用多块搭接网格技术及雷诺平均N-S方程数值模拟跨音速翼型风洞流场.着重研究了不同驻室高度、不同引射缝高度以及实验段上下壁不同开闭比对风洞马赫数分布的影响.并研究了实验段上下壁干扰对翼型测压实验的影响.通过计算得到了最优的驻室高度、引射缝高度以及最优开闭比.计算结果表明,不同的驻室高度和引射缝高度对实验段马赫数分布有很大影响；而实验段上下壁开闭比对风洞实验段的阻塞度有很大的影响.随着开闭比的逐渐增加,翼型上的激波位置也逐渐向前移动.只有在合适的开闭比下,翼型的激波位置和压力峰值才与无干扰结果一致.研究结果对风洞建设和性能改进有一定的参考意义.%Some numerical investigations of the transonic wind tunnel test section flow field are presented with focus on its geometric parameters and top and bottom wall interference by solving steady Reynolds-averaged Navier-Stokes equation with SST k-ω turbulence model equations in multi-block grid discretization frame. Particular attentions has been paid to the effects of the plenum chamber height, the ejector slot height, and wall porosity on the Mach number distribution along the wind tunnel test section centerline. By numerical simulation, the optimal value of the plenum chamber height, the ejector slot height and the wall porosity have been found. The wall porosity also has considerable influence on the surface pressure distribution of the airfoil installed in the test section and to be tested. An optimal wall porosity can also be found to make the airfoil surface pressure distribution as close as possible to the blockage-interface-free data. The results are valuable to the transonic wind tunnel design and construc-tioa
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