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82 results on '"Hirota, Mitsutomo"'

5. Effects of injection and main flow conditions on supersonic turbulent mixing structure

Author

Takahashi, Hidemi, Masuya, Goro, and Hirota, Mitsutomo

Subjects
Turbulence -- Research, Aerodynamics, Supersonic -- Research, Aerospace and defense industries, Business
Abstract

The effects of injection and main flow conditions on the turbulent structure produced by a gaseous sonic transverse injection into a supersonic airstream were investigated. The turbulent structure inherent in the mixing flowfield was characterized by the single-time two-point spatial correlations based on the concentration fluctuation and measured with acetone planar laser-induced fluorescence. Results revealed that the most intensively fluctuating region appeared on the 50%-averaged-concentration track, irrespective of the injection conditions. The highly correlated region, which indicates an organized large-scale structure, appeared as a tilting ellipse in the lower-compressibility cases and an ellipse almost parallel to the streamline in the higher-compressibility cases. These differences in structure result in the difference of the averaged jet width. The injection with the higher-compressibility condition showed more stable structures and slower development in the size due to suppression of the instability growth. The structure was likely to be stretched toward the averaged-velocity direction as the main flow Mach number increased. Increasing the velocity difference between the jet and main flow caused the large-scale eddies to appear more frequently. DOI: 10.2514/1.J050355

Published
2010

6. Scalar spatial correlations in a supersonic mixing flowfield

Author

Takahashi, Hidemi, Oso, Hiroki, Kouchi, Toshinori, Masuya, Goro, and Hirota, Mitsutomo

Subjects
Aerodynamics, Supersonic -- Research, Aerospace and defense industries, Business
Abstract

Single-time two-point spatial correlations of injectant concentrations in the supersonic mixing flowfield produced by a sonic transverse injection of air into a Much 2.0 supersonic airstream were investigated using acetone planar laser-induced fluorescence data. Side-view and end-view contour maps were obtained in several planes to characterize the turbulent structure and three-dimensionality of the mixing flowfield. The correlation maps indicated an organized large-scale structure in the upper region of the jet. The side-view correlation maps revealed that the shape of the large dominating structure was elliptic and that its major axis turned from backward-leaning to forward-leaning as the reference point of correlation moved downstream. The end-view correlation maps showed that the instantaneous jet plume appeared by turns either in the top or in the lower sides of the time-averaged injectant plume in each cross section. DOI: 10.2514/1.44684

Published
2010

7. Quantitative imaging of injectant mole fraction and density in supersonic mixing

Author

Takahashi, Hidemi, Ikegami, Shuzo, Oso, Hiroki, Masuya, Goro, and Hirota, Mitsutomo

Subjects
Aerospace engineering -- Analysis, Fluorescence -- Analysis, Aerospace and defense industries, Business
Abstract

The fluorescence ratio technique for processing planar laser-induced fluorescence data was generalized for quantitative imaging of the injectant mole fraction and extended to quantify the density distributions in a nonreacting supersonic mixing flowfield. The original fluorescence ratio approach was first developed by Hartfield et al. (Hartfield, R. J., Jr., Abbitt, J. D., III, and McDaniel, J. C., 'Injectant Mole Fraction Imaging in Compressible Mixing Flow Using Planar Laser-Induced Iodine Fluorescence,' Optics Letters, Vol. 1, No. 16, Aug. 1989, pp. 850-852.) for tests in a special closed-loop wind tunnel to eliminate the effects of thermodynamic property variations on planar laser-induced fluorescence signals in compressible flowfields. This approach provided us a quantitative means of planar mole-fraction measurement; however, it implicitly assumed that the tracer molecules were seeded at the same fraction in both the main and the secondary flows. In the present study, we generalized the Hartfield et al. method by considering differences in the tracer-seeding rates for obtaining planar images of mole fraction and density. Experimental validation of the new method was carried out in a mixing flowfield formed by sonic transverse injection into a Mach 1.9 supersonic airstream. The injectant mole-fraction distribution obtained from planar laser- induced fluorescence data processed by our new approach showed better agreement with the gas-sampling data than one based on the Hartfield et al. method. The density distribution was verified by comparison with the theoretical density ratio across the oblique shock wave. DOI: 10.2514/1.37783

