无尾桨直升机实验研究(英文)

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。

EXPERIMENTAL STUDY ON NO TAIL ROTOR (NOTAR) HELICOPTER

The circulation control tail boom is a new technology used as an anti-torque system for the no tail rotor helicopter. In order to study the effect of the different parameters on the circulation control tail boom, two models with the different circulation control tail booms are designed and constructed. The experiments are introduced in this paper by measuring the pressure distribution on the models in wind tunnel and under main rotor, respectively. By analyzing and discussing the experimental results, the effects of the momentum coefficient, the slot′s geometry parameters and the freestream velocity on the aerodynamic forces of the circulation control tail boom have been expounded, and the reasonable explanations about the test result have been given in theory.