IMECH-IR  > 高温气体动力学国家重点实验室
乘波体前缘钝化途径
韩汉桥; 王发民; 张杰
Source Publication高温气体动力学研究进展
2011
Pages320-325
Conference NameLHD2011夏季学术研讨会
Conference Date2011
Conference Place内蒙赤峰
Abstract用指数率前缘代替传统圆弧形前缘给乘波飞行器提供了一种可能的钝化方式。本文利用数值方法对三维高超声速乘波体指数率前缘进行了研究,选取了一个乘波前体作为计算的物理模型,分别采用指数率前缘和传统的圆弧形前缘进行钝化,对两种不同钝化方式计算所得的气动力、热特性进行了对比分析。对于所考虑的计算工况,乘波体的指数率前缘所受到的阻力更小,同时它有一定的钝度以减轻热防护压力,并且可以通过选取适当的指数来调整前缘钝度,以满足热防护需求,可以为工程上高超声速飞行器前缘设计提供参考。
Keyword高超声速 气动热防护 指数率前缘 气动性能
DepartmentLHD高超声速空气动力学
Language中文
Document Type会议论文
Identifierhttp://dspace.imech.ac.cn/handle/311007/47955
Collection高温气体动力学国家重点实验室
Recommended Citation
GB/T 7714
韩汉桥,王发民,张杰. 乘波体前缘钝化途径[C]高温气体动力学研究进展,2011:320-325.
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