Development of a Double Path PDI Method of Two-Wavelength Light Source and Investigation of the Airfoil Characteristics in a Low-Reynolds Number High-Subsonic Flow
| Project/Area Number |
17K06956
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| Research Category |
Grant-in-Aid for Scientific Research (C)
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| Allocation Type | Multi-year Fund |
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| Section | 一般 |
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| Research Field |
Aerospace engineering
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| Research Institution | 防衛大学校(総合教育学群、人文社会科学群、応用科学群、電気情報学群及びシステム工学群) |
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Principal Investigator |
Kashitani Masashi 防衛大学校(総合教育学群、人文社会科学群、応用科学群、電気情報学群及びシステム工学群), システム工学群, 教授 (80535279)
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| Project Period (FY) |
2017-04-01 – 2020-03-31
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| Project Status |
Completed (Fiscal Year 2019)
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| Budget Amount *help |
¥4,810,000 (Direct Cost: ¥3,700,000、Indirect Cost: ¥1,110,000)
Fiscal Year 2019: ¥910,000 (Direct Cost: ¥700,000、Indirect Cost: ¥210,000)
Fiscal Year 2018: ¥650,000 (Direct Cost: ¥500,000、Indirect Cost: ¥150,000)
Fiscal Year 2017: ¥3,250,000 (Direct Cost: ¥2,500,000、Indirect Cost: ¥750,000)
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| Keywords | 風洞試験 / 点回折干渉計 / 低レイノルズ数 / 高揚力装置 / 空力特性 / 翼型流れ / 翼型 / 数値シミュレーション / 高分解能 / 低レノルズ数 / 空気力学 / 低レイノルズ数流れ / 衝撃波管 / 可視化 |
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| Outline of Final Research Achievements |
In this study, point diffraction interferometer (the technique called PDI) based on a double path optical system was developed. Aerodynamic characteristics in a low-Reynolds-number and high-subsonic flows were investigated for the development of unmanned vehicles for Mars exploration. A diaphragmless shock tube, which allows easy change of the operation gas, was used as an intermittent wind tunnel. The double path PDI technique enables the quantitative measurement of low Reynolds number, high subsonic flows. The experiments using CO2 and air as the operation gases showed different flow patterns even if the same airfoil was used. This is due to the difference in the critical Mach number of the operation gas.
Thus, the PDI optical system proposed in this project is profitable for the flow visualization and quantitative measurements of low-Reynolds-number, high-subsonic flows. And the results are expected to contribute to the basic database of airfoils for Mars exploration.
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| Academic Significance and Societal Importance of the Research Achievements |
低レイノルズ数，高亜音速における翼型流れの可視化や翼面圧力の測定は，近年の火星探査無人機の開発と関係し国内外において積極的に取り組まれている．しかし，火星大気は地球とは異なり，その主成分がCO2であること，また，大気密度が地球の100分の1と極めて低いことが知られ，従来の測定法では得られるデータ精度に限界がある．そこで，本研究では，シュリーレン光学系を流用し低レイノルズ数でも流れの可視化と翼面圧力測定が可能な再回帰型の点回折干渉計を開発し，低レイノルズ数，高亜音速翼型流れの空力特性の解明をここり見た．これにより，火星環境下における翼型の空力特性の基礎的データベースに寄与できたものと思われる．
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Report
(4 results)
Research Products
(13 results)