Published
2008

8. Correction method for particle velocimetry data based on the Stokes drag law

Author

Koike, Shunsuke, Takahashi, Hidemi, Tanaka, Koichi, Hirota, Mitsutomo, Takita, Kenichi, and Masuya, Goro

Subjects
Shock waves -- Properties, Speed -- Measurement, Aerospace and defense industries, Business
Abstract

A correction method based on the Stokes drag law was developed for flow velocimetry using tracer particles. The present method can be used to calculate the corrected velocity from the measured velocity and its spatial gradient without the need to solve the whole flowfield. Velocity measurement was conducted for sonic transverse injection into Mach 1.8 flow using particle image velocimetry. The correction method was applied to the velocity field obtained from the particle image velocimetry data. The corrected data showed the positions and shapes of the shock waves in the measurement region more clearly. The corrected peak velocity downstream of the shock waves became closer to the theoretical values. The jet streamlines calculated from the corrected and original particle image velocimetry data were compared. The streamlines from the corrected data went lower than those from the original data.

Published
2007

10. Influence of injection nozzle geometries on mixing characteristics of jet in supersonic crossflow

Author

SRISHA, M. V. Rao, SEGUCHI, Takahiro, HATANAKA, Kazuaki, HIROTA, Mitsutomo, and SAITO, Tsutomu

Subjects
Jet in Supersonic Crossflow, Mixing, Scramjet Engine, Nozzle Geometry, Hot Wire Anemometer
Abstract

2019年度衝撃波シンポジウム (2020年3月4日-6日. 神戸大学 海事科学研究科（深江キャンパス)）神戸市, 兵庫県, Symposium on Shock Waves in Japan, FY2019 (March 3-4, 2020. Kobe University), Kobe, Hyogo Japan, 2019年度衝撃波シンポジウムは、新型コロナウイルスの感染拡大防止のため開催中止, 資料番号: SA6000148127, レポート番号: P-13[若]

Published
2020

11. Density Measurement by BOS method when Oblique Shock Wave is Added to Compressible Turbulent Mixing Layer

Author

ITO, Mizuki, HATANAKA, Kazuaki, HIROTA, Mitsutomo, and SAITO, Tsutomu

Subjects
Shock Wave, BOS, Compressible Mixing Layer
Abstract

2019年度衝撃波シンポジウム (2020年3月4日-6日. 神戸大学 海事科学研究科（深江キャンパス)）神戸市, 兵庫県, Symposium on Shock Waves in Japan, FY2019 (March 3-4, 2020. Kobe University), Kobe, Hyogo Japan, 2019年度衝撃波シンポジウムは、新型コロナウイルスの感染拡大防止のため開催中止, 資料番号: SA6000148125, レポート番号: P-11[若]

Published
2020

12. Research about Transition of Reflection form in Oblique Reflection of Plane Shock Wave used Wedge

Author

Kumagai, Yoshiki, Hatanaka, Kazuaki, Hirota, Mitsutomo, and Saito, Tsutomu

Subjects
Boundary Layer, Triple Point, Shock Wave Reflection, Transition delay
Abstract

平成30年度衝撃波シンポジウム (2019年3月5日-7日. 横浜国立大学経済・経営学部講義棟1号館 ）横浜市, 神奈川県, Symposium on Shock Waves in Japan, FY2018 (March 5-7, 2019. Yokohama National University), Yokohama, Kanagawa, 資料番号: SA6000134104, レポート番号: P-01 [若]

Published
2019

13. Influence of Fuel Jet Nozzle Geometry on Mixing in Supersonic Crossflow

Author

Rao, Srisha M. V., Seguchi, Takahiro, Hatanaka, Kazuaki, Hirota, Mitsutomo, and Saito, Tsutomu

