| Project/Area Number |
22760629
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| Research Category |
Grant-in-Aid for Young Scientists (B)
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| Allocation Type | Single-year Grants |
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| Research Field |
Aerospace engineering
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| Research Institution | Japan Aerospace Exploration Agency |
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Principal Investigator |
OZAWA Takashi 独立行政法人宇宙航空研究開発機構, 研究開発本部, 研究員 (70567544)
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| Project Period (FY) |
2010 – 2011
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| Project Status |
Completed (Fiscal Year 2011)
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| Budget Amount *help |
¥4,160,000 (Direct Cost: ¥3,200,000、Indirect Cost: ¥960,000)
Fiscal Year 2011: ¥1,040,000 (Direct Cost: ¥800,000、Indirect Cost: ¥240,000)
Fiscal Year 2010: ¥3,120,000 (Direct Cost: ¥2,400,000、Indirect Cost: ¥720,000)
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| Keywords | 希薄気体 / 極超音速流れ / 希薄風洞 / 航空宇宙工学 / 数値解析 / HRWT / DSMC / 極超音速希薄気体 |
|---|
| Research Abstract |
Investigation on aerodynamic characteristics of hypersonic rarefied gas flows has been essential for a variety of situations, such as the Super Low Altitude Test Satellite, earth reentries, or planetary atmospheric entries. At Japan Aerospace Exploration Agency, a 100-mm Hypersonic Rarefied Wind Tunnel(HRWT) has been developed. A 45-degree conical nozzle has been designed in this research, and rarefied hypersonic flows have been successfully generated with a Mach number greater than 10.In addition, an integration system between HRWT measurements and particle simulations has been developed, and this system enables us to improve aerodynamic prediction in hypersonic rarefied flows due to the determination of surface accommodation coefficients.
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