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本文利用底部外侧周向多孔排气的方法研究具有圆柱后体的超声速旋成体底部流动特性及减阻问题。研究工作在超声速风洞进行，来流马赫数从１．５３到３．０１，单位雷诺数为２．２×ｌ０￣７／ｍ到２．８×ｌ０￣７／ｍ。文中讨论了排气流量、气体介质对尾流结构与波系分布的影响，对底部增压减阻的效果，测量了底压分布，拍摄了尾流场纹影。实验结果分析表明，采用此种方法能够有效地干扰尾流边界，控制尾流特性，其中氦气在最佳排气流量情况下，收到减少底阻约２０％左右的良好效果。
In this paper, we study the bottom flow behavior and drag reduction of a supersonic rotary body with a cylindrical rear body by means of a peripheral porous exhaust at the bottom. Research work in the supersonic wind tunnel, Mach Mach number from 1.53 to 3.01, the unit Reynolds number 2.2 × l0 ~ 7 / m to 2.8 × l0 ~ 7 / m. In this paper, the influence of the exhaust gas flow, the gas medium on wake structure and the wave system distribution is discussed. The effect of pressure increase and drag reduction at the bottom is measured. The bottom pressure distribution is measured and the wakes of the wake field are recorded. Experimental results show that this method can effectively disturb the wake boundary and control the wake characteristics. Among them, helium gas has a good effect of reducing about 20% of the base resistance at the best exhaust flow rate.