Details of the Researcher

PHOTO

Tsubasa Ikami
Section
Institute of Fluid Science
Job title
Assistant Professor
Degree

  • 博士（工学）（東北大学）

  • 修士（工学）（東北大学）

e-Rad No.
80980490
Researcher ID
DWS-0142-2022

Research History 2

  • 2023/04 - Present
    Tohoku University　Institute of Fluid Science　Assistant Proferssor

  • 2022/04 - 2023/03
    Tohoku University　Graduate School of Engineering Department of Aerospace Engineering

Education 2

  • Tohoku University　Graduate School of Engineering　Department of Aerospace Engineering

    2018/10 - 2023/03

  • Tohoku University　Faculty of Engineering　Department of Mechanical and Aerospace Engineering

    2015/04 - 2018/09

Committee Memberships 1

  • 可視化情報学会　学会誌編集委員幹事

    2024/08 - Present

Professional Memberships 2

  • 日本航空宇宙学会

    2019/03 - Present

  • 可視化情報学会

    2019 - Present

Research Interests 9

  • Fluid Dynamics

  • Aerodynamics

  • Wind Tunnel

  • Mars Helicopter

  • Mars Airplane

  • Low Reynolds Number

  • Pressure-Sensitive Paint

  • Temperature-Sensitive Paint

  • Flow Measurement

Research Areas 2

  • Aerospace, marine, and maritime Engineering / Aerospace engineering /

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

Awards 12

  1. 一般表彰スペースフロンティア

    2024/03　日本機械学会宇宙工学部門　大気球を利用した火星飛行機の高高度飛行試験MABE

  2. Outstanding Reviewer Awards 2024

    2024　IOP publishing

  3. Outstanding Reviewer Awards 2023

    2023/12　IOP Publishing

  4. 総長賞

    2023/03　東北大学

  5. 奨励賞

    2022/08　可視化情報学会　PSP/TSP計測とデータ駆動型解析の組合せによる非定常流れ場の解明

  6. ベストプレゼンテーション賞

    2022/08　The 13th Pacific Symposium on Flow Visualization and Image Processing　Frequency Response of Carbon-Nanotube Temperature Sensitive Paint

  7. 大学院研究奨励賞

    2021/03　自動車技術会

  8. 総長賞

    2021/03　東北大学

  9. ベストプレゼンテーション賞

    2020/09　第48回可視化情報シンポジウム　非定常PSP計測における動的モード分解のデータ取得条件の調査

  10. ベストプレゼンテーション賞

    2019/07　第47回可視化情報シンポジウム　低速風洞での流れ場計測におけるcntTSPの応答性評価

  11. 優秀発表賞（学生）

    2019/07　第51回流体力学講演会/第37回航空宇宙数値シミュレーション技術シンポジウム　カーボンナノチューブ感温塗料を利用した低速流れにおけるNACA0012翼の動的境界層遷移計測

  12. 工学部長賞

    2019/03　東北大学

Show all ︎Show 5

Papers 20

  1. Impulsive force measurement by fast response pressure-sensitive paint during shock wave passage Peer-reviewed

    T. Ikami, J. Abe, S. Tamakuma, S. Takahashi, H. Nagai

    Shock Waves　2025/03/24

    Publisher: Springer Science and Business Media LLC

    DOI： 10.1007/s00193-025-01221-9 　

    ISSN： 0938-1287

    eISSN： 1432-2153

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    Abstract The interaction between a shock wave and an object causes an impulsive force on the object that lasts for a very short time on the order of milliseconds. This study proposes impulsive force measurements using anodized aluminum pressure-sensitive paint (AA-PSP), which is an optical pressure measurement technique. The response time of AA-PSP is on the order of microseconds, indicating the potential for fast pressure drag measurements by integrating the pressure distribution on the surface. In this study, at first, the response time of the fabricated AA-PSP is measured and determined to be $$3.3~\upmu \hbox {s}$$ . A cylindrical model coated with the AA-PSP is installed at the outlet of a shock tube, and the surface pressure is measured in order to calculate the pressure drag with a time resolution of $$10~\upmu \hbox {s}$$ . The experimental results are compared with an Euler CFD simulation computed using an in-house code. The maximum pressure drag in the numerical result exceeds that in the experimental result; however, the maximum pressure drag timings are in good quantitative agreement. In addition to measuring the impulsive force, the AA-PSP results allow for the visualization of complex flow phenomena, such as diffraction and decay in the shock wave strength. This simultaneous measurement of the flow field and impulsive forces can deepen the understanding of the relationship between them.

  2. High-luminescence polymer/ceramic pressure-sensitive paint employing low-refractive-index silica nanoparticles Peer-reviewed

    Masaki Okawa, Tsubasa Ikami, Yuma Yamagishi, Kanako Watanabe, Hiroki Nagai

    Measurement Science and Technology　36　(3)　035104-035104　2025/02/11

    Publisher: IOP Publishing

    DOI： 10.1088/1361-6501/adb065 　

    ISSN： 0957-0233

    eISSN： 1361-6501

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    Abstract Pressure-sensitive paint (PSP) is an optical pressure-measurement technique that uses oxygen quenching. In unsteady PSP measurements, PSPs necessitate not only pressure sensitivity and response speed but also higher luminescence intensity. In this study, spherical silica nanoparticles are mixed into the paint to achieve a brighter luminescence. We prototype PSPs using particle size and mixing ratio as parameters and evaluate their performance. The results exhibit the luminescence intensity changes due to the low refractive index of silica; the smaller the particle size and the higher the particle ratio, the stronger the luminescence intensity. Silica-based PSPs are approximately 1.5 times brighter than titania-based PSP; which have frequently been used in previous studies. Additionally, a comprehensive performance investigation indicates that the silica-based PSP with the brightest formulation has a pressure sensitivity of 0.72 %/kPa with a response speed of 11.0 µs. These results prove that the higher luminescence is compatible with the high sensitivity and fast response using low-refractive index nanoparticles.

  3. Unsteady Propeller Wake Interference on Wing in Tractor Configuration at Low-Reynolds-Number Condition

    Masaki Okawa, Ren Nishimura, Tsubasa Ikami, Hiroki Nagai

    Journal of Aircraft　62　(1)　3-12　2025/01

    Publisher: American Institute of Aeronautics and Astronautics (AIAA)

    DOI： 10.2514/1.c037736 　

    ISSN： 0021-8669

    eISSN： 1533-3868

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    This study investigates the unsteady interaction between the propeller slipstream and NACA0012 airfoil, which causes laminar separation at a moderate angle of attack and nonlinear aerodynamic characteristics at low Reynolds numbers. The Reynolds number based on chord length was set to [Formula: see text], and the propeller advance ratio was set to [Formula: see text]. Wind-tunnel experiments were conducted, including aerodynamic force measurement and time-resolved particle image velocimetry visualization. Regarding time-averaged characteristics, the propeller installed condition exhibits a linear change in lift; reduced drag; and, consequently, an improved lift-to-drag ratio. Consistent with the aerodynamic characteristics, suppressed separation and reduction in wake deficit are confirmed in the time-averaged flowfields. Additionally, vortex formation and shedding synchronized with propeller rotation are observed in unsteady flowfields at the middle and high angles of attack. This periodic and large-scale vortex structure suggests the possibility of further improving the performance of the propeller–wing system in low Reynolds numbers.

  4. Spatiotemporal feature extraction using frequency-domain approach for flow-field data analysis Peer-reviewed

    Tsubasa Ikami, Masaki Okawa, Makoto Takagi, Yasuhiro Egami, Yu Matsuda, Hiroki Nagai

    Physics of Fluids　36　(12)　2024/12/01

    Publisher: AIP Publishing

    DOI： 10.1063/5.0233760 　

    ISSN： 1070-6631

    eISSN： 1089-7666

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    Large-scale spatiotemporal data can easily be obtained from fluid-flow measurements owing to the development of measurement instruments. Data-driven analysis methods such as Proper Orthogonal Decomposition (POD) are used to analyze large-scale data and decompose flow-field structures into spatiotemporal correlations. In addition to decomposing the data into modes, selecting and extracting dominant features automatically are necessary. This study proposes a new analysis method that simultaneously selects the dominant POD modes and their corresponding dominant frequencies by estimating the amplitude and initial phase of the POD coefficients in the frequency domain rather than directly estimating the POD coefficients. The proposed method is applied to two types of experimental flow-field data to validate the method. In the first case, the proposed method is applied for noise reduction in pressure-sensitive paint data with a low signal-to-noise ratio. The results show that the proposed method can reduce noise more accurately and naturally than the other methods. In the second case, the dominant frequencies in the flow field and their spatial structures are estimated for vortex shedding at the trailing edge of the National Advisory Committee for Aeronautics 0012 airfoil. The data are acquired using particle image velocimetry. The results show that the proposed method can decompose flow-field data containing multiple frequency components into spatial correlations, and it can be used as a tool for feature extraction in the flow field.

