Within the framework of linear subsonic theory, the problem of determining the effect due to wall interference on the flow around airfoil according to the pressure distributions measured on the airfoil and on the wind-tunnel test section walls is solved. For the test case (testing a BGK1 airfoil in the IAR1.5m wind tunnel), we compared the wall interference corrections to freestream Mach number and airfoil angle-of-attack that were obtained using our method and in the works by other authors. For an OSPB-77 airfoil model tested in the T-128 wind tunnel for two values of wall permeability, f = 0 and 3 %, corrections to distributed data and integral loads were applied in the range of Mach numbers from 0.2 to 0.78. The application of those corrections has made it possible to bring the results for f = 0 and f = 3 % in closer agreement up to the angles of attack at which flow separation occurs on the airfoil.

在线性亚音速理论的框架内，解决了根据翼型和风洞测试段壁上测得的压力分布确定壁面干扰对翼型周围流动的影响的问题。对于测试用例（在 IAR1.5m 风洞中测试 BGK1 翼型），我们将壁干涉修正与使用我们的方法和其他作者的作品获得的自由流马赫数和翼型攻角进行了比较。对于在 T-128 风洞中针对两个壁渗透率值（f = 0 和 3%）测试的 OSPB-77 翼型模型，在 0.2 至 0.78 马赫数范围内应用了对分布式数据和积分载荷的修正。这些修正的应用使得f = 0 和f = 3 % 的结果与翼型上发生流动分离的攻角更加一致。