Papers - KITAMURA Keiichi
about 76-
福嶋 岳, 北村 圭一
Physics of Fluids 36 ( 4 ) 2024.4 [Reviewed]
DOI Web of Science CiNii Research
Authorship：Last author Language：English Publishing type：Research paper (scientific journal) Publisher：American Institute of Physics Joint Work
In finite-volume methods, monotonic upstream-centered schemes for conservation laws (MUSCL) offer second-order spatial accuracy but tend to produce highly dissipative solutions for density discontinuity and weak shock waves. To address this limitation within a second-order framework, a novel strategy for hybridizing MUSCL with the tangent of the hyperbola interface capturing technique for both steady and unsteady compressible flows is presented. This hybridization optimizes the process based on the degree of nonlinearity and discontinuity around the target cells, providing a novel method to sharply resolve weak shock waves and robustly compute strong shock waves within the hybrid scheme. The proposed scheme sharply captures exceedingly weak shock waves that conventional MUSCL fails to resolve accurately due to excessive numerical dissipation. Furthermore, for resolving small vortices induced by instability at slip lines, computational results demonstrate high-resolution surpassing fifth-order spatial accuracy schemes within this second-order spatial accuracy framework with less computational cost. Moreover, the scheme exhibits commendable convergence and robustness when applied to steady-state problems featuring strong shock waves. This scheme offers a more precise and high-resolution alternative to conventional MUSCL for compressible flow computations, as it requires no additional stencil for reconstruction, unlike conventional fifth-order schemes.
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Towards shock-stable and accurate hypersonic heating computations: A new pressure flux for AUSM-family schemes
Kitamura, K. and Shima, E.
Journal of Computational Physics 245 ( 15 ) 62 - 83 2013.7 [Reviewed]
Authorship：Lead author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Publisher：Elsevier Joint Work
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Numerical and Experimental Investigations of Epsilon Launch Vehicle Aerodynamics at Mach 1.5
Keiichi Kitamura, Satoshi Nonaka, Kazuto Kuzuu, Junya Aono, Keiichiro Fujimoto, and Eiji Shima
Journal of Spacecraft and Rockets 50 ( 4 ) 896 - 916 2013.7 [Reviewed]
Authorship：Lead author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Publisher：AIAA Joint Work
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Evaluation of Euler Fluxes for Hypersonic Flow Computations
Kitamura, K., Roe, P., and Ismail, F.
AIAA Journal 47 ( 1 ) 44 - 53 2009 [Reviewed]
Authorship：Lead author Language：English Publishing type：Research paper (scientific journal) Publisher：AIAA Joint Work
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A Study on Aerodynamic Characteristics of a Slender Body in Pitching Motion by Surface Pressure Measurement
TAMAI Ryota, MAMASHITA Tomohiro, NONAKA Satoshi, KITAMURA Keiichi, ODAGIRI Kimihide, OGAWA Hiroyuki
Journal of Evolving Space Activities 2 ( 0 ) n/a 2024.9 [Reviewed]
Language：English Publishing type：Research paper (scientific journal) Publisher：宇宙技術および科学の国際シンポジウム Joint Work
<p>Transportation efficiency of a reusable launch vehicle must be improved in order to realize low cost and frequent space transportation. Utilizing aerodynamic force instead of the engine thrust is effective during a return flight of a reusable vehicle. However, the feasibility of such a return flight is questionable since aerodynamic characteristics are not understood enough for a slender body in a pitching motion over a wide range of angles of attack. We investigated the surface pressure distribution of a slender body both in pitching motions and in the steady condition in a wind tunnel experiment, covering a range of angles of attack from 0° to 180°. Our results show the pitching motion has a significant influence in delaying the transition of surface pressure. From the measured surface pressure, we evaluated the variation of aerodynamic characteristics corresponding to various angular pitching velocities. We also found that, during the pitching motion, the transition in flow patterns around the body is related to the surface pressure distribution and, consequently, influences the aerodynamic characteristics.</p>
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Numerical Study of Transonic Buffet on SC(2)-0518 and OAT15A with Vortex Generators
Tsukamoto, Y; Kitamura, K
AIAA JOURNAL 62 ( 8 ) 3052 - 3065 2024.5 [Reviewed]
Authorship：Last author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Joint Work
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FURUSAWA Yoshikatsu, KITAMURA Keiichi, IKAMI Tsubasa, NAGAI Hiroki
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 22 ( 0 ) 49 - 58 2024.5 [Reviewed]
Authorship：Corresponding author Language：English Publishing type：Research paper (scientific journal) Publisher：一般社団法人 日本航空宇宙学会 Joint Work
<p>This study aims to clarify the unsteady flow field structure over a fixed wing positioned within propeller slipstream and its effects on lift fluctuation of the fixed wing at a low Reynolds number (Re = 30,000). Numerical analyses were conducted with the configuration of a two-bladed propeller (APC Propellers 6x4E) and a fixed wing (Ishii airfoil) at three advance ratios (<i>J</i> = 0.8, 0.6, and 0.4) at the angle of attack 5°. Consequently, it was shown that a spanwise vortex structure involving very low pressure was induced over the fixed wing, even under the highest thrust condition (<i>J</i> = 0.4). In addition, three primary causes for the lift oscillation of the fixed wing were observed: 1) periodic vortex passage over the trailing edge, 2) periodic impingement of blade wake, which was shed from the propeller blade to the leading edge of the fixed wing, and 3) the high pressure behind the propeller owing to the high thrust, which periodically increased the lower surface pressure of the fixed wing. The <i>C<sub>L</sub></i> fluctuation by 1) and its synchronization with the blade passing frequency are considered distinctive characteristics of the low-Reynolds-number flows (Re ∼ <i>O</i>(10<sup>4</sup>)).</p>
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FURUSAWA Yoshikatsu, KITAMURA Keiichi, IKAMI Tsubasa, NAGAI Hiroki, OYAMA Akira
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 67 ( 1 ) 12 - 22 2024.1 [Reviewed]
Authorship：Corresponding author Language：English Publishing type：Research paper (scientific journal) Publisher：一般社団法人 日本航空宇宙学会 Joint Work
<p>To realize a propeller-driven Mars airplane, the propeller-wing flow interaction characteristics should be clarified. Thus, we conducted numerical simulations of the propeller-wing interaction at low Reynolds number conditions (<i>Re</i> = 3.0 × 10<sup>4</sup>) corresponding to Mars atmosphere, focusing on the propeller slipstream effects on the fixed wing. Solutions for the tractor case (propeller in front of the fixed wing) and the <i>wing only</i> case were compared. The results showed that in the tractor case, the lift coefficient (<i>C<sub>L</sub></i>) of the fixed wing increased with the angle of attack (<i>α</i>) more linearly than for the <i>wing only</i> case and showed delayed stall because the propeller slipstream favorably suppressed the expansion of the recirculation region over the fixed wing in the time-averaged flow fields, supporting the experimental result. The flow over the fixed wing separated from near the leading-edge in both low and high thrust conditions even at a moderate angle of attack (<i>α</i> = 5°), whereas previous studies at relatively high Reynolds numbers (<i>Re</i> ∼ <i>O</i>(10<sup>5</sup>)) showed that almost attached flow fields were formed under the propeller slipstream influence. Additionally, it was observed that the <i>C<sub>L</sub></i> fluctuation of the fixed wing increased even when the time-averaged <i>C<sub>L</sub></i> was lower than that of the <i>wing only</i> case.</p>
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Numerical simulation of elliptic bubble deformation by underwater shock wave
Aono, J., and Kitamura, K.