  5. Triple decomposition and sparse representation for noisy pressure-sensitive paint data Peer-reviewed

    Koyo Kubota, Makoto Takagi, Tsubasa Ikami, Yasuhiro Egami, Hiroki Nagai, Takahiro Kashikawa, Koichi Kimura, Yu Matsuda

    Physics of Fluids　36　(7)　2024/07/01

    Publisher: AIP Publishing

    DOI： 10.1063/5.0220866 　

    ISSN： 1070-6631

    eISSN： 1089-7666

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    Triple decomposition is a powerful analytical method for a deep understanding of the flow structure by extracting the mean value, organized coherent motion, and stochastic part from a fluctuating quantity. Here, we perform the triple decomposition of the spatial two-dimensional data, especially pressure-sensitive paint (PSP) data, since the PSP method is widely used to measure the pressure distribution on a surface in wind tunnel testing. However, the PSP data measuring near atmospheric pressure contain significant noise, and this makes it difficult to conduct the decomposition. To construct phase-averaged data representing an organized coherent motion, we propose a relatively simple method based on a multi-dimensional scaling plot of the cosine similarity between each PSP datum. Then, the stochastic part is extracted by selecting phase-averaged data with an appropriate phase angle based on the similarity between the measurement and phase-averaged data, and the PSP data are successfully decomposed. Moreover, we consider sparse optimal sensor positions, in which the data are effectively represented, based on the stochastic part as a data-driven approach. The optimal sensor positions are determined as a combinatorial optimization problem and estimated using Fujitsu computing as a service digital annealer. We reconstruct the pressure distribution from the pressure data at the optimal sensor positions using the mean value, organized coherent motion, and stochastic part obtained from the triple decomposition. The root mean square error between the pressure measured by a pressure transducer and the reconstructed pressure obtained by the proposed method is small, even when the number of modes and sensor points is small. The application of PSP measurement is expected to expand further, and the framework for calculating triple decomposition and sparse representation based on the decomposition will be useful for detailed flow analysis.

  6. cntTSP visualization technique for rotating blade surface flow at low Reynolds number

    Tsubasa Ikami, Ren Nishimura, Hiroki Nagai

    Experiments in Fluids　65　(14)　2024/01/18

    Publisher: Springer Science and Business Media LLC

    DOI： 10.1007/s00348-023-03757-x 　

    ISSN： 0723-4864

    eISSN： 1432-1114

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    Abstract Research and development of aircraft with rotating wings at low Reynolds numbers have received much attention. This study proposes using a carbon nanotube temperature-sensitive paint (cntTSP) measurement technique to visualize the surface flow of rotor blades at low Reynolds numbers. Temperature-sensitive paint (TSP) can optically measure a two-dimensional temperature field using the thermal quenching of luminophores. A carbon nanotube thin layer is used to heat the TSP layer in cntTSP measurements. For the experimental condition, the low Reynolds number at 75% of the rotor radius was 1.1 × 104, and a blade tip speed of 7.2 m/s. Temperature distributions showing a leading edge vortex (LEV) were observed in the visualization results. Furthermore, the LEV region expanded from the wing-tip side to the wing-root side at high-pitch angles. These visualization results show the applicability of the cntTSP measurement technique for investigating the surface flow field of rotor blades at low Reynolds numbers. Graphical abstract

  7. Clustering method for time-series images using quantum-inspired digital annealer technology Peer-reviewed

    Tomoki Inoue, Koyo Kubota, Tsubasa Ikami, Yasuhiro Egami, Hiroki Nagai, Takahiro Kashikawa, Koichi Kimura, Yu Matsuda

    Communications Engineering　3　(10)　2024/01/10

    Publisher: Springer Science and Business Media LLC

    DOI： 10.1038/s44172-023-00158-0 　

    eISSN： 2731-3395

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    Abstract Time-series clustering is a powerful data mining technique for time-series data in the absence of prior knowledge of the clusters. Here we propose a time-series clustering method that leverages an annealing machine, which accurately solves combinatorial optimization problems. The proposed method facilitates an even classification of time-series data into closely located clusters while maintaining robustness against outliers. We compared the proposed method with an existing standard method for clustering an online distributed dataset and found that both methods yielded comparable results. Furthermore, the proposed method was applied to a flow measurement image dataset containing noticeable noise with a signal-to-noise ratio of approximately unity. Despite a small signal variation of approximately 2%, the proposed method effectively classified the data without any overlaps among the clusters. In contrast, the clustering results of the existing methods exhibited overlapping clusters. These results indicate the effectiveness of the proposed method.

  8. Numerical Study on Unsteady Flow Field Structure over Wing within Propeller Slipstream at Low-Reynolds-Number Peer-reviewed

    Yoshikatsu FURUSAWA, Keiichi KITAMURA, Tsubasa IKAMI, Hiroki NAGAI

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN　22　49-58　2024

    Publisher: Japan Society for Aeronautical and Space Sciences

    DOI： 10.2322/tastj.22.49 　

    eISSN： 1884-0485

  9. Numerical Study on Aerodynamic Characteristics of Wing within Propeller Slipstream at Low-Reynolds-Number Peer-reviewed

    Yoshikatsu FURUSAWA, Keiichi KITAMURA, Tsubasa IKAMI, Hiroki NAGAI, Akira OYAMA

    TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES　67　(1)　12-22　2024

    Publisher: Japan Society for Aeronautical and Space Sciences

    DOI： 10.2322/tjsass.67.12 　

    ISSN： 0549-3811

    eISSN： 2189-4205

  10. On the energy harvesting technique using a fluttering PVDF film with flow-induced vibration Peer-reviewed

    Naoyuki TAKEDA, Koki SHIGE, Osamu TERASHIMA, Tsubasa IKAMI, Hiroki NAGAI, Yasufumi KONISHI, Toshihiko KOMATSUZAKI

    Advanced Experimental Mechanics　8　25-31　2023/08

    DOI： 10.11395/aem.8.0_25 　

  11. Data-driven optimal sensor placement for high-dimensional system using annealing machine Peer-reviewed

    Tomoki Inoue, Tsubasa Ikami, Yasuhiro Egami, Hiroki Nagai, Yasuo Naganuma, Koichi Kimura, Yu Matsuda

    Mechanical Systems and Signal Processing　188　109957-109957　2023/04

    Publisher: Elsevier BV

    DOI： 10.1016/j.ymssp.2022.109957 　

    ISSN： 0888-3270

  12. Evaluation of the frequency characteristics of cntTSP measurement for unsteady low-speed flow Peer-reviewed

    Tsubasa Ikami, Yasufumi Konishi, Hiroki Nagai

    Measurement Science and Technology　34　(6)　065301-065301　2023/03/01

    Publisher: IOP Publishing

    DOI： 10.1088/1361-6501/acb8d0 　

    ISSN： 0957-0233

    eISSN： 1361-6501

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    Abstract Carbon nanotube temperature-sensitive paint (cntTSP) is a fluid measurement technology that utilizes temperature-sensitive paint (TSP). It works as an optical temperature sensor, with a thin layer of carbon nanotubes to heat the TSP layer. This study investigated the frequency characteristics of cntTSP measurements in low-speed flow. The flow field on the flat plate was periodically changed by introducing intermittent local disturbances to the flat plate in a low-speed wind tunnel test. cntTSP measurement was conducted behind the local disturbance to evaluate changes in the temperature associated with periodic changes in the flow. The amplitude of the temperature change decreased approximately linearly with the frequency in a double-logarithmic graph. Moreover, the temperature amplitude at 25 Hz was 0.008 K, and it was necessary to detect a very small temperature change to evaluate high-frequency phenomena.

  13. Investigation of Formulations on Pyrene-Based Anodized-Aluminum Pressure-Sensitive Paints for Supersonic Phenomena Peer-reviewed

    Kazuma Yomo, Tsubasa Ikami, Koji Fujita, Hiroki Nagai

    Sensors　22　(12)　4430-4430　2022/06/11

    Publisher: MDPI AG

    DOI： 10.3390/s22124430 　

    eISSN： 1424-8220

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    Pressure-sensitive paint (PSP) is an optical sensor that can measure global pressure distribution by using the oxygen quenching of dye molecules. In particular, anodized aluminum pressure-sensitive paint (AA-PSP) exhibits a fast time response. AA-PSP has been used in unsteady measurements at supersonic and transonic speeds, such as on the surface of a transonic free-flying sphere or the wall of a shock tube when the shock wave passes. To capture such ultrafast phenomena, the frame rate of the camera must be sufficiently fast, and the exposure time must be sufficiently short. Therefore, it is desirable that the AA-PSP exhibits bright luminescence, high-pressure sensitivity, and fast response time. This study focused on pyrene-based AA-PSPs and investigated their characteristics, such as luminescence intensity and pressure sensitivity, at different anodization times, dipping solvents, and dipping concentrations. Furthermore, a time-response test using a shock tube was conducted on the brightest AA-PSP. Consequently, the time for a 90% rise in pressure was 2.2 μs.

  14. Structured light illumination for pressure-sensitive paint measurement under ambient light Peer-reviewed

    Yu Matsuda, Satoshi Katayama, Tsubasa Ikami, Yasuhiro Egami, Hiroki Nagai

    Review of Scientific Instruments　93　(5)　055101-055101　2022/05/01

    Publisher: AIP Publishing

    DOI： 10.1063/5.0089000 　

    ISSN： 0034-6748

    eISSN： 1089-7623

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    We propose a pressure-sensitive paint (PSP) method under ambient light based on structured light illumination. In the PSP method, pressure is obtained by measuring the variation of the emission light intensity from a PSP coating when it is illuminated by a light source. Since the extraction of the emission light from ambient light is difficult in the conventional PSP method, the existence of ambient light induces a noticeable measurement error. While spatially uniform light is used as illumination light in the conventional PSP method, structured light, the spatial intensity of which is actively controlled, is used in the proposed method. By measuring the PSP emission by varying the spatial pattern of the structured light illumination, one can eliminate ambient light, which is not synchronized with the structured light and can measure pressure without the effect of ambient light. In this study, we demonstrate the pressure measurement under ambient light using structured light with a sinusoidal wave generated by a digital mirror device. The measured pressure agrees well with the pressure measured by a pressure transducer connected to a pressure tap. The proposed method is promising under ambient light conditions.

