跨声速风洞不同参数开孔壁对实验段流场品质影响很大，孔壁参数特性的研究对于设计跨声速风洞实验段极其重要。在不同实验段壁压差系数下，对FL-3风洞单直孔壁在二维与三维模型下得到了质量流量与速度分量线性关系。因此提出了在满足壁压差系数和边界层位移厚度等条件下，二维孔壁流动特性可通过系数变换等效为三维孔壁的流动特征参数。在二维与三维孔壁特征参数对应的基础上，对实验段多孔壁进一步研究了在二维简化模型下孔壁参数及来流马赫数对实验段内流场及壁面附近流动特征的影响规律。在l/d＝1时增大孔尺寸d＝1、2、4，ΔC_p从0.001增大到0.004 5，S/d从4%减小到2.5%。增大孔长径比l/d＝1、2、3、4，ΔC_p在l/d>2时趋于不变，在l/d＝3时m′和S/d为最大值。m′与Ma呈正相关变化，在Ma＝0.8 ~ 0.9，提高来流马赫数对壁压差系数影响很小。二维与三维模型流动特征参数转换及孔壁参数研究对于深入理解孔壁流动和计算实验段多孔壁具有一定意义。

The perforated walls of transonic wind tunnels with different parameters have a considerable influence on the flow field quality of the test section, therefore, the characterization of the perforated wall parameters is extremely essential for the design of the test section of transonic wind tunnels. The relationship between the characteristic parameters near the perforated wall of three-dimensional and two-dimensional perforated wall models was studied using the single straight perforated hole of the FL-3 wind tunnel. The mass and velocity distributions of the two-dimensional and three-dimensional perforated wall show obvious linear characteristics under different pressure difference coefficients. It is proposed that the two-dimensional perforated wall can be equivalent to the flow characteristic parameters of the three-dimensional perforated wall by the corresponding coefficient transformation under the same incoming flow Mach number when the wall pressure difference coefficient and the boundary layer displacement thickness are satisfied. A two-dimensional calculation model of the transonic wind tunnel was established, and the effects of perforated wall parameters and free stream Mach number on the flow field and flow characteristic parameters near the wall in the test section were analyzed by numerical method. When l/d = 1, the increase in perforated wall size makes the wall pressure difference coefficient increase, otherwise, the relative area of flow in the perforated wall decreases. As d = 2 mm, the flow field was proposed. When l/d > 2, ΔC_p tends to be stable. When l/d = 3, m′ and S/ d are the maximum values, in the Ma = 0.8 ~ 0.9 range, m′ is positively correlated with the incoming Mach number, but ΔC_p changes little. The pressure difference coefficient and velocity component obtained under different perforated wall parameters have certain guiding significance for understanding the perforated wall flow and adjusting the perforated wall of the test section.