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介绍了带环量控制尾梁的直升机模型在风洞中和旋翼下的测压实验。根据测量数据计算出尾梁上气动力随环量控制参数的变化情况，并绘制成曲线。主要研究动量系数和缝隙几何参数对圆柱尾梁上气动力的影响；另外，对环量控制尾梁上的流动状态也进行了显示实验。通过对实验结果的分析，研究环量控制尾梁的原理及应用，对实验中发现的现象和实验结果从理论上给出了合理的解释并作出新的探索。
The helicopter model with ring control tail boom is introduced to measure the pressure in the wind tunnel and under the rotor. According to the measured data, the aerodynamic force on the tail boom is calculated according to the control parameters of the loop volume and plotted as a curve. The main research is the influence of the momentum coefficient and the geometrical parameters on the aerodynamics of the cylindrical tail beam. In addition, the flow state on the tail beam of the annular control is also demonstrated. Through the analysis of experimental results, the principle and application of annular control tail beam are studied. The phenomena and experimental results found in the experiment are theoretically given reasonable explanations and made new exploration.