  15. Influence of Formulations on Characteristics of Ruthenium-Based Temperature-Sensitive Paints Peer-reviewed

    Tsubasa Ikami, Koji Fujita, Hiroki Nagai

    Sensors　22　(3)　901-901　2022/01/25

    Publisher: MDPI AG

    DOI： 10.3390/s22030901 　

    eISSN： 1424-8220

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    Temperature-sensitive paint (TSP) can optically measure a global temperature distribution using a thermal quenching of dye molecules. The TSP measurement is often used in wind tunnel tests to measure the temperature and flow fields in the aerodynamic field. The measurement accuracy is affected by the characteristics of TSP, such as temperature sensitivity, pressure dependency, luminescent intensity, photostability, and surface condition. The characteristics depend on the formulation of TSP. This study investigates the characteristics of the TSP using dichlorotris (1,10-phenanthroline) ruthenium(II) hydrate (Ru-phen). We compare the characteristics of TSPs using different polymers, solvents, and dye concentrations. The TSPs using polyacrylic acid as a polymer shows linear calibration curves, high luminescent intensity, high photostability, and smooth surface. On the other hand, the TSPs using polymethyl methacrylate have nonlinear calibration curves, low luminescent intensity, strong photodegradation, and a rough surface.

  16. Data-driven approach for noise reduction in pressure-sensitive paint data based on modal expansion and time-series data at optimally placed points Peer-reviewed

    Tomoki Inoue, Yu Matsuda, Tsubasa Ikami, Taku Nonomura, Yasuhiro Egami, Hiroki Nagai

    Physics of Fluids　33　(7)　077105-077105　2021/07

    Publisher: AIP Publishing

    DOI： 10.1063/5.0049071 　

    ISSN： 1070-6631

    eISSN： 1089-7666

  17. Measurement of boundary layer transition on oscillating airfoil using cntTSP in low-speed wind tunnel Peer-reviewed

    Tsubasa Ikami, Koji Fujita, Hiroki Nagai, Daisuke Yorita

    Measurement Science and Technology　32　(7)　075301-075301　2021/04/30

    Publisher: IOP Publishing

    DOI： 10.1088/1361-6501/abe2be 　

    ISSN： 0957-0233

    eISSN： 1361-6501

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    Abstract cntTSP is a flow visualization technique that combines temperature-sensitive paint (TSP) and carbon nanotube (CNT). TSP is a sprayable temperature sensor, and CNT is used as a thin inner electric heater for the TSP. The cntTSP technique allows the visualization of the movement of the boundary layer transition on a moving airfoil. In this study, cntTSP was applied to a pitch-oscillating airfoil in a low-speed wind tunnel. Three methods were compared as methods for detecting the boundary layer transition position. The transition position was successfully evaluated using a heat transfer coefficient that was calculated by the surface temperature. Moreover, at a high-reduced frequency, the detected transition positions were different between the pitching-up and pitching-down procedure. Moreover, we observed a hysteresis loop of the transition position.

  18. Low-Reynolds-Number Flowfield of Wing with Control Surface in Propeller Slipstream Peer-reviewed

    Tsubasa Ikami, Koji Fujita, Hiroki Nagai

    Journal of Aircraft　58　(2)　228-235　2021/03

    Publisher: American Institute of Aeronautics and Astronautics (AIAA)

    DOI： 10.2514/1.c035880 　

    eISSN： 1533-3868

  19. Investigation of Data Acquisition Conditions for Dynamic Mode Decomposition in Unsteady PSP Measurement Peer-reviewed

    Tsubasa IKAMI, Koji FUJITA, Hiroki NAGAI, Yu MATSUDA, Yasuhiro EGAMI

    Transactions of the Visualization Society of Japan　41　(6)　11-20　2021

    Publisher: The Visualization Society of Japan

    DOI： 10.3154/tvsj.41.11 　

    eISSN： 1346-5260

  20. Ruthenium-based fast-responding pressure-sensitive paint for measuring small pressure fluctuation in low-speed flow field Peer-reviewed

    Y Egami, A Hasegawa, Y Matsuda, T Ikami, H Nagai

    Measurement Science and Technology　32　(2)　024003-024003　2020/11/25

    Publisher: IOP Publishing

    DOI： 10.1088/1361-6501/abb916 　

    ISSN： 0957-0233

    eISSN： 1361-6501

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    Abstract A sprayable fast-responding pressure-sensitive paint (fast-PSP) has been developed to measure time-resolved small pressure fluctuation on model surfaces. To realize PSP with fast response, high robustness, and high luminescence intensity, we have developed a novel ruthenium complex-based fast-PSP. The binder layers of the proposed fast-PSP were prepared by mixing room-temperature-vulcanizing silicone (silicone) and titanium dioxide (TiO2) particles with different sizes and their effects on the properties including the time response, pressure sensitivity, and luminescence intensity were investigated. The effects of the hydrophilic and hydrophobic surface treatments of TiO2 particle on the structure and mechanical robustness of the binder layer were also studied. The developed fast-PSP was applied to the flow field measurements behind a square cylinder and was evaluated. We have succeeded in obtaining time-series data of pressure fluctuation with high accuracy even at a mean velocity of 20 m s−1.

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Misc. 1

  1. Noise Reduction in PSP Images Using Mathematical Optimization Method

    Tomoki INOUE, Yu MATSUDA, Tsubasa IKAMI, Taku NONOMURA, Yasuhiro EGAMI, Hiroki NAGAI

    Journal of the Japan Society for Precision Engineering　87　(7)　7_610-7_613　2021/07/05

    Publisher: Japan Society for Precision Engineering

    DOI： 10.2493/jjspe.87.7_610 　

    ISSN： 0912-0289

    eISSN： 1882-675X

Presentations 180

  1. Comparison of Oscillating Frequency on Flow Around an Oscillating Airfoil at Low Reynolds Number

    Lim Gabriel Yiting, Okuizumi Hiroyuki, Okawa Masaki, Konishi Yasufumi, Ikami Tsubasa, Nagai Hiroki

    第57回流体力学講演会／第43回航空宇宙数値シミュレーション技術シンポジウム　2025/07/04

  2. 低速域でのデルタ翼ウイングロック現象の発現領域と動的不安定性の調査

    山岸悠真, 伊神翼, 永井大樹

    第57回流体力学講演会／第43回航空宇宙数値シミュレーション技術シンポジウム　2025/07/04

  3. 低レイノルズ数における平板に設けた突起まわり流れの3次元解析

    大崎歩乃花, 佐々木大輔, 川本裕樹, 岡本正人, 佐々木悠斗, 大塚光, 伊神翼

    第57回流体力学講演会／第43回航空宇宙数値シミュレーション技術シンポジウム　2025/07/04

  4. 局在表面プラズモン共鳴を利用した感圧塗料の発光強度増幅

    大川真生, 伊神翼, 渡部花奈子, 永井大樹

    第57回流体力学講演会／第43回航空宇宙数値シミュレーション技術シンポジウム　2025/07/03

  5. 導電性ポリマを用いた感温塗料の開発と評価

    伊神翼, 永井大樹

    第57回流体力学講演会／第43回航空宇宙数値シミュレーション技術シンポジウム　2025/07/03

  6. Data-Driven Approach for Combining Multiple Fields of View in Unsteady PIV Data

    Haruka Kurahashi, Tsubasa Ikami, Hiroki Nagai

    16th International Symposium on Particle Image Velocimetry　2025/06/27

  7. Investigation of Spanwise Velocity Variations along Wing Surface using Curved Laser Sheet PIV

    Ritsuki Mise, Tsubasa Ikami, Hiroki Nagai

    16th International Symposium on Particle Image Velocimetry　2025/06/26

  8. Global pressure and temperature field measurements using luminescent paint combined with machine learning

    Masaki Okawa, Jinyoung Kim, Mithat Engin, Tsubasa Ikami, Hiroki Nagai

    21st International Symposium on Flow Visualization　2025/06/23

  9. Time Series Prediction Method for PIV data Using Time Evolution Equations

    Misato Kurosawa, Tsuneto Narita, Ryuji Kokubo, Masaki Okawa, Tsubasa Ikami, Yasuhiro Egami, Hiroki Nagai, Yu Matsuda

