The key test technique for aerodynamics of fighter at high angle of attack in φ3.2m low speed wind tunnel has been introduced, including model attitude correction technique at the condition of oscillation, stall flutter restrainability technique for wind tunnel models supported by wire sting, real time measurement technique of wind speed and so on. A continuous sweep test technique has been developed and successfully applied in the force measurement test of a fighter model at high angle of attack. The test results indicated that these key test technique could meet the needs of wind tunnel test for advanced fighter at high angle of attack.%介绍了中国空气动力研究与发展中心低速所Φ3.2m风洞战斗机大迎角试验技术,包括振动条件下倾角传感器迎角测量修正技术、大迎角振动抑制技术、实时速压测量技术等.某飞机模型大迎角连续扫描测力试验结果表明,Φ3.2m风洞战斗机大迎角试验技术能够满足先进战斗机大迎角气动特性风洞试验需求.
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