Explosion 33 ( 3 ) 159 - 163 2023.12 [Reviewed]
Authorship：Last author, Corresponding author Language：Japanese Publishing type：Research paper (scientific journal) Single Work
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Aerodynamic Effects of Surface Protuberance Size on Slender-Bodied Supersonic Vehicle
Nimura, K; Tsutsui, F; Kitamura, K; Nonaka, S
JOURNAL OF SPACECRAFT AND ROCKETS 61 ( 2 ) 355 - 368 2023.10 [Reviewed]
Authorship：Corresponding author Language：English Publishing type：Research paper (scientific journal) Joint Work
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Effects of Protuberance Size on Side Force Characteristics of Slender Body at Mach 0.7 and 1.3
Motoki Shogo, Nimura Kazuki, Magara Motoki, Kitamura Keiichi, Nonaka Satoshi
AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 22 ( 0 ) 71 - 78 2023.10 [Reviewed]
Authorship：Corresponding author Language：Japanese Publishing type：Research paper (scientific journal) Publisher：THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES Joint Work
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Mamashita Tomohiro, Muto Tomotaro, Kitamura Keiichi, Nonaka Satoshi
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 66 ( 4 ) 118 - 129 2023.7 [Reviewed]
DOI Web of Science CiNii Research
Authorship：Corresponding author Language：English Publishing type：Research paper (scientific journal) Publisher：一般社団法人 日本航空宇宙学会 Joint Work
<p>To investigate the aerodynamic characteristics of the reusable experimental vehicle “Reusable Vehicle-eXperiment (RV-X)” during a return phase (i.e., at 150–180° angles of attack), numerical calculations were performed on both actual-flight and wind-tunnel-test scales. The authors also validated the simulation results through comparing them with the data of corresponding wind tunnel tests. Especially, at an angle of attack of 180°, the results showed that the absolute axial force value |<i>C<sub>A</sub></i>| (i.e., drag working as an aerodynamic brake) under the flight conditions (<i>Re</i> = 9.0 × 10<sup>6</sup>) was approximately 87% smaller than that observed for the wind tunnel conditions (<i>Re</i> = 6.6 × 10<sup>5</sup>). It was discovered that this decrement is caused by a difference between the Reynolds numbers of the wind-tunnel-test and actual-flight scales. A comparison of the visualized flow fields clarified that the flow in the actual-flight scale with the larger Reynolds number does not tend to separate from the vehicle surface. Because of this, the accelerated and expanded flow at the base fillet area of the vehicle formed a significant low-pressure region, which pulled the vehicle in the direction of reducing |<i>C<sub>A</sub></i>| (i.e., decreasing aerodynamic braking).</p>
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AONO Junya, KITAMURA Keiichi
Journal of Fluid Science and Technology 18 ( 1 ) JFST0016 - JFST0016 2023.4 [Reviewed]
DOI Web of Science CiNii Research
Authorship：Last author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Publisher：一般社団法人 日本機械学会 Joint Work
<p>Multiphase flows arise in various fields that involve complicated phenomena. Studies have shown that COVID-19 can occur via air microdroplets, and breathing jets with microdroplets turn into turbulent cloud or puffs in cases of coughing and sneezing (Bourouiba et al., 2014). Microdroplets are upturned by buoyancy in the turbulent cloud and transported without falling. Furthermore, they float in air for hours and can be transported over long distances (Mittal et al., 2020). This scenario also involves a mixed phase flow of air and droplets. To simulate these phenomena, a numerical model assuming mechanical and thermal non-equilibrium multiphase flow is required to predict the range of turbulent cloud transport. In this study, to better simulate the turbulent cloud trajectories, a viscosity term is added to a two-phase flow six-equation model (two-fluid modeling or effective-fluid modeling, EFM) developed by Liou et al. (2008). It is a development of a parameter-free, viscous multiphase flow code, based on a single-phase compressible finite-volume solver (Kitamura et al., 2013). This solver is validated in the Poiseuille flow and laminar-flat-plate problem with an isothermal wall through a comparison with the analytical solutions. A detailed simulation of coughing is performed. The location of the turbulent cloud upturned by buoyancy is compared with the data of past studies.</p>
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Kitamura K., Takagi Y., Harada T., Yasumura Y., Kanamori M., Hashimoto A.
COMPUTERS & FLUIDS 255 2023.2 [Reviewed]
Authorship：Lead author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Joint Work
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Stability effect of multidimensional velocity components in numerical flux SLAU
Furusawa Yoshikatsu, Kitamura Keiichi
INTERNATIONAL JOURNAL FOR NUMERICAL METHODS IN FLUIDS 95 ( 6 ) 992 - 1010 2023.2 [Reviewed]
Authorship：Last author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Joint Work
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Aono Junya, Kitamura Keiichi
JOURNAL OF COMPUTATIONAL PHYSICS 462 111256 2022.8 [Reviewed]
DOI Web of Science CiNii Research
Authorship：Last author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Publisher：Academic Press Inc. Elsevier Science Joint Work
This paper proposes a novel method for the computation of compressible multiphase flows under the assumption of pressure equilibrium based on a 6-equation model and the AUSM (Advection Upstream Splitting Method) family. In this study, we introduce a new numerical pressure flux dissipation term based on the relative velocities in the gas and liquid phases to develop an analogous carbuncle-suppression mechanism that is applicable to gas dynamics. We also propose a mass flux dissipation term based on the pressure ratio at the gas-liquid interface and incorporate both terms into SLAU2, an AUSM-family scheme, to achieve robustness against shock anomalies. (c) 2022 The Author(s). Published by Elsevier Inc. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/).