    21st International Symposium on Flow Visualization　2025/06/22

  10. Skin friction distribution measurement on riblet using Temperature-Sensitive Paint

    Yuki Ito, Tsubasa Ikami, Mitsuru Kurita, Hiroki Nagai

    21st International Symposium on Flow Visualization　2025/06/22

  11. サバの尾びれを模倣した突起付き小型ロータの騒音評価

    佐々木悠斗, 大塚光, 得竹浩, 佐々木大輔, 伊神翼, 永井大樹

    日本航空宇宙学会第56期年会講演会　2025/04/03

  12. 進行率の異なるプロペラ後流中のNACA0012翼に対する数値解析による空力特性評価

    佐藤颯斗, 大川真生, 伊神翼, 永井大樹, 北村圭一

    日本航空宇宙学会第56期年会講演会　2025/04/03

  13. 超小型火星飛行機：膜翼を採用した収納・展開可能な超小型火星飛行機の概念検討（第二報）

    工藤惣士, 河野日香, 髙木大成, 正木拓斗, 大島草太, 伊神翼, 永井大樹, 玉置義治, 今村太郎, 金崎雅博

    日本航空宇宙学会第56期年会講演会　2025/04/04

  14. 超小型火星飛行機：超小型火星飛行機の低高度試験による機体成立性評価

    鈴木悠吾, 木村梨花, 大川真生, 伊神翼, 永井大樹

    日本航空宇宙学会第56期年会講演会　2025/04/04

  15. 高速応答感圧塗料・感温塗料同時計測による衝撃波圧力・熱流束の高精度評価

    大川真生, Jinyoung Kim, Mithat Engin, 伊神翼, 永井大樹

    2024年度衝撃波シンポジウム　2025/03/12

  16. 高速答性感温塗料の開発

    Jinyoung Kim, Mithat Engin, 大川真生, 伊神翼, 永井大樹

    2024年度衝撃波シンポジウム　2025/03/12

  17. ⾃励振動ヒートパイプの実験的研究

    加納歩輝, 川口歩夢, 伊神翼, 永井大樹

    ⽇本航空宇宙学会北部⽀部２０２５年講演会　2025/03/11

  18. Experimental Study of Flow around Oscillating Airfoil using cntTSP

    Lim Gabriel Yiting, Ikami Tsubasa, Nagai Hiroki

    2025/03/10

  19. 感温塗料を⽤いたリブレット表⾯流れ場の可視化

    伊藤夕樹, 伊神翼, 栗田充, 永井大樹

    ⽇本航空宇宙学会北部⽀部２０２５年講演会　2025/03/10

  20. High-Fidelity Rotor Design Based on Blade Element Momentum Theory

    Ritsuki Mise, Tsubasa Ikami, Hiroki Nagai

    AIAA SciTech Forum 2025　2025/01/08

  21. Silica-Based P/C-PSP Performance and Application to Wind Tunnel Experiment

    Masaki Okawa, Yuma Yamagishi, Kanako Watanabe, Tsubasa Ikami, Hiroki Nagai

    AIAA SciTech Forum 2025　2025/01/08

  22. Numerical Study on Structural Pattern Dependency of Aerodynamic Performance of Membrane Wings

    Kanta Nakai, Masahiro Kanazaki, Hiroki Nagai, Tsubasa Ikami, Yoshiharu Tamaki, Taro Imamura

    AIAA SciTech Forum 2025　2025/01/07

  23. PSPを用いた大気圏再突入カプセルの非定常圧力分布の計測

    保坂綾也, 山下大智, 大川真生, 伊神翼, 永井大樹

    令和６年度宇宙航行の力学シンポジウム　2024/12/17

  24. グラフニューラルネットワークを用いた宇宙機温度推算の高度化

    山下大智, 伊神翼, 永井大樹

    令和６年度宇宙航行の力学シンポジウム　2024/12/17

  25. Skin Friction Measurements for Rotating Blade in Low-Speed Condition by cntTSP Invited

    Tsubasa Ikami, Ren Nishimura, Hiroki Nagai

    The Conference on Theoretical and Applied Mechanics 2024　2024/11/30

  26. Development of Polymer-Ceramic Pressure-Sensitive Paint Applicable in Wind Tunnel Experiments at Very Low Speed

    Masaki Okawa, Yuma Yamagishi, Tsubasa Ikami, Kanako Watanabe, Hiroki Nagai

    The Conference on Theoretical and Applied Mechanics 2024　2024/11/30

  27. A Study on the Flow Characteristics near the Surface of Highly Acoustically Transparent Porous Materials

    N. Takeda, T. Kusano, O. Terashima, H. Nagai, Y. Konishi, T. Ikami, T. Komatsuzaki

    Twenty-first International Conference on Flow Dynamics　2024/11/19

  28. Whole Field Prediction from Sparse Sensors Using Neural Networks

    M. Takagi, T. Ikami, Y. Egami, H. Nagai, T. Kashikawa, K. Kimura, Y. Matsuda

    Twenty-first International Conference on Flow Dynamics　2024/11/19

  29. Conceptual Study on a Conventional Micro-sized Mars Airplane with Stowable and Deployable Membrane Wings

    S. Kudo, T. Takagi, H. Kono, T. Masaki, S. Oshima, M. Kanazaki, T. Ikami, H. Nagai

    Twenty-first International Conference on Flow Dynamics　2024/11/19

  30. Smoke-Visualized Wake of Quadrotor in Ground Effect

    H. Otsuka, Y. Kobayashi, S. Akaba, H. Tokutake, M. Okawa, T. Ikami, H. Nagai

    Twenty-first International Conference on Flow Dynamics　2024/11/19

  31. Plan to Study the Surface Flow of a Small Rotor Blade with a Vortex Generator

    H. Otsuka, H. Sasaki, H. Tokutake, T. Ikami, H.Nagai, H. Osaki, D. Sasaki, Y. Kawamoto

    Twenty-first International Conference on Flow Dynamics　2024/11/19

  32. Investigation on Leading Edge Vortex on Low Reynolds Number Rotor Blade by cntTSP Visualization

    T. Ikami, R. Nishimura, H. Nagai

    Twenty-first International Conference on Flow Dynamics　2024/11/20

  33. Unsteady Pressure Distribution Measurement of Hayabusa Capsule at Transonic Speeds

    R. Hosaka, D. Yamashita, T. Ikami, Y. Egami, H. Nagai

    Twenty-first International Conference on Flow Dynamics　2024/11/20

  34. Experimental Study of Unsteady Flow around Oscillating Airfoil using cntTSP

    G. Y. Lim, T. Ikami, H. Nagai

    Twenty-first International Conference on Flow Dynamics　2024/11/20

  35. Post Processing Method for PressureSensitive-Paint Data Using Machine Learning

    R. Kokubo, M. Takagi, T. Ikami, Y. Egami, H. Nagai, Y. Matsuda

    Twenty-first International Conference on Flow Dynamics　2024/11/20

  36. Development of Silica-based PSP for Unsteady Pressure Distribution Measurements in Low-Speed Flow

    Y. Yamagishi, M. Okawa, T. Ikami, K. Watanabe, H. Nagai

    Twenty-first International Conference on Flow Dynamics　2024/11/20

  37. Development of Temperature Sensitive Paint for Cryogenic Fluid Visualization

    S. Okuyama, T. Yokouchi, T. Ikami, H. Nagai

    Twenty-first International Conference on Flow Dynamics　2024/11/19

  38. Pressure Distribution Measurement on NACA0012 Airfoil using Silica-based PSP in Low-Speed Flow

    M. Okawa, Y. Yamagishi, T. Ikami, K. Watanabe, H. Nagai

    Twenty-first International Conference on Flow Dynamics　2024/11/19

  39. Numerical Study of Oscillating Heat Pipes with Different Diameter Channel

    A. Kawaguchi, Y. Sasaoka, M. Ando, A. Okamoto, T. Ikami, H. Nagai

    Twenty-first International Conference on Flow Dynamics　2024/11/19

  40. Dynamic Instability Analysis of Free Flying Objects in Transonic Regime Using Ballistic Range

    J. Kim, E. D. Leon, J. Hur, T. Ikami, K. Takahashi, T. Ogawa, M. Ahn Furudate, B. J. Lee, H. Nagai

    Twenty-first International Conference on Flow Dynamics　2024/11/19

  41. Advanced Optical Design for PIV Measurements on Curved Surfaces

    R. Mise, T. Ikami, H. Nagai

    Twenty-first International Conference on Flow Dynamics　2024/11/18

  42. Fluid-Structure Interaction Analysis of Flexible-membrane Wing at Low Reynolds Number

    K. Funada, H. Osaki, Y. Chikamoto, D. Sasaki, Y. Kawamoto, S. Takahashi, K. Fujita, H. Kurahashi, M. Okawa, T. Ikami, H. Nagai

