高超声速稀薄过渡流气动热关联计算方法研究

【作者】 李四新；

【导师】 李桦； 彭治雨；

【作者基本信息】 中国人民解放军国防科学技术大学 ， 力学， 2002， 硕士

【摘要】 本文对高超声速稀薄过渡流气动热的关联参数和计算方法进入行了研究。对驻点区和飞行器表面不同的流动区域给出了流态划分准则。在理论分析的基础上，对通常广泛采用的稀薄气动热数据关联参数—Cheng’s参数进行了改进。通过耦合压力系数，建立了一组能应用于有攻角情况下高超声速飞行器表面稀薄气动热数据分析的关联参数，根据对现有的大量国内外低密度风洞实验数据的数据关联，用最小二乘法进行数据拟合，建立了计算有攻角情况下飞行器表面稀薄气动热的关联计算方法。为了计算任意三维外型飞行器表面的稀薄气动热，本文采用了无粘表面流线轴对称比拟法与稀薄气动热的关联计算方法相结合，建立了计算有攻角情况下飞行器表面稀薄气动热的工程计算方法。通过计算结果与实验结果的比较表明，计算的沿迎风母线、背风母线及沿周向的热流分布均与实验数据符合较好。更多还原

【Abstract】 A correlation method of heat transfer rate in hypersonic rarefied flow was present in this paper. Flow criterion was introduced for stagnation point region and the body of the vehicle. On the basis of therotical analysis, the raefied heat transfer rate correlation parameter-Cheng’s parameter was modified. A set of correlation parameters, which could be used to analysis rarefied flow heating to hypersonic vehicles with attack angle, has been established through coupling with pressure coefficient. According to correlating many Low-dencity wind tunnels experimental dates at home and abroad, the least squares procedure adopted to fit the data, a engineering method of rarefied heat transfer rates on the surface of vehicle with attack angle has been established. In order to calcalate rarefied heat transfer on the surface of arbitrariness configuration, combined the inviscid surface streamlines and axisymmtric annalog, the engineer calculational method of rarefied heat transfer on the surface of vehicle with attack angle was been established. Calculational results showed heat transfer rates (along upwind and leeside generatrix, circumferential direction) were well agreement with the experimental data.更多还原