N-S) equations that took into account 11 species and 49 chemical reactions. A four-temperature model was adopted to model thermal nonequilibrium process in the discharge torch and vacuum chamber. The magnetic vector-potential equations were tightly coupled with the flow-field equations to describe the heating process by inductive discharge. The characteristics of air ICP flow such as thermal nonequilibrium, inductive discharge, and effects of Lorentz forces became clear through the present study.. |
| 53. | Naoki Kawano, Hisashi KIHARA, Ken-ichi ABE, Three-Dimensional Numerical Study of High Temperature Flow Field around an Experimental Atmospheric Re-Entry Vehicle, The 5th Asian Joint Workshop on Thermophysics and Fluid Science, 2014.09. |
| 54. | Hisashi KIHARA, アーク加熱風洞の澱み点付近の発光分光計測における視線の違いについて, 日本機械学会2014年度年次大会, 2014.09, アーク加熱風洞気流中において供試体周りの分光計測を行う場合に供試体側方から計測することが一般的であるが．模型内部から衝撃波背後の発光の様子を取得しようとしたところ，側方からと正面からで大きく異なった結果が得られた．そこでこの現象について報告すると共に，その原因について議論する． 特に違いの分かる窒素流について観測を行った． 特に側方からの観測では分子からのスペクトルが中心で観測されるが，正面からの観測では分子からの発光は非常に弱く，ほとんどが原子からの発光であった．その上ノズル中心軸における正面からの観測では，窒素原子イオンからの発光がほとんどであるが，中心軸を若干ずらし，放電を起こしている場所，陽光柱を直接観測的ない状態でデータを取得すると，窒素の中性原子からの発光が中心となった．このことから予想がつくことは，発生しているプラズマにおいて光学的な厚さが薄く，正面からの観測においてはほとんどノズル内部からの発光を捉えており，プローブ前方に発生している衝撃波背後の発光は相対的に非常に弱いことが分かった． このことにより，ノズルスロートを観測することにより，放電の状態を捉えることができる可能性が示唆された． . |
| 55. | 喩 明浩, Yusuke Takahashi, Hisashi Kihara, Ken-ichi Abe, Kazuhiko Yamada, Takashi Abe, Numerical Simulation of Nonequilibrium Inductive Plasma Flow Coupled with Electromagnetic Field Calculation, 29th International Symposium on Rarefied Gas Dynamics, 2014.06, [URL], Numerical investigation of nonequilibrium inductively coupled plasma (ICP) flow was carried out to study the physical properties of the flow inside a 10-kW ICP torch with the working gas nitrogen. The flow field was described by two-dimensional compressible axisymmetric Navier-Stokes (N-S) equations that took into account 5 species and 8 chemical reactions. The magnetic vector potential equations were tightly coupled with flow field equations to describe the heating process by inductive discharge. A four-temperature model was adopted to model thermal nonequilibrium process in the discharge torch. The characteristics of ICP flow such as thermal nonequilibrium, inductive discharge, strong effects of Lorentz forces become clear through the present study.. |
| 56. | Yu Minghao, Yusuke TKAHASHI, Hisashi KIHARA, Ken-ichi ABE, Numerical study of inductively coupled plasma flow, 平成25年度衝撃波シンポジウム, 2014.03, Numerical simulation of 10-kW inductively coupled plasma (ICP) wind tunnel was carried out to study the physical properties of the flow inside the ICP torch and vacuum chamber with air as the working gas. Two-dimensional compressible axisymmetric Navier-Stokes (N-S) equations that took into account 11 species and 49 chemical reactions of air were solved. A heat source model was used to describe the heating phenomenon instead of solving the electromagnetic equations. In the vacuum chamber, a four-temperature model was coupled with N-S equations. It was found that the plasma flow in the vacuum chamber tended to be local thermochemical equilibrium.. |
