To study the effects of Mach number, Reynolds number and deflection angle on the conical separation vortex generated by swept shock wave/turbulent boundary layer interaction , the experimental and numerical simulation methods are used. The Mach numbers are Ma $=2.95$ and Ma $=4$. The deflection angles are $12°$, $15°$ and $18°$. The incoming boundary layer thickness ${\delta }_{0.99}$ is 4.6 mm, 23 mm and 115 mm. The evolution characteristics of the vortex, including the vortex core position, the vortex area and the vortex intensity, and the effects of Mach number, Reynolds number and deflection angle on them are analyzed. The results show that the core trajectory of the vortex is distributed along the rear shock foot line of the $\lambda$ shock structure. The Reynolds number is the main factor affecting the separation vortex core. The vortex area increases linearly along the direction of the inviscid shock, and the Reynolds number and the Mach number both are the factors affecting the growth rate of the separation vortex. The vortex intensity increases linearly along the direction of the inviscid shock. The vortex intensity is mainly affected by the Mach number and the deflection angle, but is not affected by the Reynolds number.

为了研究马赫数、雷诺数和偏转角对扫掠激波/湍流边界层相互作用产生的锥形分离涡的影响，采用了实验和数值模拟的方法。马赫数是Ma $=2.95$和马 $=4$. 偏转角为$12°$,$15°$和$18°$. 传入边界层厚度${\delta }_{0.99}$是 4.6 毫米、23 毫米和 115 毫米。分析了涡的演化特征，包括涡核位置、涡面积和涡强度，以及马赫数、雷诺数和偏转角对其的影响。结果表明，涡流的核心轨迹沿后震脚线分布。$\lambda$冲击结构。雷诺数是影响分离涡核的主要因素。涡面积沿非粘性激波方向呈线性增加，雷诺数和马赫数都是影响分离涡增长速度的因素。涡流强度沿非粘性激波方向线性增加。涡流强度主要受马赫数和偏转角的影响，不受雷诺数的影响。