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在南京航空航天大学低速风洞中用前缘后掠角分别为６５°和７０°三角翼模型，采用不同厚度和不同位置安装的类似后横向支架进行过失速非定常破碎涡的测定实验，涡及破碎点位置由ＴｉＣｌ４ 烟流显示，并用相机记录。实验表明，在非定常过失速情况下，涡的破碎位置与非定常气动力一样具有迟滞环特性。在同样攻角条件下，随着类似后横向支架的加高，或其位置越靠近三角翼模型后缘，无论静态、上仰、下俯，涡破碎点位置均更靠近三角翼模型前缘。
In the low speed wind tunnel of Nanjing University of Aeronautics and Astronautics, with the leading edge sweep angle of 65 ° and 70 ° delta wing model, the use of similar thickness and different positions of the rear bracket mounted staggering stalls unsteady broken vortex determination experiment, vortex And crushing point position by the TiCl4 smoke flow display, and recorded with the camera. Experiments show that the crushing position of the vortex has the characteristics of hysteresis loop as the unsteady aerodynamic force in the case of unsteady stalling. At the same angle of attack, with the increase of similar lateral support, or closer to the trailing edge of the delta wing model, no matter static state, uplifting, leaning over and vortex breaking point are closer to the leading edge of the delta wing model.