高超声速气动热的耦合计算方法研究

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.

Coupled Flow-Thermal Analysis Approach for Hypersonic Aerodynamic Heating

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 presented in this paper shows that an accurate prediction of aero-thermal loads for hypersonic vehicles can be achieved with the developed method.