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在４ｍ×３ｍ低速风洞中研究了空气动力对战斗机内藏式导弹弹射分离轨迹的影响。采用简单网格法测量了导弹在干扰流场中的气动力，进行了分离轨迹估算，用捕获轨迹试验得到了分离轨迹，选定了最佳弹射力参数。试验结果表明，实验导弹安全分离必须采用弹射力，气动俯仰力矩是影响导弹姿态的重要因素，气动力对分离位置影响较小。
The effect of aerodynamics on the trajectory of the missiles of the embedded missiles of fighter jets is studied in a 4m × 3m low speed wind tunnel. The aerodynamic force of the missile in the disturbed flow field was measured by the simple grid method, the separation trajectory was estimated, and the separation trajectory was obtained by the capture trajectory test. The optimal ejection parameters were selected. The experimental results show that the ejection force must be used for the safe separation of experimental missiles, and the aerodynamic pitching moment is an important factor that affects the attitude of the missile. The aerodynamic force has little influence on the separation position.