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Tsutsui Fumiya, Kitamura Keiichi, Nonaka Satoshi
INTERNATIONAL JOURNAL OF AERONAUTICAL AND SPACE SCIENCES 23 ( 4 ) 670 - 679 2022.8 [Reviewed]
Authorship：Corresponding author Language：English Publishing type：Research paper (scientific journal) Joint Work
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Side Force Characteristics of Slender-Bodied Supersonic Vehicle with Two Protuberances
Tsutsui Fumiya, Takagi Yuya, Takimoto Hiroyuki, Kitamura Keiichi, Nonaka Satoshi
JOURNAL OF SPACECRAFT AND ROCKETS 59 ( 5 ) 1697 - 1712 2022.6 [Reviewed]
DOI Web of Science CiNii Research
Authorship：Corresponding author Language：English Publishing type：Research paper (scientific journal) Joint Work
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Kawashima Hayato, Kitamura Keiichi, Nonaka Satoshi
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 65 ( 3 ) 116 - 122 2022.5 [Reviewed]
DOI Web of Science CiNii Research
Authorship：Corresponding author Language：English Publishing type：Research paper (scientific journal) Publisher：一般社団法人 日本航空宇宙学会 Joint Work
<p>To accurately obtain a drag value for slender bodies (e.g., a rocket used in wind tunnel testing), base pressure and cavity pressure are required to be corrected to remove the effect of a sting. As the drag value significantly depends on the correction of the base/cavity pressure, attention should be paid, in spite of the absence of clear guidelines, to decide these two pressure values. In this study, to resolve this issue, wind tunnel test and numerical calculation results are used. As a result, first, we found that it is appropriate to measure the pressure near the base surface at four points and average them to estimate the base pressure. Second, the cavity pressure can be estimated the same as the uniform-flow static pressure even when shock waves are generated around the vehicle body. Based on these corrections, the total drag coefficient, <i>C</i><sub>D</sub>, showed an effective agreement between the wind tunnel test and computational fluid dynamics. Furthermore, in absence of the sting, the drag value increased by 8%.</p>
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Kitamura K., Yue Z., Fujimoto T., Asai H., Kubota A., Myokan M., Ichihara D., Sasoh A.
PHYSICS OF FLUIDS 34 ( 4 ) 2022.4 [Reviewed]
DOI Web of Science CiNii Research
Authorship：Lead author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Publisher：AIP Publishing Joint Work
In this study, three-dimensional numerical simulations and experiments of the interaction between a normal shock and bubbles generated by the repetitive energy depositions of a laser pulse in a Mach 1.92 flow was conducted. As a result of the shock-bubble interaction, a vortex ring, caused by a baroclinic effect, was generated. Owing to the self-induced velocity field, the advection velocity of the vortex rings decreased with increasing laser pulse energy. In the experiments, when interactions among the vortex rings became strong, separations in transverse directions between adjacent bubbles were induced. This was reproduced through numerical simulations by imposing an artificial disturbance in the initial positions of the bubbles, i.e., by 5% of the bubble diameter in a transversal direction. The asymmetric behaviors of a row of vortex rings were classified into three patterns based on the ratio of the distance between the vortex rings to the size of the vortex rings (lambda: inverse Strouhal number). In pattern 1, with >2.9, there was negligible interference between the vortex rings because the interval of the vortex rings was sufficiently large. In pattern lambda, with lambda = 0.97-1.2, separation in the vortex-ring rows appeared, and the separation angle increased as A. decreased. In pattern lambda, with a lambda <0.62, the interference intensified, and the vortex rings collapsed, forming a turbulent flow behind the shock wave. Published under an exclusive license by AIP Publishing.
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Takagi Yuya, Muto Tomotaro, Kitamura Keiichi, Nonaka Satoshi
JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 70 ( 1 ) 14 - 21 2022.2 [Reviewed]
Authorship：Corresponding author Language：Japanese Publishing type：Research paper (scientific journal) Publisher：THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES Joint Work
<p>In order to reduce launch cost, ISAS/JAXA has been developing a reusable vertical-takeoff and vertical-landing (VTVL) rocket. Currently, the prototype model ``RV-X'' is being developed. This rocket adopts nose-entry returning flight system and needs the turnover maneuver before landing. It is known that the side-force is generated by asymmetrical vortices when the rocket flies at high angles of attack, and also known that the apex angle of the nose cone affects the magnitude of side force. In this study, we conducted wind tunnel testing and CFD on the aerodynamics of the RV-X with a double-cone nose. The surface flow field were used for CFD validation. Consequently, we obtained following findings: 1) the slight asymmetry of the experimental model due to machining accuracy and surface roughness significantly affected the magnitude of side force, 2) the flow field by CFD at 60º angle-of-attack was qualitatively consistent with the surface flow field visualized by an oil-flow technique, 3) the vortices generated from the nose collapsed at the rear part of the body and formed an asymmetrical flow field, 4) the generation of asymmetrical vortices with respect to the angle of attack was influenced primarily by the first cone, but the created side force was determined by interactions of the first and the second cones. </p>
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SLAU2-HLLD Numerical Flux with Wiggle-Sensor for Stable Low Mach Magnetohydrodynamics Simulations
Tomohiro Mamashita, Keiichi Kitamura, Takashi Minoshima
Computers & fluids 231 105165-1 - 105165-12 2021.12 [Reviewed]
Authorship：Corresponding author Language：English Publishing type：Research paper (scientific journal) Joint Work
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Numerical Study of Surface Pressure Fluctuation on Rigid Disk-Gap-Band-Type Supersonic Parachutes
Kitamura K., Fukumoto K., Mori K.