| 57. | 吉竹 恒, Ken-ichi ABE, Hisashi KIHARA, Immersed Boundary Methodを用いた高揚力装置まわり流れの数値解析, 第27回数値流体力学シンポジウム, 2013.12. |
| 58. | 漆間 統, Hisashi KIHARA, Ken-ichi ABE, 非等方性SGSモデルを導入したLES/RANSハイブリッドモデルの翼周り流れへの適用, 第27回数値流体力学シンポジウム, 2013.12. |
| 59. | 木原 尚, 梅野 晃太郎, 安倍 賢一, アーク加熱風洞における光ファイバーを用いた模型内部からの分光計測, 日本機械学会2013年度年次大会, 2013.09, [URL], When we produce a thermal protection system (TPS) for the space vehicle entering a planet, the arc-heated wind tunnel is used widely. The arc-heated flow is very complicated. In addition, we assume the on-board measurement of spectroscopy to understand the flow properties of very strong shock-heated gas. Present work show a method of head-on measurement of spectroscopy used optical fiber in high-enthalpy gas. At first, the head-on measurement of spectroscopy and side-on measurement were compared. At argon flow, the electronic excited temperature has 500 K difference between these two methods. At the nitrogen flow, in the case of the head-on, it could see only the spectrum from nitrogen atom. The light weight ablator (like PICA) materials was used as TPS. The head-on measurement could operate over the 10 seconds for light weight ablator. In addition, the time resolved measurement of spectroscopy caught the change of the property of spectrum.. |
| 60. | Osamu URUMA, Hisashi Kihara, Ken-ichi Abe, An Improvement of Hybrid LES/RANS Model for Complex Turbulence with the Aide of an Anisotropy-Resolving Subgrid-Scale Model , 29th Internatonal Symposium on Space Tchnology and Sience, 2013.06, We propose a new Hybrid LES/RANS Model (HLR) which combines large eddy simulation (LES) with the Reynolds-averaged Navier-Stokes (RANS) equation with the aide of an anisotropy-resolving subgrid-scale (SGS) model based on a scale-similarity model 4). We find that the introduction of an SGS anisotropic term give a reasonable influence on the transition between RANS and LES. To investigate the model performance, the proposed model is applied to fully-developed plane channel flows with various grid resolutions and at several Reynolds numbers. For further investigation, we apply the present model to high Reynolds-number complex turbulent flows of practical interest. The Ahmed body with the 25° angle of the rear slant which the Reynolds number based on length of is Re=2.78×10⁶ is selected for verification of the present model. For the flow structure, the result of HLR model shows similar to that of experiment in coarse and fine grid. The value of the friction drag coefficient of HLR model has a smaller the grid dependence than that of LES and corresponds to that of experimental. However, the pressure drag is underestimated. As the result, the drag coefficient of Ahmed body is underestimated.. |
| 61. | 喩 明暁, 木原 尚, 安倍 賢一, Numerical Investigation on Plasma Flow in Low Power Inductively Coupled Plasma Wind Tunnel, The 4th Asian Symposium on Computational Heat Transfer and Fluid Flow, 2013.06. |
