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该洞壁干扰修正方法以实测的洞壁附近的压力分布作为边界条件；要求来流和洞壁附近的Ｍａｃｈ数都小于１；但允许模型附近出现局部超音速区和激波。它适用于各种透气壁或实壁实验段。应用该方法对国外三个模型的实验数据进行了洞壁干扰修正计算，修正结果与ＮＡＳＡ非线性洞壁干扰修正方法的结果十分接近或完全吻合。该方法已用于Ｂ７３７模型在１．２ｍ风洞中实验数据的洞壁干扰修正，其结果显示该方法适用于大展弦比飞机的跨音速风洞实验数据修正。
The wall-interference correction method takes the measured pressure distribution near the wall as the boundary condition; it is required that the Mach numbers near the flow and the wall be less than 1; however, the local supersonic region and shock waves are allowed to appear near the model. It is suitable for a variety of ventilation wall or solid wall experimental section. Applying this method, the experimental data of three foreign models are calculated and corrected for the interference of the tunnel wall. The results of the correction are in close agreement with those of the non-linear correction method of the NASA tunnel wall. The proposed method has been used to correct the borehole disturbance of experimental data of B737 model in a 1.2m wind tunnel. The results show that this method is suitable for the experimental data correction of transonic wind tunnel with large aspect ratio aircraft.