| Project/Area Number |
11650162
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| Research Category |
Grant-in-Aid for Scientific Research (C)
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| Allocation Type | Single-year Grants |
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| Section | 一般 |
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| Research Field |
Fluid engineering
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| Research Institution | Tohoku University |
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Principal Investigator |
SAWADA Kesuke Tohoku University, Graduate School of Engineering, Professor, 大学院・工学研究科, 教授 (80226068)
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| Project Period (FY) |
1999 – 2001
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| Project Status |
Completed (Fiscal Year 2001)
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| Budget Amount *help |
¥3,400,000 (Direct Cost: ¥3,400,000)
Fiscal Year 2001: ¥900,000 (Direct Cost: ¥900,000)
Fiscal Year 2000: ¥800,000 (Direct Cost: ¥800,000)
Fiscal Year 1999: ¥1,700,000 (Direct Cost: ¥1,700,000)
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| Keywords | Aerodynamic Heating / Ablator / Ablation Product Gas / Turbulent Transition / Pioneer-Venus / Stardust SRC / Radiative Hydrodynamics / Galileo Entry Capsule / アブレ-タ / MUSES-C / 輻射流れ場 / マルチバンドモデル / 密結合計算 / パラレル演算処理 / 乱流モデル / 密結合解法 |
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| Research Abstract |
We have developed a trajectory-based unified aerodynamic heating analysis code for entry capsule that employs ablator as heatshield. Using the code, an entry flight simulation for Stardust sample return capsule has been conducted in which significant increase of heating rate due to an earlier transition of the boundary layer was indicated. We have also calculated flow field for 4 entry probe vehicles in the Pioneer-Venus mission. Significantly higher heating rate at downstream region was obtained for all probe vehicles. A reasonable agreement is shown in the comparison of thermocouple temperatures with that given in the flight data. It is shown that significant heating phenomenon at downstream region is caused by an earlier turbulent transition due to ablation product gas. It is also indicated that a quantitative prediction of this phenomenon is possible if we employ Park's injection-induced turbulence model that assumes ablation product gas to be inherently turbulent.
Significant aerodynamic heating at downstream region was also observed when Galileo probe vehicle entered into Jovian atmosphere. A spectrally detailed radiation coupled CFD code on a parallel computer system has been developed that will be used in the simulation of entry flight for Galileo probe vehicle.
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