高超声速气动热的耦合计算方法研究  

Coupled Flow-thermal Analysis Approach for Hypersonic Aerodynamic Heating

作　　者：赵晓利[1] 孙振旭[2] 安亦然[2] 郑钢铁[1] 

机构地区：[1]清华大学航天航空学院,北京100084 [2]北京大学工学院,湍流与复杂系统国家重点实验室,北京100871

出　　处：《科学技术与工程》2010年第22期5450-5455,5461,共7页Science Technology and Engineering

摘　　要：为了准确预测高超声速飞行器承受的气动热载荷,需要进行流动-传热耦合分析。采用耦合传热方法,考虑流体流动和结构传热之间的实时相互影响,对圆柱壳高超声速气动加热风洞实验进行了三维非定常数值模拟,将数值模拟结果与实验结果进行了全面对比,得到的表面压力、冷壁热流、热壁热流和温度分布与实验结果符合良好,验证了耦合计算方法的准确性,提高了气动热模拟精度,实现了气动加热的准确计算。The accurate prediction of aerodynamic heating for hypersonic vehicle depends on coupled flow-thermal analysis.A new flow-thermal coupling approach based on coupled heat transfer simulation is applied to the analysis of hypersonic aerodynamically heated leading edge,interactions between flow and structural heat transfer is studied.The three-dimensional unsteady flow-thermal coupling is studied for Mach Number 6.47 flow over a cylinder for which the flow behavior and aero-thermal loads are calibrated by experimental data,and the numerical results of surface pressure,cold-wall heating-rate,hot-wall heating-rate and temperature distributions are all well consistent with experimental data.The results show that an accurate prediction of aero-thermal loads for hypersonic vehicles can be achieved with the developed method.

关 键 词：气动热 耦合 高超声速 

分 类 号：V411.4[航空宇航科学与技术—航空宇航推进理论与工程]