| Project/Area Number |
05650937
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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 | KYUSHU UNIVERSITY |
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Principal Investigator |
ASO Shigeru Kyushu University, Dept.Aero.& Astro. Associate Professor, 工学部, 助教授 (40150495)
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| Co-Investigator(Kenkyū-buntansha) |
KIHARA Hisashi Kyushu University, Dept.Aero.& Astro. Research Associate, 工学部, 助手 (60243911)
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| Project Period (FY) |
1993 – 1994
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| Project Status |
Completed (Fiscal Year 1994)
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| Budget Amount *help |
¥2,100,000 (Direct Cost: ¥2,100,000)
Fiscal Year 1994: ¥400,000 (Direct Cost: ¥400,000)
Fiscal Year 1993: ¥1,700,000 (Direct Cost: ¥1,700,000)
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| Keywords | Aerodynamic heating / High temperature effect / Shock wave / Spaceplane / Vibrational energy / Dissociation reaction / Hypersonic flow |
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| Research Abstract |
The purpose of the present study is to study of high temperature effects on shock wave induced aerodynamic heating phenomena, which are observed around vehicles at hypersonic speed. The major results obtained in the present study is as follows :
1) As high temperature effects the roles of vibration energy and translational energy are studied. In the internal energy vibrationa energy is considered. For the temperature model vibrationa equilibrium condition is assumed. Numerical simulation on shock wave induced aerodynamic heating phenomena with this model have been conducted. Calculated results with and without vibration energy have been compared. The results show the aerodynamic heating loads with vibrational energy is much higher than that without energy and high temperature effect of vibrational energy is very important for precise prediction of aerodynamic heating loads.
2) As high temperature model dissociation reaction is considered. Calculated shock wave reflection patterns with dissociation reaction of oxygen gas show good agreement with experiments. Also for the catalytic condition of the wall both of fully catalytic and fully non-catalytic wall conditions have been considered and checked each other. Aerodynamic heating load with fully catalytic wall is much higher than that of non-catalytic wall. This means in the formula of (total heating loads) = (aerodynamic heating load) + (additional heating load due to chemical reactions), (additional heating load due to chemical reactions) sometimes becomes higher than (aerodynamic heating load).
In the calculations air (80% nitrogen gas and 20% oxygen gas) is also used and good agreements with experiments have been obtained. Those above results show high temperature effects is very important for prediction of aerodynamic heating loads.
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