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"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高超音速飞行器周围激波诱导的气动加热现象的影响。主要研究结果如下：1）研究了高温效应中振动能和平动能的作用。在内能振动中，考虑了能量。对于温度模型振动，假定了一个平衡条件.利用该模型对激波诱导的气动加热现象进行了数值模拟。计算结果与无振动能量的结果进行了比较。结果表明，考虑振动能时的气动热载荷远高于不考虑振动能时的气动热载荷，振动能的高温效应对气动热载荷的精确预测至关重要。计算得到的氧气离解反应的激波反射图与实验结果吻合较好。对于壁面的催化条件，考虑了完全催化和完全非催化两种壁面条件，并进行了相互校核。全催化壁面的气动热负荷远高于非催化壁面。这意味着在总热负荷=气动热负荷+化学反应附加热负荷的公式中，化学反应附加热负荷有时会大于气动热负荷，计算中也采用了空气（80%氮气和20%氧气），与实验结果吻合较好。以上结果表明，高温效应对气动热载荷的预测是非常重要的。