| 62. | 松田 貴幸, 木原 尚, 安倍 賢一, Numerical Study of Thermochemical Nonequilibrium Flow around Reentry Capsule and Estimation of Aerodynamic Heating, The 7th Asian Pacific Conferenc on Aerospace Technology and Science, 2013.05, Numerical simulation of the flow fields was performed for the mission of Apollo AS-202 to investigate the influence of the laminar-turbulent transition position in the boundary layer around a reentry capsule on the heat flux at the wall. For this purpose, we intentionally varied the laminar-turbulent transition position and the obtained results were compared. It turned out that the transition position had a big influence on the heat flux at the wall in the forebody region. On the other hand, in the afterbody region, some discrepancies were seen compared with the experimental data. This is thought to be caused by the lack of considering the effects of the radiation heating and the radiation equilibrium, as well as the axisymmetric flow assumption.. |
| 63. | 木原 尚, 平田 尚也, Ken-ichi Abe, A Study of Thermal Response and Flow Field Coupling Simulation around HAYABUSA Capsule Loaded with Light-weight Ablator, The 11th International Symposium on Experimental and Computational Aerothermodynamics of Internal Flows, 2013.05, The numerical simulation of flow field around HAYABUSA capsule with light-weight ablator thermal response coupled with pyrolysis gas flow inside ablator was carried out. In addition, the radiation from high temperature gas around the capsule was tightly- coupled with flow field. The HAYABUSA capsule reentered the atmosphere about 12 km/sec in velocity and Mach number about 30. During such an atmospheric entry, space vehicle is exposed very savior aerodynamic heating due to convection and radiation. In this study, HAYABUSA capsule was treated as a typical model of the atmospheric entry spacecraft. The light-weight ablator had porous structure, and permeability was an important parameter to analyze flow inside ablator. In this study, permeability was a variable parameter depended on density of ablator. It found that the effect of permeability of light-weight ablator was important with present analysis.. |
| 64. | 川野 亨樹, 崔 , 平田 尚也, 木原 尚, 安倍 賢一, 熱分解による透過率変化を考慮した軽量アブレータ熱応答試験の数値シミュレーション, 平成23年度衝撃波シンポジウム, 2013.03, アーク加熱風洞での軽量アブレータの加熱試験の様子をより再現するために軽量アブレータの特徴である内部の流れを様子を温度による透過率変化をパラメータの一つとして導入することにより高精度な数値シミュレーションを外部の流れとともにカップリングさせて行いこの取り扱いの必要性を明らかにした． . |
| 65. | 喩 明暁, 高橋裕介, 木原 尚, 安倍 賢一, Numerical evaluation of nonequilibrium plasma flow in 1kW class thruster, ISPlasma, 2013.01, 衛星の軌道修正用の小型のアークジェット推進機内部の弱電離気体がノズルから排出するまでの熱的および化学的に非平衡な流れ場の様子を簡単なモデルを用いることにより明らかにした．. |
| 66. | 平田尚也, 木原 尚, 安倍 賢一, 超軌道再突入環境における軽量アブレータの熱応答解析, 2012年度日本機械学会流体力学部門講演会, 2012.11, Hayabusa再突入カプセルの再突入環境をモデルにとり，熱防御システムとして近年開発が進んでいる軽量アブレータを用いた場合どのようになるか，また，従来のアブレータとどのような違いが出て何に注意しながら耐熱設計をしなければならないかを論じた．. |
| 67. | 木原 尚， 平田尚也， 安倍賢一, 軽量アブレータの熱分解ガス内部流動と熱応答, 日本機械学会2012年度年次大会, 2012.09. |
| 68. | Yusuke Takahashi, Takashi Abe, Hiroki Takayanagi, Masahito Mizuno, Hisashi Kihara, Ken-Ichi Abe, Nonequilibrium plasma flow properties in arc-heated wind tunnels, 50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, 2012.06, Turbulent plasma flows in arc heaters such as JAXA 750 kW, NASA 20 MW and Kyushu University 20 kW facilities were investigated and the distributions of flow-field properties were successfully obtained. For this purpose, an integrated analysis model to simulate various-scale arc-heated flows with high accuracy was developed. The turbulent flow field was