| Project/Area Number |
09650177
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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 |
YAMAMOTO Satoru Division of Engineering, Tohoku University, Associate Professor, 大学院・工学研究科, 助教授 (90192799)
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| Project Period (FY) |
1997 – 1999
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| Project Status |
Completed (Fiscal Year 1999)
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| Budget Amount *help |
¥2,900,000 (Direct Cost: ¥2,900,000)
Fiscal Year 1999: ¥1,000,000 (Direct Cost: ¥1,000,000)
Fiscal Year 1998: ¥900,000 (Direct Cost: ¥900,000)
Fiscal Year 1997: ¥1,000,000 (Direct Cost: ¥1,000,000)
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| Keywords | Fluid Dynamics / Compressible Flow / Unsteady Flow / Non-perfect Gas / Shock Wave / Vortex / Shock / vortex Interaction / Numerical Method / 圧縮性流れ / 過干渉 |
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| Research Abstract |
1. Numerical method of unsteady hypersonic shock/shock interference flows considering thermochemical nonequilibrium effect was developed. The fourth-order compact MUSCL TVD scheme coupled with AUSM_DV in space and maximum second-order LU-SGS scheme in time enable us to capture unsteady high-temperature shock-shock interference flows quite stably.
2. Numerical method of unsteady transonic shock/vortex interaction flows considering relative humidity was developed. The classical condensation theory is applied to newly derived fundamental equations for gas-liquid two phase flows. Nonequilibrium condensations appear around a high angle of attack airfoil in very humid condition were successfully calculated using the present method.
3. Computational code of unsteady three-dimensional hypersonic shock/shock interference flows was developed. Hypersonic flows around a blunted fin on the flat plate were calculated and the unsteady flow mechanism which indicates why they become unsteady flows is clearly explained.
4. Computational code of three-dimensional condensation cloud around wing was developed. The nonequilibrium condensation around the 3-D wing in humid condition, so-called 'condensation cloud', was successfully calculated.
5. Computational code of unsteady three-dimensional hypersonic shock/shock interference flows with thermochemical nonequilibrium effect was developed. The calculated results indicate the importance of considering the chemical reaction also in 3-D cases. The shock stand-off distance decreases dramatically and the heating rate is considerably changed in the high-temperature condition.
6. Computational code of axisymmetric magnet-plasma viscous flows was developed. An efficient implicit method for solving flow equations and the induced equation of magnetic field simultaneously.
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