    Twenty-first International Conference on Flow Dynamics　2024/11/18

  43. Effect of Pre-strain on Unsteady Characteristics of Flexible-membrane Wing at Low Reynolds Number

    H. Kurahashi, T. Ikami, H. Nagai

    Twenty-first International Conference on Flow Dynamics　2024/11/18

  44. Uncertainty Quantification of Spacecraft Thermal Analysis Using Transient Surrogate Model

    D. Yamashita, T. Ikami, H. Nagai

    Twenty-first International Conference on Flow Dynamics　2024/11/18

  45. Conceptual Study on an Flying Wing Type Micro-sized Mars Airplane with Canard

    R. Kimura, M. Okawa, T. Ikami, H. Nagai

    Twenty-first International Conference on Flow Dynamics　2024/11/18

  46. 展開式膜翼を用いたカナードを有する全翼機形状の超小型火星飛行機の概念検討

    木村梨花, 大川真生, 伊神翼, 永井大樹

    第68回宇宙科学技術連合講演会　2024/11/08

  47. 膜翼を採用した収納・展開可能な超小型火星飛行機の概念検討

    工藤惣士, 髙木大成, 河野日香, 正木拓斗, 大島草太, 金崎雅博, 伊神翼, 永井大樹

    第68回宇宙科学技術連合講演会　2024/11/08

  48. 火星飛行機に向けた高高度プロペラ性能評価試験（HIGHPER） - 結果速報 -

    大川真生, 三瀬律紀, 山下大智, 倉橋晴香, 伊神翼, 永井大樹, 大塚光, 得竹浩, 大山聖

    第68回宇宙科学技術連合講演会　2024/11/08

  49. 火星飛行機に向けた高高度プロペラ性能評価試験 (HIGHPER) - 結果速報 -

    大川真生, 三瀬律紀, 山下大智, 倉橋晴香, 伊神翼, 永井大樹, 大塚光, 得竹浩, 大山聖

    2024年度大気球シンポジウム　2024/10/21

  50. 非定常サロゲートモデルによる宇宙機熱解析の不確かさの定量化

    山下大智, 田中寛人, 伊神翼, 永井大樹

    第37回計算力学講演会　2024/10/19

  51. 翼素運動量理論に基づく新たな回転翼設計手法の提案と検証

    三瀬律紀, 伊神翼, 永井大樹

    第62回飛行機シンポジウム　2024/10/16

  52. 火星飛行機の高高度飛行試験(MABE-2)における空力特性の分析

    金崎雅博, 藤田昂志, 安部明雄, 伊神翼, 大山聖, 永井大樹

    第62回飛行機シンポジウム　2024/10/16

  53. 低レイノルズ数回転翼に生じる前縁剥離渦と空力特性の考察

    伊神翼, 西村練, 永井大樹

    日本流体力学会 年会2024　2024/09/25

  54. コウモリを模した柔軟膜翼の予ひずみが非定常特性に与える影響調査

    倉橋晴香, 木村梨花, 伊神翼, 永井大樹

    日本流体力学会 年会2024　2024/09/25

  55. シリカ粒子の分散制御による感圧塗料の性能向上

    大川真生, 山岸悠真, 伊神翼, 渡部花奈子, 永井大樹

    第75回コロイドおよび界面化学討論会　2024/09/20

  56. 自励振動型ヒートパイプにおける逆止弁配置の熱輸送特性に関する実験的検証

    川口歩夢, 笹岡佑全, 安藤麻紀子, 岡本篤, 伊神翼, 永井大樹

    混相流シンポジウム2024　2024/09/06

  57. Sparse representation of pressure-sensitive paint data

    Yu Matsuda, Makoto Takagi, Tsubasa Ikami, Yasuhiro Egami, Hiroki Nagai

    9th Japanese-German Joint Seminar Molecular Imaging Technology for Interdisciplinary Research　2024/08/28

  58. Pressure distribution measurement in low-speed flow using silica-based P/C-PSP

    Masaki Okawa, Yuma Yamagishi, Tsubasa Ikami, Kanako Watanabe, Hiroki Nagai

    9th Japanese-German Joint Seminar Molecular Imaging Technology for Interdisciplinary Research　2024/08/28

  59. Transient Surrogate Model using Recurrent Neural Networks for Spacecraft Thermal Analysis

    Daichi Yamashita, Hiroto Tanaka, Tsubasa Ikami, Hiroki Nagai

    2024 International Conference on Environmental Systems　2024/07/21

  60. Experimental Study of Heat Transfer Characteristics of Oscillating Heat Pipe with Different Numbers and Orientations of Check Valves

    Ayumu Kawaguchi, Yuzen Sasaoka, Makiko Ando, Atsushi Okamoto, Tsubasa Ikami, Hiroki Nagai

    2024 International Conference on Environmental Systems　2024/07/21

  61. ニューラルネットワークによる感圧塗料計測場のスパース予測

    都木誠, 伊神翼, 江上泰広, 永井大樹, 柏川貴弘, 木村浩一, 松田佑

    第52回可視化情報シンポジウム　2024/07/19

  62. シリカを用いた高輝度PSPの開発

    大川真生, 山岸悠真, 伊神翼, 渡部花奈子, 永井大樹

    第52回可視化情報シンポジウム　2024/07/19

  63. High Altitude Flight Demonstration Test Report on Mars Airplane Balloon Experiment-2 (MABE2)

    Hiroki Nagai, Akira Oyama, Koji Fujita, Masahiro Kanazaki, Atsushi Takano, Akio Abe, Katsushi Mitsutake, Hiroshi Tokutake, Tsubasa Ikami

    COSPAR 2024　2024/07/15

  64. 低レイノルズ数における柔軟膜翼の振動と流れ場の相互作用に関する研究

    倉橋晴香, 大川真生, 伊神翼, 永井大樹

    第56回流体力学講演会／第42回航空宇宙数値シミュレーション技術シンポジウム　2024/07/03

  65. 火星飛行機の高高度飛行試験(MABE-2)の熱制御系について

    永井大樹, 大山聖, 藤田昂志, 伊神翼, 金崎雅博, 安部明雄

    日本航空宇宙学会第55期年会講演会　2024/04/18

  66. 火星飛行機の高高度飛行試験(MABE-2)の航法誘導制御系について

    安部明雄, 大山聖, 永井大樹, 藤田昂志, 伊神翼, 金崎雅博

    日本航空宇宙学会第55期年会講演会　2024/04/18

  67. 火星飛行機の高高度飛行試験(MABE-2)における空力特性について

    金崎雅博, 藤田昂志, 安部明雄, 伊神翼, 大山聖, 永井大樹

    日本航空宇宙学会第55期年会講演会　2024/04/18

  68. 火星飛行機の高高度飛行試験(MABE-2)の概要

    大山聖, 永井大樹, 藤田昂志, 金崎雅博, 髙野敦, 安部明雄, 満武勝嗣, 得竹浩, 伊神翼

    日本航空宇宙学会第55期年会講演会　2024/04/18

  69. 低レイノルズ数領域でホバリングする回転翼の設計手法の提案とその評価

    三瀬律紀, 西村練, 大川真生, 伊神翼, 永井大樹

    日本航空宇宙学会北部支部2024年講演会　2024/03/15

  70. 低レイノルズ数中のプロペラ-固定翼系におけるプロペラ進行率と空力特性に関する研究

    大川真生, 伊神翼, 永井大樹

    日本航空宇宙学会北部支部2024年講演会　2024/03/15

  71. データ駆動を用いた宇宙機熱解析の非定常サロゲートモデルの提案

    山下大智, 伊神翼, 永井大樹

    日本航空宇宙学会北部支部2024年講演会　2024/03/14

  72. マイクロ秒以下の超高速応答性を持つAA-PSPの開発

    阿部淳之介, 伊神翼, 永井大樹

    2023年度衝撃波シンポジウム　2024/03/06

  73. Dynamic Behavior Measurement of New Sample Return Capsule for Deep Space Exploration using Transonic Wind Tunnel

    Rito Kawano, Tsubasa Ikami, Hiroki Nagai, Kazuhiko Yamada

    AIAA SciTech Forum　2024/01/11

  74. Surface Flow Measurement in Low-Rotational-Speed Rotor using cntTSP

    Ren Nishimura, Tsubasa Ikami, Hiroki Nagai

    AIAA SciTech Forum　2024/01/09

  75. 局在表面プラズモン共鳴を利用した超高輝度感圧塗料の設計

    大川真生, 伊神翼, 渡部花奈子, 永井大樹

    第19回学際領域における分子イメージングフォーラム　2023/12/22

  76. PSP計測データのテンソル分解を利用した低ランク近似手法の開発

    小久保琉史, 窪田航陽, 都木誠, 伊神翼, 江上泰広, 永井大樹, 松田佑

    第19回学際領域における分子イメージングフォーラム　2023/12/22

  77. cntTSPを用いた回転翼における表面摩擦応力場の計測

    伊神翼, 西村練, 永井大樹

    第19回学際領域における分子イメージングフォーラム　2023/12/22

  78. 新型⼤気圏再突⼊カプセルにおいて背⾯形状が動的特性に与える影響調査

    川野理人, 伊神翼, 高橋幸一, 永井大樹, 山田和彦

    令和5年度宇宙航行の力学シンポジウム　2023/12/11

  79. ⽕星⾶⾏機におけるプロペラ進⾏率が固定翼の空⼒性能に与える影響調査

    大川真生, 伊神翼, 永井大樹

    令和5年度宇宙航行の力学シンポジウム　2023/12/11

  80. 第２回⽕星⾶⾏機⾼⾼度⾶⾏試験(MABE2)の結果報告

    大山聖, 永井大樹, 藤田昂志, 金崎雅博, 高野敦, 安部明雄, 満武勝嗣, 得竹浩, 伊神翼

    令和5年度宇宙航行の力学シンポジウム　2023/12/11

  81. 火星飛行機の高高度飛行試験

    大山聖, 永井大樹, 藤田昂志, 金崎雅博, 高野敦, 安部明雄, 満武勝嗣, 得竹浩, 伊神翼

    日本機械学会第32回スペース・エンジニアリング・コンファレンス　2023/11/24

  82. cntTSPを用いた低レイノルズ数回転翼に生じる前縁剥離渦の可視化

    西村練, 伊神翼, 永井大樹

    第61回飛行機シンポジウム　2023/11/16

  83. 頂点効果によるロータ推力変動の評価

    赤羽峻瑛, 原大生, 大塚光, 得竹浩, 伊神翼, 永井大樹

    第61回飛行機シンポジウム　2023/11/15

  84. 同軸反転ロータの低Re数空力振動の数値解析

    坂爪竣哉, 北村圭一, 西村練, 伊神翼, 永井大樹

    第61回飛行機シンポジウム　2023/11/15

  85. Compressibility Effects around Propeller on Propeller-Wing Aerodynamic Interaction for Mars Airplane

    Y. Furusawa, K. Kitamura, T. Ikami, M. Okawa, H. Nagai

    Twentieth International Conference on Flow Dynamics　2023/11/08

  86. On the Reduction of the Flow-induced Noise Using Bio-inspired Porous Material with Low Acoustic Transmission Loss

    N. Takeda, K. Shige, O. Terashima, Y. Konishi, T. Ikami, H. Nagai, T. Komatsuzaki

    Twentieth International Conference on Flow Dynamics　2023/11/07

  87. Application of Post-Processing Method Using Digital Annealer to PSP Measurement Data

    K. Kubota, T. Inoue, T. Ikami, Y. Egami, H. Nagai, T. Kashikawa, K. Kimura, Y. Matsuda

    Twentieth International Conference on Flow Dynamics　2023/11/07

  88. Computational and Experimental Study of Unsteady Flowfield around Flexible-membrane Wing at Low Reynolds Number toward Mars Airplane

