"A Study on Effects of High Temperature Chemical Reactions on Shock Induced Aerodynamic Heating of Hypersonic Vehicle"

“高温化学反应对高超声速飞行器激波气动加热影响的研究”

基本信息

批准号：
05650937
负责人：
ASO Shigeru
金额：
$ 1.34万
依托单位：
KYUSHU UNIVERSITY
依托单位国家：
日本
项目类别：
Grant-in-Aid for General Scientific Research (C)
财政年份：
1993
资助国家：
日本
起止时间：
1993 至 1994
项目状态：
已结题

项目摘要

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.

本研究的目的是研究高温对冲击波诱导的空气动力学加热现象的影响，这是在高超音速速度下在车辆周围观察到的。在本研究中获得的主要结果如下：1）由于高温影响振动能量和翻译能的作用。在内部能量振动中，可以考虑。对于温度模型振动，假定平衡条件。通过此模型进行了冲击波诱导的空气动力加热现象的数值模拟。比较了有或没有振动能的计算结果。结果表明，具有振动能量的空气动力学加热载荷远高于没有能量的能量，并且振动能的高温效应对于精确预测空气动力学加热负荷非常重要。2）由于高温模型解离反应。与氧气的解离反应的计算冲击波反射模式与实验表现出良好的一致性。同样，对于壁的催化条件，完全催化和完全非催化壁条件的催化条件也被考虑并相互检查。带有完全催化壁的空气动力学加热负荷远高于非催化壁。这意味着（总加热负荷）=（空气动力加热负荷） +（由于化学反应引起的额外加热负荷），有时（由于化学反应引起的额外加热负荷）有时会变得高于（空气动力学加热负荷）。在计算中（80％的氮气和20％氧气），也使用了良好的协议，并与实验者达成了良好的协议。上述结果表明，高温影响对于预测空气动力学加热负荷非常重要。