三维侧压高超声速进气道试验与计算研究

Experimental and numerical study on hypersonic inlet with 3-D side compression wedges

针对三维侧压高超声速进气道开展了试验与计算研究。试验在中国航天空气动力技术研究院的高超声速脉冲风洞中进行,在试验中,来流马赫数为6,文中采用三维有限体积并行计算程序对风洞试验条件下的流动进行了数值模拟,采用k-g湍流模型,时间迭代采用LU隐式格式,对流通量采用了AUSM+、AUSMPW两种不同的空间离散格式进行了对比计算研究,结果表明两个不同的格式都能较好地模拟进气道流场。顶板中心线和离开中心线0.02m位置处的压力分布计算值和试验结果基本一致,表明AUSM+、AUSMPW格式的激波分辨率较高,粘性耗散比较低。计算结果还显示在侧压板壁面出现激波诱导边界层分离现象。

The 3-D hypersonic inlet with side compression wedges was experimentally and numerically studied.The test was carried out in the hypersonic pulsed wind tunnel in China Academy of Aerospace Aerodynamics.The free stream Mach number was 6.The numerical simulation of the inlet has also been carried out by the 3-D finite-volume parallel computational procedure.In the study,k-g turbulence model and LU implicit approach were adopted,AUSM＋ and AUSMPW spatial discrete methods were adopted for comparison.The result indicates that both methods can simulate the inlet field.The calculated pressure distributions along central line of the upper wall and 0.02m apart the central line are in general agreement with the experimental data,which indicates that the shockwave resolution of AUSM＋ and AUSMPW is high and their viscosity dissipation is relatively lower.The numerical results also demonstrate that the shockwave induces boundary layer separation on the side wall.