Subjects
Jet in Supersonic Crossflow, Mixing, Scramjet Engine, Nozzle Geometry, Hot Wire Anemometer
Abstract

平成30年度衝撃波シンポジウム (2019年3月5日-7日. 横浜国立大学経済・経営学部講義棟1号館 ）横浜市, 神奈川県, Symposium on Shock Waves in Japan, FY2018 (March 5-7, 2019. Yokohama National University), Yokohama, Kanagawa, 資料番号: SA6000134109, レポート番号: P-06 [若]

Published
2019

16. Behavior of triple point immediately after transition of reflection form of oblique shock wave

Author

Machida, Keisuke, Hatanaka, Kazuaki, Hirota, Mitsutomo, and Saito, Tsutomu

Subjects
Shock Wave, Transition, Boundary Layer, Triple Point, Reflection
Abstract

平成29年度衝撃波シンポジウム (2018年3月7日-9日. 東北大学片平さくらホール ）仙台市, 宮城県, (2018年3月7日-9日. 宇宙航空研究開発機構角田宇宙センター ）角田市, 宮城県, Symposium on Shock Waves in Japan, FY2017 (March 7-9, 2018. Sakura Hall), Sendai, Miyagi, (March 7-9, 2018. Kakuda Space Center, Japan Aerospace Exploration Agency (JAXA)(KSPC)), Kakuda, Miyagi, 資料番号: SA6000119131, レポート番号: P-01【若】

Published
2018

17. Investigations on Mixing Characteristic Changes of Compressible Turbulent Mixing Layer in a Confined Duct Interacting with Shock Waves

Author

Ikeda, Taiki, Hatanaka, Kazuaki, Hirota, Mitsutomo, Saito, Tsutomu, and Rao, Srisha M. V.

Subjects
Shock Wave, Mixing Characteristics, Compressible Turbulent Mixing Layer, Hot-Wire Velocimetry
Abstract

平成29年度衝撃波シンポジウム (2018年3月7日-9日. 東北大学片平さくらホール ）仙台市, 宮城県, (2018年3月7日-9日. 宇宙航空研究開発機構角田宇宙センター ）角田市, 宮城県, Symposium on Shock Waves in Japan, FY2017 (March 7-9, 2018. Sakura Hall), Sendai, Miyagi, (March 7-9, 2018. Kakuda Space Center, Japan Aerospace Exploration Agency (JAXA)(KSPC)), Kakuda, Miyagi, 資料番号: SA6000119011, レポート番号: 1A3-1【若】

Published
2018

18. Influence of Nozzle Geometry on Mixing Effect of Gas Injecting Supersonic Flow

Author

Seguchi, Takahiro, Ikeda, Taiki, Hatanaka, Kazuaki, Hirota, Mitsutomo, and Saito, Tsutomu

Subjects
Planar Laser Induced Fluorescence, Mixing, Scramjet Engine, Jet Flow, Nozzle Geometry
Abstract

平成29年度衝撃波シンポジウム (2018年3月7日-9日. 東北大学片平さくらホール ）仙台市, 宮城県, (2018年3月7日-9日. 宇宙航空研究開発機構角田宇宙センター ）角田市, 宮城県, Symposium on Shock Waves in Japan, FY2017 (March 7-9, 2018. Sakura Hall), Sendai, Miyagi, (March 7-9, 2018. Kakuda Space Center, Japan Aerospace Exploration Agency (JAXA)(KSPC)), Kakuda, Miyagi, 資料番号: SA6000119137, レポート番号: P-07【若】

Published
2018

19. Numerical studies on reflection form of weak shock wave propagating over wedges

Author

Hatanaka, Kazuaki, Wang, Haoyi, Hirota, Mitsutomo, Saito, Tsutomu, and Takayama, Kazuyoshi

