中文摘要：

采用经可压缩修正后的标准k-ε湍流模型对一类高超声速飞行器模型的气动特性进行了研究。计算中主要考虑了马赫数和飞行攻角的影响。计算结果表明,通过可压缩性修正,标准k-ε湍流模型能准确捕捉激波结构和复杂的压力变化规律;在激波系和预压缩面间构成的流动域内形成了高压均匀流动,实现了飞行器设计目标;在激波结构和激波发展趋势方面,计算结果和实验数据符合得很好,而两者在前体预压缩面上的压比值方面略有差异;经可压缩性修正后湍流模型的计算结果要明显优于原始湍流模型,可作为高超声速气动计算的有效方法。

英文摘要：

A series of numerical analyses have been performed to investigate the flow characteristics of a hypersonic vehicle model. Flow fields corresponding to the Mach number and attack angle were analyzed by solving the Reynolds averaged Navier- stokes equations with the stand k-6 turbulence model in which the compressibility effects were considered. With the correction of compressibility effects,the standard k-8 turbulence model can capture delicate shock wave structures and complex pressure variation characteristics, and their calculation results are in highly agreement. The calculated shock wave structures and pressure variation tendency agree well with experimental data, except for some differences in the variation of the static pressure on the pre-compressed surface. Compared with the original k-8 turbulence model, the improved model with compressibility effects correction obtains more accurate data, implying the validity and effectiveness of the numerical approach for analyzing relevant flow field.