摘要
运用自主开发的数值模拟软件对高超声速进气道复杂内流场计算进行了数值模拟,以验证其对高超声速进气道流动模拟的适用程度。通过某二元高超进气道模型内流场,德国RWTH Aachen所公布的高超进气道模型内流场计算,对该软件描述高超声速进气道内波系反射相交、激波/边界层干扰、高反压下隔离段内激波串等复杂流动现象的能力进行了考核与分析。计算结果表明该软件能够描述高超声速进气道内复杂的流动现象,即使在进气道承受高的燃烧室反压时,仍具有较高精度。但该软件中的紊流模型不能较好地预报边界层分离,特别是对分离区的大小及其诱导激波的强度等的预测存在一定的误差,因此需要进一步的改进和完善。
To validate the software, a numerical study is carried out to investigate the hypersonic flows in the inlet. The calculational examples include a simulation of two-dimensional hypersonic laminar flows in the inlet and the calculation of two-dimensional hypersonic laminar flows in Germany RWTH Aachen inlet. This paper analyzes the capabilities of simulating the reflections and intersections of various shock waves, the shock wave/boundary layer interaction in the hypersonic inner and the shock train in the isolate under the high pressure. Results indicate that the software can describe the complex hypersonic flows in the inlet and reflect the flow when the inlet endures high the pressure of the eombustor. But the turbulence models by using the software can not exactly describe the separation of boundary layer, especially the size of the separation field and the strength of induced shock.
出处
《南京航空航天大学学报》
EI
CAS
CSCD
北大核心
2008年第5期605-610,共6页
Journal of Nanjing University of Aeronautics & Astronautics
关键词
高超声速飞行器
进气道
激波
边界层
hypersonic aerodynamics
inlet
shock waves
boundary layer