described by the Navier-Stokes equations with a multitemperature model, which was tightly coupled with electric-field and radiation-field calculations. An accurate and low-cost radiation model and a low-Reynolds number two-equation turbulence model were introduced into the flow-field simulation. Arc discharge in constrictor section and expansion processes in nozzle section play key roles for forming an arc-heated flow. Thus, it is important to correctly model those phenomena for predicting the high-enthalpy flow properties accurately. To validate the present numerical model, the computed results were compared with the corresponding experimental data for the mass-averaged enthalpy, temperatures and number density. Through the comparison of the predicted results with detailed experimental data obtained by spectroscopic and laser-induced fluorescence techniques, the present integrated analysis model was validated. In addition, the mechanisms of energy input by discharge and energy loss were discussed with distributions of the temperature and heat flux derived from the arc column. Although it was indicated that more detailed discharge model is possibly required in order to describe arc discharge with higher accuracy, the present flow-field model was found to give generally good agreement for various operating conditions of the facilities.. |
| 69. | 木原 尚，平田尚也，安倍賢一, 20kW級アーク加熱風洞で加熱されるアブレータ内部の熱分解ガス流動の影響, 衝撃波シンポジウム, 2012.03, Thermal-response analysis and an arc-heated wind tunnel experiment were carried out to study the effect of the pyrolysis gas flow inside the heating ablator. The analysis treated the heating process of arc-heater and the thermal-response analysis code included heat conduction, pyrolysis of resin, pyrolysis gas flow, and surface recession due to chemical reactions. In this study, the pyrolysis gas flow was treated as the multi-dimensional (axisymmetric) and unsteady phenomenon. This computation showed that the detailed analysis considering the multi-dimensional pyrolysis-gas flow and the flow injection of pyrolysis gas led to improvement of the predictive performance for the ablator thermal response. In addition, the temperature measurements inside and surface of the light-weight ablator were carried out. It was used two type ablator in this experiment. As for one, surfaces were coated and the other was non-coated. . |
| 70. | 山田雅隆，木原 尚，安倍賢一, 超軌道再突入飛行体周りの熱化学的非平衡流に対する機体の耐熱特性に関する数値解析, 宇宙航行の力学シンポジウム, 2011.12, HAYABUSA再突入カプセルの超軌道からの再突入時の機体周りの流れ場と熱伝達及びアブレータ内部の熱応答の弱カップリング計算を行った．この計算においては衝撃波層からの輻射についても3-bandモデルを非平衡流に拡張することによりカップリングも行っている．この輻射モデルは非常に計算コストが低くかつ精度が高く維持することができた．この研究ではアブレータの厚さが十分であることも確認された．. |
| 71. | 山田雅隆，木原 尚，安倍賢一, 超軌道再突入飛行体周りの熱化学的非平衡流に対する機体の耐熱特性に関する数値解析, 日本航空宇宙学会西部支部講演会, 2011.11, HAYABUSA再突入カプセルの超軌道からの再突入時の機体周りの流れ場と熱伝達及びアブレータ内部の熱応答の弱カップリング計算を行った．この計算においては衝撃波層からの輻射についても3-bandモデルを非平衡流に拡張することによりカップリングも行っている．この輻射モデルは非常に計算コストが低くかつ精度が高く維持することができた．この研究ではアブレータの厚さが十分であることも確認された．. |
| 72. | Naoya Hirata, Sohey Nozawa, Yusuke Takahashi, Hisashi Kihara and Kenichi Abe, Numerical Study of Pyrolysis Gas Flow and Transfer inside an Ablator, The Asian Symposium on Computational Heat Transfer and Fluid Flow , 2011.09. |