AIAA JOURNAL 58 ( 12 ) 5347 - 5360 2020.12 [Reviewed]
Authorship：Lead author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Joint Work
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Numerical Study of Surface Pressure Fluctuation on Rigid Disk-Gap-Band-Type Supersonic Parachutes
北村 圭一
AIAA journal 2020.11 [Reviewed]
Authorship：Lead author, Last author Language：English Publishing type：Research paper (scientific journal) Publisher：American Institute of Aeronautics and Astronautics Joint Work
In the aerodynamic characteristics of supersonic parachutes, it is important to understand surface pressure distribution because it is strongly related to the fluctuation of drag and problematic unstable deformation of a parachute. However, there is a paucity of studies that focuses on the detailed surface pressure distribution. Therefore, we investigated the interior and exterior of a rigid disk-gap-band-type parachute as the first step, under the assumption that the forebody or suspension lines are absent, and thus the pressure and drag fluctuations are small. Two configurations are considered: one with a continuous gap and a vent orifice, representing a conventional Disk-Gap-Band parachute, and one with a discontinuous gap made up of 8 separate orifices and a vent orifice. By making the gap discontinuous, the interior and exterior pressure fluctuations are reduced. Furthermore, as indicated by the flowfield analysis, the discrete gap reduces the asymmetric pressure distribution interior the parachute, and the interior pressure fluctuation far from the center is suppressed. The result is considered useful for the suppression of unstable deformation such as area oscillation. This is currently a problem in supersonic parachute operation. In addition, we have identified locations on the model surface where the pressure fluctuations contribute to the drag fluctuations of the model.
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OGAWA Suguru, KITAMURA Keiichi
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 18 ( 6 ) 289 - 298 2020.11 [Reviewed]
Authorship：Last author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Publisher：THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES Joint Work
<p>In recent years, research is actively being conducted on unmanned air vehicles (UAVs), micro-air vehicles (MAVs), and Mars airplanes. In these flights, there is a common problem that laminar separation likely occurs due to the low Reynolds number (Re = 10<sup>4</sup>–10<sup>5</sup>) flight conditions. Laminar separation causes a reduction in the lift-to-drag ratio and hence needs to be controlled. In this study, we utilize the “moving surface method” to resolve this problem. This method supplies momentum to the separation part and controls flow near the wing surface by actively moving the upper surface in the direction of uniform flow; the 2D effect of this method has been demonstrated in a previous study. In this study, we successfully extended this effect to 3D wings. Upon applying the moving surface method, the NACA0006 wing achieved the largest lift-to-drag ratio improvement at an angle-of-attack of 6° and this was achieved by the Ishii wing as well. This is because, in this method, the laminar-separation bubble disappears, thus leading to a large drag reduction. In addition, as the angle-of-attack increases, differences in the 2D flow field become prominent and a strong 3D flow field appears, even when the moving surface method is not applied; at an angle-of-attack of 9°, many small vortices are generated, which complicates the flow field. The aerodynamic coefficient also varies; especially, the 3D drag coefficient is larger than its 2D counterpart. The moving surface method thus successfully suppresses 3D flow and flow separation, leading to a 2D attached flow field.</p>
Other Link： https://ci.nii.ac.jp/naid/130007935961
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Three-Dimensional Hypersonic Aeroheating Computations Associated with Cross-Flow Jet Interactions
KITAMURA Keiichi, HASE Naoya, TAGUCHI Masato, MORI Koichi
AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 19 ( 0 ) 141 - 150 2020.10 [Reviewed]
Authorship：Lead author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Publisher：THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES Joint Work
<p>Hypersonic aeroheating is one of challenging tasks in the modern Computational Fluid Dynamics (CFD), partly due to difficulties in accurate capturing of shockwaves and thermal boundary-layers, and partly due to lack of the reference data. We have tackled this problem by computationally reproducing the heating created by a hypersonic-flow/cross-flow-jet aerodynamic interaction. In the first half of this work, we surveyed both numerical flux functions and computational grids, and reached the conclusion that both AUSM<sup>+</sup>-up2 and SLAU2 successfully yielded analytical heating values with symmetry profiles over a blunt-body at Mach 8.1 (without the jet), as long as the minimum cell size was set small enough (cell-Reynolds-number being 0.32 or smaller). Then the second half was dedicated to the cross-flow-jet interaction. Using AUSM<sup>+</sup>-up2, we again succeeded in simulating the jet-interaction-induced aeroheating and pressure augmentations and their distributions, as well as complicated three-dimensional flow structures. Furthermore, a new heating mechanism not tied to pressure increase has been identified. These pieces of information are expected to serve as one of guidelines for hypersonic CFD, new insights into hypersonic flow physics, and also additional data for validation purposes.</p>
Other Link： https://ci.nii.ac.jp/naid/130007931612
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SLAU2 applied to two-dimensional, ideal magnetohydrodynamics simulations
Kitamura Keiichi, Mamashita Tomohiro, Ryu Dongsu
COMPUTERS & FLUIDS 209 104635-1 - 104635-16 2020.9 [Reviewed]
DOI Web of Science CiNii Research
Authorship：Lead author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Publisher：Pergamon-Elsevier Science Ltd Joint Work
SLAU2 (Simple Low-dissipation Advection-Upstream-splitting-method 2) numerical flux function, one of AUSM-type methods (3-wave solver), originally developed and widely used in gasdynamics, has been applied to two-dimensional magnetohydrodynamics (MHD) simulations. According to numerical tests for a wide range of flow and magnetic conditions, its reliability, efficiency, and accuracy have been demonstrated: i) Robustness of SLAU2 against shock-anomalies (e.g., carbuncle phenomena) has been confirmed in the MHD-extended version of our hypersonic flow test; ii) The computational cost has been reduced for approximately 3% compared with HLLD (Harten-Lax-van_Leer with Discontinuities), a more expensive, 5-wave solver; iii) Nevertheless, its solution qualities are almost equal to those of HLLD, as opposed to very diffused HLL solutions. For benchmark tests, detailed and important flow physics such as multidimensional shock/shock interactions have been successfully reproduced by SLAU2. We hope that SLAU2 will contribute to further progress of the astrophysics and other research fields. (C) 2020 Elsevier Ltd. All rights reserved.
