高超声速多突起物干扰研究
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摘要
利用N-S数值计算解法对高超声速气流中多突起物互相干扰流场进行了计算,对单一梯形截面突起物和锥形凸台干扰下的两种情况下的流场进行对比分析,研究了其流动机理和流场结构,结果表明锥形凸台干扰下的梯形截面突起物侧面压力远大于单一梯形截面的突起物附近的压力,热环境更加恶劣。
The hyposonic flows around the Muti-protuberance structure and single protuberance is numerically simulated ith Navier-Stokes solver.Compare with the difference of pressure between the single echelon section and multi-protuberance of echelon section and cone platform.Flowfield structure and flow mechanics is analysised.It is found that the pressure and aeroheat of multi-protuberance are more than the single protuberance.
The hyposonic flows around the Muti-protuberance structure and single protuberance is numerically simulated ith Navier-Stokes solver.Compare with the difference of pressure between the single echelon section and multi-protuberance of echelon section and cone platform.Flowfield structure and flow mechanics is analysised.It is found that the pressure and aeroheat of multi-protuberance are more than the single protuberance.
引文
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[11]张翔,阎超,杨威,等.高超声速飞行器气动热网格依赖性研究[J].战术导弹技术,2016,(3):21-27.
[2]Holden M S,Buffalo.A study of flow separation in regions of shock wave-boundary layer interaction in hypersonic flow[C].American institute of aeronautics and astronautics,fluid and plasma dynamics conference,11th,Seattle United States,1978:1-21.
[3]Holden M,Maclean M,Wahdams T,et al.Experimental studies of shock wave/turbulent boundary layer interaction in high reynolds number supersonic and hypersonic flows to evaluate the performance of CFD codes[C].40th fluid dynamics conference and exhibit,Chicago,IL,United states,2010.
[4]范绪箕,董葳.飞行器突起物周围气动加热的计算方法[J].宇航学报,1998,19(1):98-101.
[5]马汉东,李素循,吴礼义.高超声速绕平板上直立圆柱流动特性研究[J].宇航学报,2000,21(1):1-5.
[6]李素循.激波与边界层主导的复杂流动—华夏英才基金学术文库[M].北京:科学出版社,2007.
[7]冈敦殿,易仕和,赵云飞.超声速平板圆台突起物绕流实验和数值模拟研究[J].物理学报,2015,64(5):1-8.
[8]阎超.计算流体力学方法及应用[M].北京:北京航空航天大学出版社,2007.
[9]阎超,禹建军,李君哲.热流CFD计算中格式和网格效应若干问题研究[J].空气动力学学报,2006,24(1):125-130.
[10]董素君,居世超,齐玢.气动热计算模型及网格效应分析[J].航空计算技术,2011,41(2):40-42.
[11]张翔,阎超,杨威,等.高超声速飞行器气动热网格依赖性研究[J].战术导弹技术,2016,(3):21-27.