Subjects
Oblique Shock, Numerical Study, Shock Wave
Abstract

平成28年度衝撃波シンポジウム (2017年3月8日-10日. ヴェルクよこすか 横須賀市立勤労福祉会館）横須賀市, 神奈川県, Symposium on Shock Waves in Japan, FY2016 (March 8-10, 2017. Werk Yokosuka), Kanagawa, Japan, 資料番号: SA6000084036, レポート番号: 1C2-1

Published
2017

20. Investigations of Mixing Characteristic of Compressible Turbulent Mixing Layer in a Rectangular Duct by Using Hot-Wire Anemometer

Author

Ikeda, Taiki, Fuse, Ryosuke, Hatanaka, Kazuaki, Hirota, Mitsutomo, Saito, Tsutomu, and Rao, Srisha M.V.

Subjects
Mixing Measurement, Calibration, Hot-Wire Anemometer, Compressible Turbulent Mixing Layer
Abstract

平成28年度衝撃波シンポジウム (2017年3月8日-10日. ヴェルクよこすか 横須賀市立勤労福祉会館）横須賀市, 神奈川県, Symposium on Shock Waves in Japan, FY2016 (March 8-10, 2017. Werk Yokosuka), Kanagawa, Japan, 資料番号: SA6000084017, レポート番号: 1A4-3【若】

Published
2017

21. Numerical and Experimental Investigations of Fluidic Thrust Vectoring

Author

LI, Li, HIROTA, Mitsutomo, and SAITO, Tsutomu

Subjects
Secondary jet, 538.3, Converging-diverging nozzle, Fluid thrust vectoring, CFD
Abstract

Fluidic thrust vectoring (FTV), an ability of air vehicles to manipulate the nozzle flow deflect their longitudinal axis, can satisfy the modern aircraft requirements dramatically. Numerical and experimental studies of FTV are performed with a nozzle pressure ratio (NPR) of 4–10, a secondary pressure ratio (SPR) of 1, 2 or 3, and two different secondary jet locations. Numerical simulations of the nozzle flow are done with solving the Navier-Stokes equations, and the input parameters are set to match the experimental conditions. The thrust pitching moment and the thrust pitching angle are determined to evaluate the FTV performance., 特集 : Special Section for the Papers Presented at the Symposium on Mechanical Engineering, Industrial Engineering, and Robotics held at Noboribetsu, Hokkaido, Japan on 11 - 12 January 2012

Published
2013

27. Influence of Nozzle Geometry on Mixing Effect of Supersonic Free Jets

Author

Asano, Shingo, Rao, Srisha M.V., Hirota, Mitsutomo, and Saito, Tsutomu

Subjects
Planar Laser Induced Fluorescence, Supersonic Jet Flow, ESTS Nozzle, Boundary Layer, Streamwise Vortex, Compressible Mixing Layer
Abstract

平成27年度衝撃波シンポジウム (2016年3月7日-9日. 熊本大学 黒髪南地区）熊本市, 熊本県, Symposium on Shock Waves in Japan, FY2015 (March 7-9, 2016. Kumamoto University), Kurokami Chuo-ku, Kumamoto, Japan, 資料番号: SA6000049058, レポート番号: 2A1-4【若】

Published
2016

28. Measurement of Free Jet Turbulent Flow with Hot-Wire Anemometer

Author

Ikeda, Taiki, Asano, Shingo, Rao, Srisha M.V., Hirota, Mitsutomo, Saito, Tsutomu, and Takagi, Shohei

Subjects
Turbulent Mixing, Turbulent Flow, Nozzle Geometry, Hot-Wire Anemometer, Supersonic Free Jet
Abstract

平成27年度衝撃波シンポジウム (2016年3月7日-9日. 熊本大学 黒髪南地区）熊本市, 熊本県, Symposium on Shock Waves in Japan, FY2015 (March 7-9, 2016. Kumamoto University), Kurokami Chuo-ku, Kumamoto, Japan, 資料番号: SA6000049059, レポート番号: 2A1-5【若】