| 73. | Masataka Yamada, Yohei MATSUDA, Naoya HIRATA, Yusuke TAKAHASHI, Hisashi KIHARA and Ken-ichi ABE, Numerical Simulation of Flow Field and Heat Transfer around HAYABUSA Reentry Capsule , 28th International Symposium of Spacetechnology and Spacesience , 2011.06. |
| 74. | 平田尚也，野澤創平，高橋裕介，木原 尚，安倍賢一, アブレータ内部のガス流動を考慮した熱応答解析技術の高精度化について, 平成22年度衝撃波シンポジウム, 2011.03. |
| 75. | 野澤創平，木原 尚，安倍賢一, 軽量アブレータから放出されるスポレーション粒子に関する実験的数値的研究, 平成22年度衝撃波シンポジウム, 2011.03. |
| 76. | Yusuke Takahashi, Hisashi Kihara, Ken-Ichi Abe, Numerical simulation of flow fields in large-scale segmented-type arc heaters, 27th Congress of the International Council of the Aeronautical Sciences 2010, ICAS 2010, 2010.12, Turbulent plasma flow in large-scale arc heater such as NASA 60 MW Interaction Heating Facility was numerically investigated and the distribution of the arc-heated flow-field properties were successfully obtained.The turbulent flow-field was described by the Reynolds- Averaged Navier-Stokes equations with a multitemperature model,tightly coupled with the electric field and the radiation-field calculations. In addition,an accurate and low-cost radiation model and a low-Reynolds number two-equation turbulence model were introduced into the flowfield simulation.It was quantitatively clarified that radiation and turbulence phenomena are very important mechanisms to transfer heat and momentum from high-temperature core region to cold gas region near the wall.To validate the present numerical model,the numerical solutions were compared with the experimental data,e.g.,arc voltage,mass-averaged enthalpy,chamber pressure and heat efficiency.It was indicated that the present flow-field simulation model showed good agreement over various operating conditions of the facilities.. |
| 77. | 高橋裕介, 木原 尚, 安倍賢一, アーク加熱気流解析の電圧予測に対する陰極表面近傍の物理現象の影響, 宇宙航行の力学シンポジウム, 2010.12. |
| 78. | 松田洋平，野澤創平，高橋裕介，木原 尚，安倍賢一, 木星大気突入飛翔体周りの数値解析における各種物理モデルのアブレータ損耗量への影響評価, 宇宙航行の力学シンポジウム, 2010.12. |
| 79. | 入口信也, 木原 尚, 安倍賢一, 非構造格子を用いた3次元複雑模型形状周りの数値解析, 日本航空宇宙学会西部支部講演会, 2010.11. |
| 80. | 大崎祐摩,Francois Berthelemy, 木原 尚, 安倍賢一, 3次元ディフューザ流れにおける剥離を伴う大規模乱流構造の数値予測とその高精度化に関する研究, 日本航空宇宙学会西部支部講演会, 2010.11. |
| 81. | Sohei NOZAWA, Tadashi KANZAKA, Hisashi KIHARA and Ken-ich ABE, Experimental and Numerical Studies of Spalled PArticles Ejected from a Light-weight Ablator, 61st International Astronautical Congress, 2010.09. |
| 82. | Yusuke TAKAHASHI, Hisashi KIHARA and Kin-ich ABE, Numerical Simulation of FLow Fields in Large-Scale Segmented-Type Arc Heaters, 27th Congress of the International Council of Aeronautical Sciences 2010, 2010.09. |
| 83. | 木原 尚, 神坂直志, 安倍賢一, アーク気流中に置かれたアブレータの熱応答, 日本機械学会全国大会, 2010.09. |
| 84. | 高橋裕介，木原 尚，安倍賢一, 低Re数型乱流モデルを用いたアーク加熱気流解析, 平成21年度衝撃波シンポジウム, 2010.03. |
| 85. | 野澤創平，神坂直志，木原 尚，安倍賢一, 軽量アブレータから放出されるスポレーション粒子の可視化実験, 平成21年度衝撃波シンポジウム, 2010.03. |
| 86. | 野澤創平，木原 尚，安倍賢一, アブレータから放出されるスポレーション粒子に関する基礎研究, 平成21年度宇宙航行の力学シンポジウム, 2009.12. |
| 87. | 高橋裕介，木原 尚，安倍賢一, 大型アーク加熱風洞における乱流輸送の影響について, 平成21年度宇宙航行の力学シンポジウム, 2009.12. |
| 88. | Tadashi Kanzaka, Sohey Nozawa, Yusuke Takahashi, Hisashi Kihara, Ken-ichi Abe , Numerical Analysis of Thermal Response of Ablator Exposed to 20kW Arc-heated Flow, 日本航空宇宙学会西部支部講演会, 2009.12. |
