| Project/Area Number |
23860076
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| Research Category |
Grant-in-Aid for Research Activity Start-up
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| Allocation Type | Single-year Grants |
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| Research Field |
Fluid engineering
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| Research Institution | Japan Aerospace Exploration Agency |
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Principal Investigator |
ANYOJI Masayuki 独立行政法人宇宙航空研究開発機構, 宇宙科学研究所, プロジェクト研究員 (70611680)
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| Co-Investigator(Renkei-kenkyūsha) |
OKAMOTO Masato 金沢工業大学, 工学部, 教授 (70462124)
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| Research Collaborator |
HIDAKA Hidenori 金沢工業大学, 大学院・工学研究科, 修士二年
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| Project Period (FY) |
2011 – 2012
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| Project Status |
Completed (Fiscal Year 2012)
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| Budget Amount *help |
¥3,250,000 (Direct Cost: ¥2,500,000、Indirect Cost: ¥750,000)
Fiscal Year 2012: ¥1,560,000 (Direct Cost: ¥1,200,000、Indirect Cost: ¥360,000)
Fiscal Year 2011: ¥1,690,000 (Direct Cost: ¥1,300,000、Indirect Cost: ¥390,000)
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| Keywords | 火星飛行機 / 低レイノルズ数 / 三次元翼 / 剥離泡 / 翼端渦 / 舵効き / 火星探査航空機 / 機体の安定性 / 火星探査 / 風洞実験 / 空力計測 |
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| Research Abstract |
To obtain engineering design guidelines of main wings or tails toward realization of a Mars airplane that flies in the very rare Martian atmosphere, the relationship between design parameters of a three dimensional wing and aerodynamic characteristics at low Reynolds numbers are clarified and knowledge about fluid dynamic mechanisms which causes aerodynamic changes is obtained. Besides, wind tunnel tests on aerodynamic characteristics of a Mars-airplane scale model are conducted. Effectiveness of control surfaces becomes low at low Reynolds numbers. This is due to nonlinear aerodynamic characteristics of a tail airfoil and the effectiveness of control surfaces is improved successfully by a proper tail airfoil
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