Published
2016

29. Experimental and Numerical Studies of Supersonic Free Jets from Complex Geometry Nozzles

Author

Asano, Shigeo, Rao, Srisha, Saito, Tsutomu, and Hirota, Mitsutomo

Subjects
Supersonic Jet Flow, ESTS Nozzle, Copressible Mixing Layer, Boundary Layer, Streamwise Vortex, Planar laser Induced Fluorescence
Abstract

平成26年度衝撃波シンポジウム (2015年3月9日-11日. 群馬県伊香保温泉 ホテル天坊）渋川市, 群馬県, Symposium on Shock Waves in Japan, FY2014 (March 9-11, 2015. Hotel Tenbo), Shibukawa, Gunma, Japan, 資料番号: SA6000038019, レポート番号: 1B1-4（若）

Published
2015

30. Performance of shock tunnel using a diaphragmless shock tube and application for study of supersonic flow

Author

Hirama, Yoshiki, Yano, Toshiaki, Kaga, Kentaro, Hirota, Mitsutomo, and Saito, Tsutomu

Subjects
Detached Shock Wave, Shock Tunnel, Nozzle Flow
Abstract

平成26年度衝撃波シンポジウム (2015年3月9日-11日. 群馬県伊香保温泉 ホテル天坊）渋川市, 群馬県, Symposium on Shock Waves in Japan, FY2014 (March 9-11, 2015. Hotel Tenbo), Shibukawa, Gunma, Japan, 資料番号: SA6000038070, レポート番号: 2C1-4（若）

Published
2015

31. ダクト内圧縮性混合層の研究

Author

Rao, Srisha M. V., Asano, Shingo, Hirota, Mitsutomo, and Saito, Tsutomu

Subjects
Pressure Gradient Effects, Compressible Mixing Layer, Shocks
Abstract

平成26年度衝撃波シンポジウム (2015年3月9日-11日. 群馬県伊香保温泉 ホテル天坊）渋川市, 群馬県, Symposium on Shock Waves in Japan, FY2014 (March 9-11, 2015. Hotel Tenbo), Shibukawa, Gunma, Japan, 資料番号: SA6000038014, レポート番号: 1A3-2（若）

Published
2015

33. Investigations on Compressible Mixing Layers in Confined Ducts

Author

RAO, Srisha M.V., ASANO, Shingo, IMANI, Ismah, HIROTA, Mitsutomo, and SAITO, Tsutomu

Abstract

The lacuna in addressing the fundamentals of compressible mixing layers subjected to pressure gradients in confined ducts motivated the current investigations. Studies are conducted on a canonical compressible mixing layer established between M1=2.0 and M2=1.5 flows within a suction type supersonic wind tunnel. Pressure gradients are imposed on the mixing layer by placing appropriate inserts on the test section walls. High speed schlieren visualizations and static pressure measurements are performed. Interesting shock-shear layer interactions are observed in the test section.

Published
2015

34. Experimental Study on the Ignition Delay of Hybrid Rockets

Author

Nakata, Daisuke, Muhammad, Hafeez, Tanatsugu, Nobuhiro, Higashino, Kazuyuki, and Hirota, Mitsutomo

Subjects
Ignition Delay, Hybrid Rocket, Flame Spread Velocity
Abstract

平成25年度宇宙輸送シンポジウム（2014年1月16日-17日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県, Space Transportation Symposium FY2013 (January 16-17, 2014. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000016044, レポート番号: STCP-2013-044

Published
2014

35. 2014 Annual Report on activity of the working group on ignition and combustion at high pressures with a shared apparatus for microgravity experiments

Author

Nomura, Hiroshi, Mikami, Masato, Moriue, Osamu, Tsue, Mitsuhiro, Yamasaki, Hiroshi, Segawa, Daisuke, Tanabe, Mitshaki, Takahashi, Shuhei, Hashimoto, Nozomu, Imamura, Osamu, Okai, Keiichi, Hirota, Mitsutomo, Suganuma, Yusuke, and Kikuchi, Masao