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TAKAGI Yuya, AOGAKI Takuya, KITAMURA Keiichi, NONAKA Satoshi
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 18 ( 4 ) 149 - 158 2020.7 [Reviewed]
Authorship：Corresponding author Language：English Publishing type：Research paper (scientific journal) Publisher：THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES Joint Work
<p>Conventional rockets are faced with several problems such as high launching cost. Therefore, in Japan, a reusable vertical-takeoff-and-vertical-landing (VTVL) rocket vehicle is being developed. This vehicle utilizes nose entry as the return flight system including the attitude change (turnover) due to aerodynamic forces. To safely achieve turnover, it is necessary to reduce the difference between the maximum value and minimum value of <i>C</i><sub>m</sub> (i.e., pitching-moment coefficient). In this study, a delta-wing with vortex flaps (developed for the aircraft industry) is attached to the aft of the vehicle with the expectation of improving the <i>C</i><sub>m</sub> characteristics during the turnover process. Consequently, when the flap deflection angle is 0°, the nose-up <i>C</i><sub>m</sub> can be reduced at forward angles (i.e., AOA 0° - 90°) because vortices generated by the fins result in a nose-down <i>C</i><sub>m</sub> and cancel the nose-up <i>C</i><sub>m</sub>. Moreover, when the flap deflection angle is -30°, the nose-down <i>C</i><sub>m</sub> is enhanced at the backward angles (i.e., AOA 90° - 180°) because the flaps reduce the vortices generated by fins. Hence, setting the flap deflection angle at 0° for the forward angles and -30° for the backward angles reduced the difference between the maximum and minimum values of <i>C</i><sub>m</sub> (i.e., 12% smaller than a conventional model).</p>
Other Link： https://ci.nii.ac.jp/naid/130007869262
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A Multistate Low-dissipation Advection Upstream Splitting Method for Ideal Magnetohydrodynamics
Minoshima Takashi, Kitamura Keiichi, Miyoshi Takahiro
ASTROPHYSICAL JOURNAL SUPPLEMENT SERIES 248 ( 1 ) 2020.5 [Reviewed]
Language：English Publishing type：Research paper (scientific journal) Joint Work
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AUSM-like expression of HLLC and its all-speed extension
Kitamura Keiichi, Shima Eiji
INTERNATIONAL JOURNAL FOR NUMERICAL METHODS IN FLUIDS 92 ( 4 ) 246 - 265 2019.11 [Reviewed]
Authorship：Lead author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Joint Work
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Canny-Edge-Detection/Rankine-Hugoniot-conditions unified shock sensor for inviscid and viscous flows
Fujimoto Takeshi R., Kawasaki Taro, Kitamura Keiichi
JOURNAL OF COMPUTATIONAL PHYSICS 396 264 - 279 2019.11 [Reviewed]
Authorship：Last author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Joint Work
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Hybridized SLAU2-HLLI and hybridized AUSMPW plus -HLLI Riemann solvers for accurate, robust, and efficient magnetohydrodynamics (MHD) simulations, part I: one-dimensional MHD
Kitamura K., Balsara D. S.
SHOCK WAVES 29 ( 5 ) 611 - 627 2019.7 [Reviewed]
Authorship：Lead author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Joint Work
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Numerical Experiments on Anomalies from Stationary, Slowly Moving, and Fast-Moving Shocks
Kitamura Keiichi, Shima Eiji
AIAA JOURNAL 57 ( 4 ) 1766 - 1775 2019.4 [Reviewed]
Authorship：Lead author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Joint Work
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Experimental and Numerical Investigations of Slender Body Side Force with Asymmetric Protuberances
Kawauchi K., Harada T., Kitamura K., Nonaka S.
JOURNAL OF SPACECRAFT AND ROCKETS 56 ( 5 ) 1346 - 1357 2019.3 [Reviewed]
Authorship：Corresponding author Language：English Publishing type：Research paper (scientific journal) Joint Work
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Numerical Analysis on Flow in/around Simplified Supersonic Parachute at Opening
TAKABAYASHI Koki, KITAMURA Keiichi
AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 18 ( 0 ) 67 - 72 2019.3 [Reviewed]
Authorship：Last author, Corresponding author Language：Japanese Publishing type：Research paper (scientific journal) Publisher：THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES Joint Work
<p>A supersonic parachute is one of effective and promising deceleration processes at entry into a planet. However, fundamental researches on its aerodynamics, particularly at its opening phase, have not been fully carried out. In this study, flow fields in/around simple configurations that modeled a supersonic parachute at its opening are discussed using computed fluid dynamics. Results indicate that pressure inside the parachute is exposed to twice (at the maximum) as large as the pitot pressure at Mach 2. In addition, the so-called “breathing," which is a more characteristic unsteady phenomenon, appears due to the internal pressure fluctuation, which changes the position of the detached shock wave periodically. Finally, at a higher Reynolds number, the boundary-layer inside the parachute became thinner, leading to more complex shock/boundary-layer interactions.</p>
Other Link： https://ci.nii.ac.jp/naid/130007610667
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Roll Moment Characteristics of Supersonic Flight Vehicle Equipped with Asymmetric Protuberance
HARADA Toshiaki, KITAMURA Keiichi, NONAKA Satoshi
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 2019.3 [Reviewed]
Authorship：Corresponding author Language：English Publishing type：Research paper (scientific journal) Publisher：一般社団法人 日本航空宇宙学会 Joint Work
<p>Most of flight vehicles have various protuberant devices on their surfaces, but asymmetry in their positioning with respect to the body axis can affect aerodynamic characteristics of vehicles, particularly roll moment. Thus, it is important in rocket development to clarify the effects of the protuberances on the vehicle aerodynamic characteristics. In this study, as a basic research, we systematically investigated such effects using CFD, by changing the positions of a protuberance. As a result, the roll moment increased nearly linearly with angle of attack (=<i>α</i>), but its trend was different in protuberance locations, particularly when arranged near the center-of-gravity. In positioning there at <i>α </i>= 20 °, the wake vortex center moved farther away from protuberance compared with <i>α</i> = 15 °, then the pressure decline at its wake side was suppressed, and thus, the pressure difference between its upstream and downstream sides became smaller. As a consequence, the roll moment did not arise linearly, but decreased at <i>α</i> = 20 °.</p>
Other Link： https://ci.nii.ac.jp/naid/130007584717
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Computational Study on Finned Reusable Rocket Aerodynamics during Turnover
AOGAKI Takuya, KITAMURA Keiichi, NONAKA Satoshi
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 2019.1 [Reviewed]
Authorship：Corresponding author Language：English Publishing type：Research paper (scientific journal) Publisher：一般社団法人 日本航空宇宙学会 Joint Work
