在NF-3风洞的二元试验段开展了翼型极大迎角(±180°)条件下气动特性的试验技术研究。针对翼型极大迎角风洞试验的洞壁干扰,提出了风洞壁压信息洞壁干扰修正的改进方法。试验结果表明,发展的试验技术和提出的洞壁干扰修正方法适合于翼型极大迎角试验。 The experimental study on the aerodynamic characteristics under the condition of maximum angle of attack (± 180 °) of airfoil was carried out in the dual test section of NF-3 wind tunnel. Aiming at the tunnel wall disturbance in the airfoil at high angle of attack wind tunnel, an improved method to correct the tunnel wall pressure disturbance is proposed. The test results show that the developed test technique and the proposed method of correction of the wall interference are suitable for the maximum angle of attack of the airfoil.