Subjects
Sounding rocket project, Combustion, Microgravity, Cool flame, Ignition, Droplet array
Abstract

第29回宇宙環境利用シンポジウム (2015年1月24日-25日. 宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)), 相模原市, 神奈川県, Space Utilization Research (January 24-25, 2015. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 著者人数: 14名, 資料番号: SA6000035011, レポート番号: ISAS-SUR29-S06

Published
2015

36. Activity Report of Research Team for Investigation on Combustion Mechanisms in Acoustic Fields

Author

Tanabe, Mitsuaki, Okai, Keiichi, Hirota, Mitsutomo, Moriue, Osamu, Klinkov, Konstantin, and Eigenbrod, Christian

Subjects
Space Utilization, Convection, Acoustics, Combustion
Abstract

第26回宇宙利用シンポジウム(2010年1月25日-26日, 宇宙航空研究開発機構宇宙科学研究本部相模原キャンパス), The Twenty-sixth Space Utilization Symposium (January 25-26, 2010: ISAS/JAXA Sagamihara, Japan), The research team work for the near-future microgravity experiments on the combustion experiment in acoustic field, part of which requires long-term microgravity conditions. The current activity is focused on the development of experimental devices for the shared apparatus that is under development in cooperation with "the research team on ignition and combustion at high pressures with a shared apparatus for microgravity experiments". A feasible schlieren optics arrangement for the apparatus is presented as well as concise result on the combustion experiments in acoustic field., 形態: カラー図版あり, 共催: 日本学術会議, Physical characteristics: Original contains color illustrations, joint hosting: The Science Council of Japan, 資料番号: AA0064730023

Published
2010

37. Numerical and Experimental Investigations of Fluidic Thrust Vectoring

Author

LI Li, HIROTA Mitsutomo, SAITO Tsutomu, LI Li, HIROTA Mitsutomo, and SAITO Tsutomu

Abstract

Fluidic thrust vectoring (FTV), an ability of air vehicles to manipulate the nozzle flow deflect their longitudinal axis, can satisfy the modern aircraft requirements dramatically. Numerical and experimental studies of FTV are performed with a nozzle pressure ratio (NPR) of 4–10, a secondary pressure ratio (SPR) of 1, 2 or 3, and two different secondary jet locations. Numerical simulations of the nozzle flow are done with solving the Navier-Stokes equations, and the input parameters are set to match the experimental conditions. The thrust pitching moment and the thrust pitching angle are determined to evaluate the FTV performance., 特集 : Special Section for the Papers Presented at the Symposium on Mechanical Engineering, Industrial Engineering, and Robotics held at Noboribetsu, Hokkaido, Japan on 11 - 12 January 2012

Published
2013

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Author

Nakamura, Yuji, Yamada, Yuichiro, Hirota, Mitsutomo, Saito, Tsutomu, Nakamura, Yuji, Yamada, Yuichiro, Hirota, Mitsutomo, and Saito, Tsutomu

Abstract

A strategy to diagnose ultra-lean flames utilizing the "acetone-OH simultaneous PLIF" concept via a one-laser and one-detector combination system is presented. The main of the present work is to overcome difficulties encountered in our previous studies; namely, that the seeding amount of acetone used for visualization purposes must be sufficiently small in order to avoid its effect on flame structure (at least <5% of fuel), while clear imaging also must be accomplished under such conditions. For this purpose, several important revisions have been made; 1) the 266 nm excitation line has been added to improve the fluorescence from acetone, 2) a dual-peak band-pass filter has been introduced instead of conventional blue filter and 3) controllability of fine acetone seeding has been improved. The effects of these changes on flame imaging are also investigated. Clear visualization of the flame zone of a very lean premixed flame, of which the limiting equivalence ratio is below 0.6, has been successfully achieved for the first time with one-laser and one-detector system. The time-dependent, near-extinction flame behavior is also clearly imaged, suggesting that this method could utilize to investigate the flame extinction study.

Published
2011

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