| 89. | Tadashi Kanzaka, Sohey Nozawa, Yusuke Takahashi, Hisashi Kihara and Ken-ichi Abe, Numerical Investigation of Thermal Response of Ablator Exposed to Thermochemical Nonequilibrium Flow, The 6th Asian-Pasific Conference Aerospace Technology and Science, 2009.11. |
| 90. | S. Nozawa, H. Kihara, K. Abe, An Investigation of Spalled Particle Behavior Ejected from an Ablator Surface with the Aid of CFD, The Asian Symposium on Computational Heat Transfer and Fluid Flow, 2009.10. |
| 91. | 木原 尚，神坂直志, 松原 学, 安倍賢一, アーク気流中に置かれたプローブの温度計測と数値計算, 日本機械学会2009年度全国大会, 2009.09. |
| 92. | S. Nozawa, H. Kihara, K. Abe, Numerical investigation of spalled particle behavior ejected from an ablator surface, 27th International Symposium on Space Technology and Science, 2009.07. |
| 93. | Sohei NOZAWA, Hisashi KIHARA and Kin-ich ABE, Numerical Investigation of Spalled Particle Behavior Ejected from an Ablator Surface, 27th International Symposium on Space Technology and Science, 2009.06. |
| 94. | Yusuke Takahashi, Hisashi Kihara, Ken Ichi Abe, Numerical investigation of thermochemical nonequilibrium flow field in a 20kW arc heater coupled with electric field calculation, 26th International Symposium on Rarefied Gas Dynamics, RGD26, 2009.04, Numerical simulation is carried out and the distribution of flow field properties is obtained for nonequilibrium flow in a constrictor-type 20kW arc-heated wind tunnel. In the arc heater, plasma flow is highly in nonequilibrium and arc discharge plays a critical role. The flow field is described by the Navier-Stokes equations with a multi-temperature model. The flow field equations are solved with the governing equation for the electric field being coupled. Furthermore, to validate the present numerical model, the numerical solutions are compared with the corresponding experimental data. The flow characteristics in the 20kW arc heater, e.g., the arc charge and the supersonic expansion, become clear through the present simulation. Moreover, the computed results for the arc heater indicate almost full dissociation/ ionization reactions and thermochemical equilibrium in the constrictor part, while strong nonequilibrium clearly appears in the nozzle section.. |
| 95. | Yuusuke TAKAHASHI, Hisashi KIHARA, Ken-ichi ABE, Numerical Investigation of Thermochemical Nonequilibrium Flow Field in a 20kW Arc Heater Coupled with Electric Field Calculation, 26th International Symposium of Rarefied Gas Dynamics, 2008.07. |
| 96. | 田邊友季 木原尚 安倍賢一, 木星大気突入飛翔体まわりの化学的非平衡数値解析, 平成19年度 衝撃波シンポジウム, 2008.03. |
| 97. | 高橋裕介 木原尚 安倍賢一, 20kWアークヒータにおける電場と熱化学的非平衡流の連成解析, 平成19年度 衝撃波シンポジウム, 2008.03. |
| 98. | Yusuke Takahashi, Hisashi KIHARA, Ken-ich ABE , Numerical Simulation of Plasma Flows in a 20kW Arc-heated Wind Tunnel Using Multi-temperature Model, Third Asian-Pacific Congress on Computational Mecanics, 2007.12. |
| 99. | 高橋裕介 木原尚 安倍賢一, アーク加熱風洞における熱化学的非平衡流の数値解析, 平成18年度 衝撃波シンポジウム, 2007.03. |
| 100. | 木原 尚, 波多野正樹, 南金山憲幸, 安倍賢一, 西田迪雄, アブレータ熱防御におけるスポレーション現象の基礎的研究, 第82期 日本機械学会流体工学部門 講演会, 2004.11. |
| 101. | 亀山 剛, 木原 尚, 安倍賢一, 西田迪雄, 高エンタルピー空気の熱化学的非平衡ノズル流, 日本機会学会流体工学部門講演会, 2003.09. |
| 102. | 和田 英一, 西田 迪雄, 桜井 晃, 安倍 賢一, 木原 尚, 松原 学, 大屋 裕二, 小型風車後流の速度計測, 風力エネルギー利用シンポジウム, 2003.11. |
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