    D. Sasaki, K. Funada, K. Fujita, Y. Kawamoto, S. Takahashi, T. Ikami, H. Kurahashi, H. Nagai

    Twentieth International Conference on Flow Dynamics　2023/11/07

  89. Numerical Analysis on the Heat Transport Performance of Oscillating Heat Pipe with Different Heating Section Arrangement

    A. Kawaguchi, T. Yokouchi, M. Ando, T. Ikami, H. Nagai

    Twentieth International Conference on Flow Dynamics　2023/11/07

  90. Study on Combining Method of Time Series Flow Fields with Different Phases around Airfoil for Unsteady PIV

    H. Kurahashi, T. Ikami, H. Nagai

    Twentieth International Conference on Flow Dynamics　2023/11/07

  91. Experimental Investigation on Dynamic Instability at Transonic Speeds of Thin-aeroshell Reentry Capsule

    R. Kawano, T. Ikami, H. Nagai, K. Yamada

    Twentieth International Conference on Flow Dynamics　2023/11/07

  92. Effects of Propeller Rotation Speed on Aerodynamic Performance of Wing in Tractor-Configuration

    M. Okawa, R. Nishimura, H. Kurahashi, T. Ikami, H. Nagai

    Twentieth International Conference on Flow Dynamics　2023/11/06

  93. Sonic Boom Distribution Measurement of Supersonic Projectile in Ballistic Range

    J. Abe, T. Ogawa, T. Ikami, H. Nagai, S. Takahashi

    Twentieth International Conference on Flow Dynamics　2023/11/06

  94. Visualization of Leading Edge Vortex in Low Reynolds Number Rotor by cntTSP

    R. Nishimura, T. Ikami, H. Nagai

    Twentieth International Conference on Flow Dynamics　2023/11/06

  95. Development of Pressure Distribution Measurement Technique Using AA-PSP at Transonic Free-Flight

    Y. Takikawa, K. Takahashi, T. Ogawa, T. Ikami, H. Nagai, D. Kurihara, J. P. Gonzales, H. Sakaue

    Twentieth International Conference on Flow Dynamics　2023/11/06

  96. Proposal of Noise Reduction Method for PSP Data Using Multivariate Singular Spectrum Analysis

    M. Takagi, K. Kubota, R. Shigehara, T. Ikami, Y. Egami, H. Nagai, Y. Matsuda

    Twentieth International Conference on Flow Dynamics　2023/11/06

  97. ゴム気球を用いた火星飛行機用プロペラの高高度試験（HIGHPER）

    大川真生, 西村練, 三瀬律紀, 山下大智, 伊神翼, 大塚光, 得竹浩, 大山聖, 永井大樹

    2023年度大気球シンポジウム　2023/10/23

  98. 第２回火星飛行機高高度飛行試験(MABE2)の結果報告（速報）

    大山聖, 永井大樹, 藤田昂志, 金崎雅博, 高野敦, 安部明雄, 満武勝嗣, 得竹浩, 伊神翼

    2023年度大気球シンポジウム　2023/10/23

  99. 新型カプセルにおける遷音速動的不安定現象の形状依存性検討

    川野理人, 伊神翼, 永井大樹, 山田和彦

    第67回宇宙科学技術連合講演会　2023/10/18

  100. ドローンからの自由落下による新型再突入カプセルの空力安定性評価

    伊神翼, 川野理人, 永井大樹, 山田和彦

    第67回宇宙科学技術連合講演会　2023/10/18

  101. 火星ヘリコプタに学ぶ竹とんぼの設計手法の提案

    伊神翼, 大川真生, 西村練, 永井大樹

    第67回宇宙科学技術連合講演会　2023/10/17

  102. ゴム気球を用いた火星飛行機用プロペラの高高度試験(HIGHPER)の概要と結果速報

    大川真生, 三瀬律紀, 山下大智, 西村練, 伊神翼, 大塚光, 得竹浩, 大山聖, 永井大樹

    第67回宇宙科学技術連合講演会　2023/10/17

  103. 低レイノルズ数回転翼に生じる前縁剥離渦のcntTSPによる可視化-アスペクト比の効果-

    伊神翼, 西村練, 永井大樹

    日本流体力学会 年会2023　2023/09/20

  104. 周波数領域における POD 基底を用いた非定常 PSP データのノイズ低減

    伊神翼, 永井大樹, 松田佑, 江上泰広

    第51回可視化情報シンポジウム　2023/08/10

  105. デジタルアニーラを用いた熱流動場のモデリング手法の提案

    窪田航陽, 井上智輝, 伊神翼, 江上泰広, 永井大樹, 柏川貴弘, 木村浩一, 松田佑

    第51回可視化情報シンポジウム　2023/08/10

  106. cntTSPを用いた前進飛行するロータの非定常流れ場構造の可視化

    伊神翼, 西村練, 永井大樹

    日本航空宇宙学会第54期年会講演会　2023/04/13

  107. Unsteady Interference between Propeller Slipstream and Flow Field around NACA0012 under Low Reynolds Number Condition

    Masaki Okawa, Ren Nishimura, Tsubasa Ikami, Hiroki Nagai

    AIAA SCITECH 2023 Forum　2023/01/26

  108. Aspect Ratio Effect of Coaxial Rotor in Low Reynolds Number Condition

    Ren Nishimura, Masaki Okawa, Tsubasa Ikami, Hiroki Nagai

    AIAA SCITECH 2023 Forum　2023/01/26

  109. cntTSP を用いた低レイノルズ数における回転翼の表面温度分布の可視化

    西村練, 伊神翼, 永井大樹

    第18回学際領域における分子イメージングフォーラム　2022/12/09

  110. 低速流れにおける非定常 cntTSP 計測の周波数特性評価

    伊神翼, 小西康郁, 永井大樹

    第18回学際領域における分子イメージングフォーラム　2022/12/09

  111. 感圧塗料データの処理におけるデジタルアニーラを用いたセンサ位置選択アルゴリズムの提案

    井上智輝, 伊神翼, 江上泰広, 永井大樹, 長沼靖雄, 木村浩一, 松田佑

    第65回自動制御連合講演会　2022/11

  112. A Study of Furface Pressure Variation Induced by Planar Shock Wave Impinging on a Circular Cylinder from Various Angles

    S. Takahashi, S. Tamakuma, T. Ikami, H. Nagai

    Nineteenth International Conference on Flow Dynamics　2022/11/11

  113. Propeller-Slipstream/Main-Wing Aerodynamic Interaction for Mars Airplane, Part II

    K. Kitamura, Y. Furusawa, T. Ikami, M. Okawa, K. Fujita, H. Nagai

    Nineteenth International Conference on Flow Dynamics　2022/11/10

  114. Clean Energy Power Generation Using Flow-Induced Self-Excited Vibration of an Elastic Body

    K. Shige, N. Takeda, M. Okuno, T. Ikami, T. Kobayashi, O. Terashima, Y. Konishi, H. Nagai, T. Komatsuzaki

    Nineteenth International Conference on Flow Dynamics　2022/11/09

  115. Development and Application of Ultra-fast Response Pressure-Sensitive Paint Technology

    Hiroki Nagai, Shintaro Tamakuma, Tsubasa Ikami, Shun Takahashi

    Nineteenth International Conference on Flow Dynamics　2022/11/10

  116. Postprocessing Method for Pressure-Sensitive Paint Data Based on Mathematical Optimization

    Koyo Kubota, Tomoki Inoue, Tsubasa Ikami, Yasuhiro Egami, Daiki Nagai, Yu Matsuda

    Nineteenth International Conference on Flow Dynamics　2022/11/10

  117. Proposal of PSP Measurement Method under Ambient Light

    Rio Tanaka, Satoshi Katayama, Tsubasa Ikami, Yasuhiro Egami, Hiroki Nagai, Yu Matsuda

    Nineteenth International Conference on Flow Dynamics　2022/11/10

  118. Stall Delay in Propeller Slipstream at Low Reynolds Number

    Masaki Okawa, Ren Nishimura, Tsubasa Ikami, Hiroki Nagai

    Nineteenth International Conference on Flow Dynamics　2022/11/10

  119. Visualization of Coaxial Rotor at Low Reynolds Number Condition

    Ren Nishimura, Masaki Okawa, Tsubasa Ikami, Hiroki Nagai

    Nineteenth International Conference on Flow Dynamics　2022/11/10

  120. Effects of Oscillation of Flexible-membrane Wing on Flow Field at Low Reynolds Number

    Haruka Kurahashi, Kentaro Yamamoto, Masaki Okawa, Tsubasa Ikami, Koichi Takahashi, Hiroki Nagai