<p>The development of a fully reusable vertical-takeoff-and-vertical-landing (VTVL) rocket is indispensable for reducing space transportation costs. However, there are many technical issues associated with such vehicles, such as turnover maneuvers during return flight where the pitching moment plays a key role. It is known that aerodynamic characteristics can be controlled by installing aerodynamic devices, but the relationship between the aerodynamic characteristics and the flowfields has not been explored. To clarify this relationship using computational fluid dynamics (CFD), we investigated these flowfields and aerodynamic characteristics, in the case where we install such devices (fins) in the nose part of a reusable rocket. We found that vortices form downstream of the aerodynamic devices. For angles of attack between 0 and 90 degrees (in which the fins are located in the upstream portion), these vortices significantly affect the surface pressure on the rocket and increase the pitching moment. On the other hand, for AOAs between 90 to 180 degrees (in which the fins are in the downstream portion), the effect of these vortices on the on-surface pressure is negligible, and only vortices formed near the surface of the fins increase the pitching moment.</p>
Other Link： https://ci.nii.ac.jp/naid/130007585297
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Numerical Analysis on Reusable Rocket Aerodynamics with Reduced-Yaw-Force Configurations
INATOMI Ayano, KITAMURA Keiichi, NONAKA Satoshi
TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 17 ( 4 ) 439 - 446 2019.1 [Reviewed]
Authorship：Corresponding author Language：English Publishing type：Research paper (scientific journal) Publisher：一般社団法人 日本航空宇宙学会 Joint Work
<p>It is known that aerodynamic characteristics of a slender body vary substantially at high angles-of-attack (AoAs), and then, will have strong impacts on its flight. For, example, the yaw force makes flight unstable. In this study, we investigated the relation between the yaw force and the configuration, and details of flowfield around the slender-bodied-vehicle numerically. The configuration consisting of “nose cone” and “square aftbody” parts was employed as the baseline, and then, compared with other three configurations having different fineness ratios. According to our computed results, in the case of 50 degrees of AoA, the longer the model became, the more asymmetry appeared: yaw force and asymmetry were found to be attributed not only to the length of the body, but also to the nose bluntness. On the contrary, in the case of 140 degrees, the shorter the model became, the more asymmetry appeared. Furthermore, the large nose bluntness increased C<sub>Y</sub>. Interestingly, this trend is totally opposite to that observed at 50 degrees. It had been considered that the large nose bluntness and the small fineness ratio can reduce asymmetry and C<sub>Y</sub>, however, this study showed that it is not true in the case over 90 degrees, due to complex wake flow structure discovered in the present numerical simulations.</p>
Other Link： https://ci.nii.ac.jp/naid/130007674831
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High Angle-of-Attack Pitching Moment Characteristics of Slender-Bodied Reusable Rocket
Aogaki Takuya, Kitamura Keiichi, Nonaka Satoshi
JOURNAL OF SPACECRAFT AND ROCKETS 55 ( 6 ) 1476 - 1489 2018.11 [Reviewed]
Authorship：Corresponding author Language：English Publishing type：Research paper (scientific journal) Joint Work
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Postlimiters and Simple Dirty-Cell Detection for Three-Dimensional Unstructured (Unlimited) Aerodynamic Simulations
Kitamura K., Aogaki T., Inatomi A., Fukumoto K., Takahama T., Hashimoto A.
AIAA JOURNAL 56 ( 8 ) 3192 - 3204 2018.8 [Reviewed]
Authorship：Lead author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Joint Work
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Pressure-equation-based SLAU2 for oscillation-free, supercritical flow simulations
Kitamura Keiichi, Shima Eiji
COMPUTERS & FLUIDS 163 86 - 96 2018.2 [Reviewed]
Authorship：Lead author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Joint Work
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Aerodynamic Improvements of Airfoils at Low Reynolds Number by Moving Surface Method
KITAMURA Keiichi, OGAWA Suguru, TAKAHAMA Toshimasa
AEROSPACE TECHNOLOGY JAPAN, THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 17 ( 0 ) 227 - 236 2018 [Reviewed]
Authorship：Lead author, Corresponding author Language：Japanese Publishing type：Research paper (scientific journal) Publisher：THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES Joint Work
<p>The moving surface method (Wang Y., et al., J. Jpn. Soc. Aero. Space Sci., Vol. 58, 2010, pp. 239-244, in Japanese) is applied to low Reynolds number flows over thin airfoils as a flow separation control method for further aerodynamic enhancement. The moving surface method is based on Couette Flow-type momentum addition and is expected as a promising means in order to achieve lift enhancement. In order to evaluate aerodynamic effects of the moving surface method at a low Reynolds number, we employed NACA0006, Ishii airfoil, and Owl-like airfoil, and performed two dimensional CFD simulations. The results demonstrate that by applying the moving surface method, the leeward flow separation is successfully suppressed and lift-to-drag ratio is increased, particularly for the Owl-like airfoil. In addition, interestingly, a further drag reduction has been observed by increasing the surface-moving velocity, in which pressure suction at the leading edge is promoted. As a consequence, the maximum lift-to-drag ratio reached 44 (Owl-like airfoil with 9 degrees of attack angle), 2.2 times the case without the moving surface.</p>
Other Link： https://ci.nii.ac.jp/naid/130007420575
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Simple a posteriori slope limiter (Post Limiter) for high resolution and efficient flow computations
Kitamura Keiichi, Hashimoto Atsushi
JOURNAL OF COMPUTATIONAL PHYSICS 341 313 - 340 2017.7 [Reviewed]
Authorship：Lead author, Corresponding author Language：Japanese Publishing type：Research paper (scientific journal) Joint Work
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Assessment of WENO-extended two-fluid modelling in compressible multiphase flows
Kitamura Keiichi, Nonomura Taku
INTERNATIONAL JOURNAL OF COMPUTATIONAL FLUID DYNAMICS 31 ( 3 ) 188 - 194 2017 [Reviewed]
Authorship：Lead author, Corresponding author Language：Japanese Publishing type：Research paper (scientific journal) Joint Work
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Assessment of SLAU2 and Other Flux Functions with Slope Limiters in Hypersonic Shock-Interaction Heating
Kitamura, K.
Computers & Fluids 129 134 - 145 2016.4 [Reviewed]
Authorship：Lead author, Last author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Publisher：Elsevier Single Work
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Reduced Dissipation AUSM-Family Fluxes: HR-SLAU2 and HR-AUSM+-up for High Resolution Unsteady Flow Simulations
Kitamura, K. and Hashimoto, A.
