环量控制尾梁是无尾桨直升机反扭矩新技术。为了研究不同参数对环量控制尾梁的影响 ,设计制造了两个环量控制尾梁模型 ,本文介绍了该模型分别在风洞中和旋翼下进行的分布压力测量实验。通过对实验结果的分析、讨论 ,阐述了动量系数、缝隙几何参数以及相对来流速度等参数对环量控制尾梁上气动力的影响 ,并从理论上对实验结果进行了合理的解释。 Ring control tail boom is a new technology of tail rotor helicopter anti-torque. In order to study the influence of different parameters on the annular control tail boom, two annular control tail beam models are designed and manufactured. The paper introduces the distributed pressure measurement experiment of the model under wind tunnel and rotor respectively. Through the analysis and discussion of the experimental results, the influence of the momentum coefficient, the geometrical parameters of the slot and the relative flow velocity on the aerodynamics of the annular beam is theoretically explained. The experimental results are explained theoretically.