    Nineteenth International Conference on Flow Dynamics　2022/11/10

  121. Numerical Study on Propeller Scale Effect on Flow Field around Blade

    Yoshikatsu Furusawa, Keiichi Kitamura, Tsubasa Ikami, Masaki Okawa, Hiroki Nagai

    Nineteenth International Conference on Flow Dynamics　2022/11/10

  122. Visualization of Rotor Surface Flow in Hovering by cntTSP

    Tsubasa Ikami, Ren Nishimura, Hiroki Nagai

    Nineteenth International Conference on Flow Dynamics　2022/11/10

  123. 低レイノルズ数におけるプロペラ後流中の主翼周りの3次元流れ場構造

    大川真生, 伊神翼, 藤田昂志, 永井大樹

    第60回飛行機シンポジウム　2022/10/13

  124. 火星ヘリコプタを目指した同軸反転ロータの後流流れ場の解明

    西村練, 大川真生, 伊神翼, 藤田昂志, 永井大樹

    第60回飛行機シンポジウム　2022/10/13

  125. Evaluation of Frequency Characteristics of cntTSP

    Tsubasa Ikami, Yasufumi Konishi, Koichi Takahashi, Hiroki Nagai

    8th German-Japanese Joint online Seminar Molecular Imaging Technology for Interdisciplinary Research　2022/09/23

  126. Noise Suppression Method for PSP Data Based on Reduced-Order Modeling

    Tomoki Inoue, Yu Matsuda, Tsubasa Ikami, Taku Nonomura, Yasuhiro Egami, Hiroki Nagai

    The 13th Pacific Symposium on Flow Visualization and Image Processing　2022/08/08

  127. Frequency Response of Carbon-Nanotube Temperature Sensitive Paint

    Tsubasa Ikami, Koichi Takahashi, Yasufumi Konishi, Hiroki Nagai

    The 13th Pacific Symposium on Flow Visualization and Image Processing　2022/08/08

  128. 低レイノルズ数において後縁剥離を伴う翼周り流れ場とプロペラ後流の非定常干渉

    大川真生, 伊神翼, 藤田昂志, 永井大樹

    第54回流体力学講演会 / 第40回航空宇宙数値シミュレーション技術シンポジウム　2022/06/29

  129. 低レイノルズ数条件下における同軸反転ロータのアスペクト比の違いによる性能調査

    西村練, 大川真生, 伊神翼, 藤田昂志, 永井大樹

    第54回流体力学講演会 / 第40回航空宇宙数値シミュレーション技術シンポジウム　2022/06/29

  130. 低レイノルズ数における柔軟膜翼の非定常流れ場解析

    永井大樹, 山本健太郎, 伊神翼, 大川真生, 藤田昂志

    第54回流体力学講演会 / 第40回航空宇宙数値シミュレーション技術シンポジウム　2022/06/29

  131. カーボンナノチューブ感温塗料の周波数応答

    伊神翼, 高橋幸一, 小西康郁, 永井大樹

    第54回流体力学講演会 / 第40回航空宇宙数値シミュレーション技術シンポジウム　2022/06/29

  132. Unsteady Flow Field on Wing Surface in Propeller Slipstream at Low Reynolds Number

    Tsubasa Ikami, Koji Fujita, Hiroki Nagai

    AIAA AVIATION 2022 Forum　2022/06/30

  133. 火星ヘリコプタ用同軸反転ロータの後流流れ場構造の解明

    西村練, 大川真生, 伊神翼, 藤田昂志, 永井大樹

    日本航空宇宙学会北部支部2022年講演会　2022/03/18

  134. 低レイノルズ数におけるプロペラ後流中の翼面上非定常流れ場の調査

    大川真生, 伊神翼, 藤田昂志, 永井大樹

    東北学生会第52回学生員卒業研究発表講演会　2022/03/08

  135. 一様流中の旗の後流構造に関する研究

    奥野未侑, 西川礼恩, 伊神翼, 寺島修, 小西康郁, 小松﨑俊彦

    日本機械学会北陸信越支部 2022年合同講演会　2022/03/04

  136. Deployable Micro-Mars Airplane Stowed in 1U CubeSat

    Hiroto Tanaka, Tsubasa Ikami, Kohe Sone, Yudai Hamashima, Kohe Takeda, Kento Kaneko, Kazuma Yomo, Tatsuya Kobayashi, Masaki Okawa, Koji Fujita, Hiroki Nagai

    33rd International Symposium on Space Technology and Science　2022/03/02

  137. 低レイノルズ数におけるプロペラ後流の通過に同期した翼面上剥離渦の形成

    大川真生, 伊神翼, 藤田昂志, 永井大樹

    令和3年度宇宙航行の力学シンポジウム　2021/12/21

  138. 火星ヘリコプタ用同軸反転ロータの空力特性とその流れ場

    西村練, 大川真生, 伊神翼, 藤田昂志, 永井大樹

    令和3年度宇宙航行の力学シンポジウム　2021/12/21

  139. 数理最適化手法を用いた感圧塗料計測法のデータ後処理手法の開発

    窪田航陽, 井上智輝, 伊神翼, 江上泰広, 永井大樹, 松田佑

    第17回学際領域における分子イメージングフォーラム　2021/12/13

  140. cntTSP のカーボンナノチューブ層におけるポリマの影響

    伊神翼, 藤田昂志, 永井大樹

    第17回学際領域における分子イメージングフォーラム　2021/12/13

  141. 構造化光を用いた感圧塗料計測法の提案

    片山哲, 松田佑, 伊神翼, 江上泰広, 永井大樹

    第17回学際領域における分子イメージングフォーラム　2021/12/13

  142. 低レイノルズ数におけるプロペラ後流が引き起こす主翼表面上の非定常流れ場の考察

    伊神翼, 林孝亮, 藤田昂志, 永井大樹

    第 59 回飛行機シンポジウム　2021/11/30

  143. 1U のキューブサットから展開する超小型火星飛行機の概念設計及び火星までの軌道設計

    田中寛人, 伊神翼, 曽根航平, 濱島優大, 武田浩平, 金子賢人, 四方一真, 松原幸世, 小林達矢, 大川真生, 藤田昂志, 永井大樹

    第 65 回宇宙科学技術連合講演会　2021/11/12

  144. Propeller-Slipstream/Main-Wing Aerodynamic Interaction for Mars Airplane

    Keiichi Kitamura, Yoshikatsu Furusawa, Tsubasa Ikami, Koji Fujita, Hiroki Nagai

    Eighteenth International Conference on Flow Dynamics　2021/10/27

  145. Proposal of a Noise Reduction Method for Pressure-Sensitive Paint Data Using Mathematical Optimization

    Tomoki Inoue, Yu Matsuda, Tsubasa Ikami, Taku Nonomura, Yasuhiro Egami, Hiroki Nagai

    Eighteenth International Conference on Flow Dynamics　2021/10/27

  146. Understanding of Flow-Field of Pitching Airfoil at Low Reynolds Number

    Yuko Yoshizane, Tsubasa Ikami, Koji Fujita, Hiroki Nagai

    Eighteenth International Conference on Flow Dynamics　2021/10/27

  147. Unsteady Flow Field around Flexible-membrane Wing at Low Reynolds Number

    Kentaro Yamamoto, Tsubasa Ikami, Koichi Takahashi, Koji Fujita, Hiroki Nagai

    Eighteenth International Conference on Flow Dynamics　2021/10/27

  148. Dynamic Mode Decomposition Analysis of Karman Vortex Structure Measured by Unsteady PSP - Investigation of Effect of Sampling Frequency on Spatio-Temporal Features -

