Shock Tube Research on Oblique Shock Reflection Over a Dust Layer
| Project/Area Number |
01550051
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| Research Category |
Grant-in-Aid for General Scientific Research (C)
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| Allocation Type | Single-year Grants |
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| Research Field |
Aerospace engineering
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| Research Institution | Saitama Institute of Technology |
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Principal Investigator |
ADACHI Takashi Saitama Institute of Technology, Faculty of Engineering, Professor, 工学部, 教授 (30118658)
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| Co-Investigator(Kenkyū-buntansha) |
KOBAYASHI Susumu Saitama Institute of Technology, Faculty of Engineering, Associate Professor, 工学部, 助教授 (10170325)
SUZUKI Tateyuki Saitama Institute of Technology, Faculty of Engineering, Professor, 工学部, 教授 (20118665)
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| Project Period (FY) |
1989 – 1990
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| Project Status |
Completed (Fiscal Year 1990)
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| Budget Amount *help |
¥1,900,000 (Direct Cost: ¥1,900,000)
Fiscal Year 1990: ¥700,000 (Direct Cost: ¥700,000)
Fiscal Year 1989: ¥1,200,000 (Direct Cost: ¥1,200,000)
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| Keywords | Shock Wave / Dust Layer / Oblique Shock Reflection / Mach Reflection / Unsteady Flow |
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| Research Abstract |
Oblique reflection of a planar shock wave over a dust layer was investigated. Experiments were conducted using a shock tube, and waves were visualized through schlieren method. Angles of incidence and reflection were measured directly from negative films. Incident shock Mach number was fixed at 1.41. Mean diameter of spherical particles deposited on a wedge and depth of the dust layer were 30mum and 0.6mm respectively. Main conclusions are as follows :
1. Results were compared with those for two-dimensional guttered wedge, and following points of resemblance were revealed. (1) Unsteady behavior of incidence and reflection shows that the shock reflection over both the dust layer and two-dimensional guttered wedge is essentially unsteady phenomena. (2) Transition from regular to Mach reflection occurs as the incident shock propagates for constant incident shock Mach number and slope of wedge surface. (3) For the specified incident shock Mach number and slope of wedge surface where reflection pattern is Mach type for smooth surface, reflection in both cases remains regular type. This fact can be explained well by a modified two-shock theory taking account of "sink effect" of dust layer.
2. Experiments for the dust layer were compared with the modified two-shock theory. It is found that the relative flow velocity just behind the Mach stem or reflection point have a velocity component normal to the dusty surface. The deflection angles are about 4^O -6^O for Mach reflection and 8^O -14^O for regular reflection.
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Report
(3 results)
Research Products
(10 results)