Computers & Fluids 126 41 - 57 2016.3 [Reviewed]
Authorship：Lead author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Publisher：Elsevier Joint Work
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On All-Speed Compressible CFD Solver Unifying the Implicit MUSCL and SMAC scheme
Eiji Shima, Keiichi KITAMURA
NAGARE: journal of Japan Society of Fluid Mechanics 35 ( 5 ) 391 - 401 2016 [Reviewed]
Authorship：Last author Language：Japanese Publishing type：Research paper (scientific journal) Publisher：Japan Society of Fluid Mechanics Joint Work
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Experimental Investigations on Flexible Parachutes in Supersonic Flow
Taguchi, M., Semba, N., Okada, M., Yasui, I., Kitamura, K., Mori, K., and Nakamura, Y.
Journal of Japan Society of Aeronautical and Space Sciences 63 ( 6 ) 241 - 247 2015.12 [Reviewed]
Language：Japanese Publishing type：Research paper (scientific journal) Publisher：The Japan Society for Aeronautical and Space Sciences Joint Work
Other Link： https://www.jstage.jst.go.jp/article/jjsass/63/6/63_63_241/_article/-char/ja/
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Preliminary, One-Way Coupled, Rain-Droplets/Airflow Simulations over Automobile
Harada, N., Kitamura, K., Okutsu, Y., Hamamoto, N., Mori, K., and Nakamura, Y.
International Journal of Automotive Engineering 6 ( 4 ) 105 - 112 2015 [Reviewed]
Language：English Publishing type：Research paper (scientific journal) Joint Work
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Extension and Comparative Study of AUSM-Family Schemes for Compressible Multiphase Flow Simulations
Kitamura, K., Liou, M.-S., and Chang, C.-H.
Communications in Computational Physics 16 ( 3 ) 632 - 674 2014.9 [Reviewed]
Authorship：Lead author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Publisher：Global-Science Press Joint Work
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Simple and Robust HLLC Extensions of Two-Fluid AUSM for Multiphase Flow Computations
Kitamura, K. and Nonomura, T.
Computers & Fluids 100 321 - 335 2014.6 [Reviewed]
Authorship：Lead author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Publisher：Elsevier Joint Work
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A Simple Interface Sharpening Technique with a Hyperbolic Tangent Function Applied to Compressible Two-Fluid Modeling
Nonomura, T., Kitamura, K., and Fujii, K.
Journal of Computational Physics 258 95 - 117 2014.2 [Reviewed]
Language：English Publishing type：Research paper (scientific journal) Publisher：Elsevier Joint Work
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Numerical Simulation Based on CFD for Aerodynamic Characteristics of Kite in Flight
Mano, S., Kitamura, K., Doi, K., and Nakamura, Y.
Trans. JSASS Aerospace Tech. Japan 12 1 - 10 2014.2 [Reviewed]
Authorship：Corresponding author Language：English Publishing type：Research paper (scientific journal) Publisher：The Japan Society for Aeronautical and Space Sciences Joint Work
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Green-Gauss/Weighted-Least-Squares Hybrid Gradient Reconstruction for Arbitrary Polyhedra Unstructured Grids
Shima, E., Kitamura, K., and Haga, T
AIAA Journal 51 ( 11 ) 2740 - 2747 2013.11 [Reviewed]
Authorship：Corresponding author Language：English Publishing type：Research paper (scientific journal) Publisher：AIAA Joint Work
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New approaches for computation of low Mach number flows
Shima, E. and Kitamura, K.
Computers & Fluids 85 143 - 152 2013.10 [Reviewed]
Authorship：Last author Language：English Publishing type：Research paper (scientific journal) Publisher：Elsevier Joint Work
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Numerical Analysis of Flow Field and Aerodynamic Characteristics of a Quadrotor
Yasuda, H., Kitamura, K., and Nakamura, Y.
Trans. JSASS Aerospace Tech. Japan 11 61 - 70 2013.9 [Reviewed]
Language：English Publishing type：Research paper (scientific journal) Publisher：The Japan Society for Aeronautical and Space Sciences Joint Work
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Multidimensional Numerical Noise from Captured Shockwave and Its Cure
Shima, E. and Kitamura, K.
AIAA Journal 51 ( 4 ) 992 - 998 2013.4 [Reviewed]
Authorship：Last author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Publisher：AIAA Joint Work
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Carbuncle Phenomena and Other Shock Anomalies in Three Dimensions
Kitamura, K., Shima, E., and Roe, P.
AIAA Journal 50 ( 12 ) 2655 - 2669 2012 [Reviewed]
Authorship：Lead author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Publisher：AIAA Joint Work
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Simple and Parameter-Free Second Slope Limiter for Unstructured Grid Aerodynamic Simulations
Kitamura, K., and Shima, E.
AIAA Journal 50 ( 6 ) 1415 - 1426 2012 [Reviewed]
Authorship：Lead author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Publisher：AIAA Joint Work
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Numerical Analysis on Aerodynamic Characteristics of Advanced Solid Rocket
Kitamura, K., Fujimoto, K., Kuzuu, K., Nonaka, S., Irikado, T., Fukuzoe, M., and Shima, E.
AEROSPACE TECHNOLOGY JAPAN 10 ( 0 ) 1 - 10 2011 [Reviewed]
Authorship：Lead author, Corresponding author Language：Japanese Publishing type：Research paper (scientific journal) Publisher：The Japan Society for Aeronautical and Space Sciences Joint Work
Other Link： https://www.jstage.jst.go.jp/article/astj/10/0/10_0_1/_article/-char/ja/
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Kitamura, K., Kuzuu, K., Irikado, T., Nonaka, S., Fujimoto, K., Fukuzoe, M., and Shima, E.
AEROSPACE TECHNOLOGY JAPAN 10 ( 0 ) 43 - 50 2011 [Reviewed]
Authorship：Lead author, Corresponding author Language：Japanese Publishing type：Research paper (scientific journal) Publisher：The Japan Society for Aeronautical and Space Sciences Joint Work
Other Link： https://www.jstage.jst.go.jp/article/astj/10/0/10_0_43/_article/-char/ja/
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Validation of Arbitrary Polyhedra Unstructured CFD Code for Aerodynamic Analyses
Kitamura, K., Fujimoto, K., Kuzuu, K., Shima, E., and Wang, Z.J.
Trans. Japan Soc. Aero. Space Sci. 53 ( 182 ) 311 - 319 2011 [Reviewed]
Authorship：Lead author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Publisher：The Japan Society for Aeronautical and Space Sciences Joint Work
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Performance of Low-Dissipation Euler Fluxes and Preconditioned LU-SGS at Low Speeds
Kitamura, K., Shima, E., Fujimoto, K., and Wang, Z.J.