    Tsubasa Ikami, Koji Fujita, Hiroki Nagai, Yu Matsuda, Yasuhiro Egami

    19th International Symposium on Flow Visualization　2021/09/16

  149. 次世代再突入カプセルの低速飛行時の空力特性とその流れ場

    濱島優大, 伊神翼, 高橋幸一, 藤田昂志, 永井大樹, 山田和彦

    第53回流体力学講演会／第39回航空宇宙数値シミュレーション技術シンポジウム　2021/06/30

  150. 低レイノルズ数における柔軟膜翼の 非定常流れ場のPIV解析

    山本健太郎, 伊神翼, 高橋幸一, 藤田昂志, 永井大樹

    第53回流体力学講演会／第39回航空宇宙数値シミュレーション技術シンポジウム　2021/06/30

  151. 低レイノルズ数下でのプロペラ後流中における 主翼表面上の非定常流れ場の解明

    伊神翼, 林孝亮, 藤田昂志, 永井大樹

    第53回流体力学講演会／第39回航空宇宙数値シミュレーション技術シンポジウム　2021/06/30

  152. 低速域における次世代再突入カプセル表面の流れ場の可視化

    濱島優大, 伊神翼, 高橋幸一, 藤田昂志, 永井大樹, 山田和彦

    日本航空宇宙学会北部支部２０２１年講演会　2021/03/18

  153. 低レイノルズ数における石井翼型の空力特性に対する圧縮性の影響

    吉實優子, 伊神翼, 藤田昂志, 永井大樹

    日本航空宇宙学会北部支部２０２１年講演会　2021/03/18

  154. Response Evaluation of cntTSP for Detection of Dynamic Boundary Layer Transition in Low-Speed Wind Tunnel

    Tsubasa Ikami, Koji Fujita, Hiroki Nagai, Daisuke Yorita

    AIAA Scitech 2021 Forum　2021/01/12

  155. 深宇宙からのサンプルリターンに向けた次世代再突入カプセルの低速域における空力特性

    濱島優大, 伊神翼, 高橋幸一, 藤田昂志, 永井大樹, 山田和彦

    令和2年度宇宙航行の力学シンポジウム　2020/12/14

  156. 火星希薄大気を模擬した低レイノルズ数領域におけるピッチ振動する翼の空力特性

    吉實優子, 伊神翼, 藤田昂志, 永井大樹

    令和2年度宇宙航行の力学シンポジウム　2020/12/14

  157. 非定常cntTSP計測における迎角振動翼での境界層遷移位置評価手法の比較

    伊神翼, 藤田昂志, 永井大樹

    第58回飛行機シンポジウム　2020/11/25

  158. 非定常PSP 計測でのデータ取得条件が動的モード分解に与える影響の調査

    伊神翼, 藤田昂志, 永井大樹, 松田佑, 江上泰広

    第16 回学際領域における分子イメージングフォーラム　2020/11/19

  159. ピッチスイープする翼を用いたcntTSP の時間応答性の調査

    伊神翼, 藤田昂志, 永井大樹

    第16 回学際領域における分子イメージングフォーラム　2020/11/19

  160. Development of PSP Measurement Technique Using Structured Illumination

    Satoshi Katayama, Yu Matsuda, Yasuhiro Egami, Tsubasa Ikami, Hiroki Nagai

    Seventeenth International Conference on Flow Dynamics　2020/10/28

  161. Evaluation of Boundary Layer Transition Positions on Pitching Airfoil for Unsteady cntTSP Measurement

    Tsubasa Ikami, Koji Fujita, Hiroki Nagai

    Seventeenth International Conference on Flow Dynamics　2020/10/28

  162. ルテニウム型高速応答感圧塗料を用いた低速流れ場の微小圧力変動計測

    江上泰広, 長谷川敦也, 松田佑, 伊神翼, 永井大樹

    流体力学講演会／航空宇宙数値シミュレーション技術シンポジウム2020オンライン　2020/09/28

  163. 非定常PSP計測における動的モード分解のデータ取得条件の調査

    伊神翼, 藤田昂志, 永井大樹, 松田佑, 山崎遊野, 江上泰広

    第48回可視化情報シンポジウム　2020/09/24

  164. 非定常PSP計測における固有直交分解と動的モード分解のノイズ除去効果

    森重聡一郎, 山崎遊野, 松田佑, 伊神翼, 永井大樹, 江上泰広

    第48回可視化情報シンポジウム　2020/09/24

  165. Measurement of Boundary Layer Transition on Oscillating Airfoil using cntTSP in Low-Speed Wind Tunnel

    Tsubasa Ikami, Koji Fujita, Hiroki Nagai, Daisuke Yorita

    AIAA Scitech 2020 Forum　2020/01/06

  166. cntTSPを用いたピッチ振動翼上の非定常流れ場構造の調査

    伊神翼, 藤田昂志, 永井大樹, 依田大輔, Christian Klein

    第15回学際領域における分子イメージングフォーラム　2019/12/12

  167. Investigation of a Time Response of cntTSP Sensor for a Dynamic Visualization of the Laminar-to-turbulent Boundary Layer Transition

    Daisuke Yorita, Jonathan Lemarechal, Christian Klein, Koji Fujita, Tsubasa Ikami, Hiroki Nagai

    Sixteenth International Conference on Flow Dynamics　2019/11/07

  168. Validation of Fast-Pressure-Sensitive Paint for Measuring Small Pressure Fluctuation

    Yasuhiro Egami, Yuya Yamazaki, Yu Matsuda, Tsubasa Ikami, Hiroki Nagai

    Sixteenth International Conference on Flow Dynamics　2019/11/07

  169. PIV Measurement of Oscillating Airfoil at Low Reynold Number

    Tsubasa Ikami, Koji Fujita, Hiroki Nagai

    Sixteenth International Conference on Flow Dynamics　2019/11/06

  170. 低速流れでの動的な境界層遷移計測におけるcntTSPの時間応答性の調査

    伊神翼, 藤田昂志, 永井大樹, 依田大輔, Christian Klein

    第57回飛行機シンポジウム　2019/10/16

  171. Carbon Nanotube TSP Technique in a Pitch-Sweep Wind Tunnel Test

    Daisuke Yorita, Jonathan Lemarechal, Christian Klein, Tsubasa Ikami, Koji Fujita, Hiroki Nagai

    7th Japanese-German Joint Seminar -Molecular Imaging Technology for Interdisciplinary Research-　2019/09/17

  172. Evaluation of cntTSP for Boundary Layer Transition Detection in Low Speed Flow

    Tsubasa Ikami, Koji Fujita, Hiroki Nagai, Daisuke Yorita, Christian Klein

    7th Japanese-German Joint Seminar -Molecular Imaging Technology for Interdisciplinary Research-　2019/09/17

  173. 低速風洞での流れ場計測におけるcntTSPの応答性評価

    伊神翼, 藤田昂志, 永井大樹, 依田大輔, Christian Klein

    第47回可視化情報シンポジウム　2019/07/26

  174. カーボンナノチューブ感温塗料を利用した低速流れにおけるNACA0012翼の動的境界層遷移計測

    伊神翼, 藤田昂志, 永井大樹, 依田大輔, Christian Klein

    第51回流体力学講演会　2019/07/02

  175. cntTSPを用いた迎角スイープ中の動的な境界層遷移計測

    伊神翼, 依田大輔, Christian Klein, 藤田昂志, 永井大樹

    第14回学際領域における分子イメージングフォーラム　2019/03/08

  176. Flow Field on Wing Surface with Control Surface in Propeller Slipstream at Low Reynolds Number

    Tsubasa Ikami, Kensuke Kanou, Koichi Takahashi, Koji Fujita, Hiroki Nagai

    AIAA Scitech 2019 Forum　2019/01/11

  177. プロペラ後流中にある舵面を持つ翼の流れ場構造

    伊神翼, 藤田昂志, 永井大樹

    第56回飛行機シンポジウム　2018/11/16

  178. Investigation on Carbon Nanotube TSP for Dynamic Visualization of Boundary-layer Transition

    Daisuke Yorita, Jonathan Lemarechal, Christian Klein, Koji Fujita, Tsubasa Ikami, Hiroki Nagai

    Fifteenth International Conference on Flow Dynamics　2018/11/08

  179. Research and Development Co-Axial Rotor to Realize Mars Helicopter

    Hiroki Nagai, Kensuke Kanou, Tsubasa Ikami, Koji Fuijita, Kouichi Yonezawa

    Fifteenth International Conference on Flow Dynamics　2018/11/08

  180. Visualization of Wing Surface Flow in Propeller Slipstream at Low Reynolds Number

    Tsubasa Ikami, Kensuke Kanou, Koji Fujita, Hiroki Nagai

    Fifteenth International Conference on Flow Dynamics　2018/11/08

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Research Projects 9

  1. A Challenge to Measurement of Low Reynolds Number Unsteady Aerodynamics Using Localized Plasmon Resonance

    Offer Organization: Japan Society for the Promotion of Science

    System: Grants-in-Aid for Scientific Research

    Category: Grant-in-Aid for Scientific Research (B)

    Institution: Tohoku University

    2025/04 - 2028/03

  2. Unsteady Flow Field Measurement on Moving Airfoil by Heater-integrated TSP

    Offer Organization: Japan Society for the Promotion of Science

    System: Grants-in-Aid for Scientific Research

    Category: Grant-in-Aid for Early-Career Scientists

    Institution: Tohoku University

    2024/04 - 2027/03

  3. ヘテロダイン検波を援用した非定常カーボンナノチューブ感温塗料計測の高精度化

    Offer Organization: 公益財団法人 マツダ財団

    System: 第39回（2023年度）マツダ研究助成－科学技術振興関係－

    Institution: 東北大学流体科学研究所

    2024/04 - 2026/03

  4. 風洞試験と数値計算による翅脈を持つ柔軟膜翼のデジタルツイン研究開発

    伊神 翼, 金崎 雅博

    Offer Organization: 東北大学流体科学研究所

    System: 令和６年度東北大学流体科学研究所一般公募共同研究

    Institution: 東北大学流体科学研究所

    2024/04 - 2025/03

  5. 突起を持つロータブレード周りの低レイノルズ数における流れ構造の解明

    大塚 光, 伊神 翼

    Offer Organization: 東北大学流体科学研究所

    System: 令和６年度東北大学流体科学研究所一般公募共同研究

    Institution: 東北大学流体科学研究所

    2024/04 - 2025/03

  6. 流体計測のイノベーション - 超高輝度感圧塗料で拓く新しい圧力可視 化・計測 -

    伊神 翼, 渡部花奈子, 永井大樹

    Offer Organization: 国立研究開発法人宇宙航空研究開発機構 航空技術部門

    System: JAXA 航空イノベーションチャレンジ

    Institution: 東北大学流体科学研究所

    2024/06 - 2025/02

  7. 導電性ポリマ型TSPによる回転翼ブレード表面の非定常流れ場評価手法の創出

    伊神 翼

    Offer Organization: 日本学術振興会

    System: 科学研究費助成事業

    Category: 特別研究員奨励費

    Institution: 東北大学

    2022/04/22 - 2024/03/31

  8. Study on ground effect on multirotor unmanned aerial vehicles considering symmetry rotor position

    2023/04 - 2024/03

  9. Evaluation on ground effect on a quad rotor UAV using symmetry reflecting walls

    2022/04 - 2023/03

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Teaching Experience 1

  1. 機械知能・航空実験I　東北大学

Social Activities 1

  1. 飛行機はどうして“飛ぶの？” 〜火星飛行機と「ながれ」の科学〜

    夏休み大学探検

    2023/08/01 -

Media Coverage 1

  1. サイエンスバトル 理論武闘

    日本テレビ　サンバリュ

    2022/01

    Type: TV or radio program

Other 1

  1. 第43回可視化フロンティア「PSP/TSP講習会2023」TSP基礎・発展

    More details Close

    可視化情報学会が主催する第43回可視化フロンティア「PSP/TSP講習会2023」において，「TSP基礎・発展」という題目で講師を務めた．