Communications in Computational Physics 10 ( 1 ) 90 - 119 2011 [Reviewed]
Authorship：Lead author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Joint Work
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Parameter-Free Simple Low-Dissipation AUSM-Family Scheme for All Speeds
Shima, E. and Kitamura, K.
AIAA Journal 49 ( 8 ) 1693 - 1709 2011 [Reviewed]
Authorship：Last author Language：English Publishing type：Research paper (scientific journal) Publisher：AIAA Joint Work
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Effects of Crack on Heat Flux in Hypersonic Shock/Boundary-Layer Interaction
Ozawa, H., Hanai, K., Kitamura, K., Mori, K., and Nakamura, Y.
Journal of Japan Society of Aeronautical and Space Sciences 58 ( 674 ) 68 - 75 2010 [Reviewed]
Language：Japanese Publishing type：Research paper (scientific journal) Publisher：The Japan Society for Aeronautical and Space Sciences Joint Work
Other Link： https://www.jstage.jst.go.jp/article/jjsass/58/674/58_674_68/_article/-char/ja/
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Wind Tunnel Tests on Aerodynamic Characteristics of Advanced Solid Rocket
Kitamura, K., Fujimoto, K., Nonaka, S., Irikado, T., Fukuzoe, M., and Shima, E.
AEROSPACE TECHNOLOGY JAPAN 9 ( 0 ) 9 - 14 2010 [Reviewed]
Authorship：Lead author, Corresponding author Language：Japanese Publishing type：Research paper (scientific journal) Publisher：The Japan Society for Aeronautical and Space Sciences Joint Work
Other Link： https://www.jstage.jst.go.jp/article/astj/9/0/9_0_9/_article/-char/ja/
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Unsteady Aerodynamic Interaction between Two Bodies at Hypersonic Speed
Ozawa, H., Kitamura, K., Hanai, K., Mori, K., and Nakamura, Y.
Trans. Japan Soc. Aero. Space Sci. 53 ( 180 ) 114 - 121 2010 [Reviewed]
Language：English Publishing type：Research paper (scientific journal) Publisher：The Japan Society for Aeronautical and Space Sciences Joint Work
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Evaluation of Euler Fluxes for Hypersonic Heating Computations
Kitamura, K., Shima, E., Nakamura, Y., and Roe, P.L.
AIAA Journal 48 ( 4 ) 763 - 776 2010 [Reviewed]
Authorship：Lead author, Corresponding author Language：English Publishing type：Research paper (scientific journal) Publisher：AIAA Joint Work
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Abort System Using Supersonic Aerodynamic Interaction for Capsule-Type Space Transportation System
Ozawa, H., Kitamura, K., Hanai, K., Miyoshi, M., Mori, K., and Nakamura, Y.
Journal of Japan Society of Aeronautical and Space Sciences 57 ( 664 ) 175 - 182 2009 [Reviewed]
Language：Japanese Publishing type：Research paper (scientific journal) Publisher：The Japan Society for Aeronautical and Space Sciences Joint Work
Other Link： https://www.jstage.jst.go.jp/article/jjsass/57/664/57_664_175/_article/-char/ja/
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The Role of Vortices in Side Jet/Blunt Body Interaction at Hypersonic Speed
Ibrahim, M.K., Nakamura, T., Kitamura, K., Mori, K., and Nakamura, Y.
Trans. JSASS Space Tech. Japan 7 1 - 10 2009 [Reviewed]
Language：English Publishing type：Research paper (scientific journal) Publisher：The Japan Society for Aeronautical and Space Sciences Joint Work
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Research on Acoustic Environment during Rocket Launch
Murakami, K., Kitamura, K., Hashimoto, A., Aoyama, T. and Nakamura, Y.
Theoretical and Applied Mechanics Japan 56 463 - 469 2008 [Reviewed]
Language：English Publishing type：Research paper (scientific journal) Joint Work
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Kitamura, K., Ozawa, H., Hanai, K., Mori, K. and Nakamura, Y.
Journal of Japan Society of Aeronautical and Space Sciences 56 ( 653 ) 278 - 285 2008 [Reviewed]
Authorship：Lead author Language：Japanese Publishing type：Research paper (scientific journal) Publisher：The Japan Society for Aeronautical and Space Sciences Joint Work
Other Link： https://www.jstage.jst.go.jp/article/jjsass/56/653/56_653_278/_article/-char/ja/
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Numerical Analysis on Aerodynamic Heating in Hypersonic Shock Interacting Flow
Kitamura, K. and Nakamura, Y.
Journal of Japan Society of Aeronautical and Space Sciences 56 ( 653 ) 269 - 277 2008 [Reviewed]
Authorship：Lead author Language：Japanese Publishing type：Research paper (scientific journal) Publisher：The Japan Society for Aeronautical and Space Sciences Joint Work
Other Link： https://www.jstage.jst.go.jp/article/jjsass/56/653/56_653_269/_article/-char/ja/
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Very Simple, Carbuncle-Free, Boundary-Layer-Resolving, Rotated-Hybrid Riemann Solvers
Nishikawa, H. and Kitamura, K.
Journal of Computational Physics 227 ( 4 ) 2560 - 2581 2008 [Reviewed]
Authorship：Last author Language：English Publishing type：Research paper (scientific journal) Publisher：Elsevier Joint Work
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Effects of TSTO Orbiter Configuration on Supersonic Flow Field with Aerodynamic Interactions
Kitamura, K., Mori, K., Hanai, K., Yabashi, T., Ozawa, H. and Nakamura, Y.
Journal of Japan Society of Aeronautical and Space Sciences 55 ( 646 ) 509 - 515 2007 [Reviewed]
Authorship：Lead author Language：Japanese Publishing type：Research paper (scientific journal) Publisher：The Japan Society for Aeronautical and Space Sciences Joint Work
Other Link： https://www.jstage.jst.go.jp/article/jjsass/55/646/55_646_509/_article/-char/ja/
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Effect of the Clearance between Two Bodies on TSTO Aerodynamic Heating
Nishino, A., Ishikawa, T., Kitamura, K. and Nakamura, Y.
Journal of Japan Society of Aeronautical and Space Sciences 53 ( 622 ) 503 - 509 2005 [Reviewed]
Language：Japanese Publishing type：Research paper (scientific journal) Publisher：The Japan Society for Aeronautical and Space Sciences Joint Work
Other Link： https://www.jstage.jst.go.jp/article/jjsass/53/622/53_622_503/_article/-char/ja/