悬停及小速度前飞状态下旋翼对机身及平尾气动特性的影响  

Effects of Rotor on Fuselage and Horizontal Tail Aerodynamicsin Hover and Low Speed Forward Flight

作　　者：孙正荣[1] 杨永东[1] 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《空气动力学学报》1999年第3期243-250,共8页Acta Aerodynamica Sinica

摘　　要：介绍了一副研究型旋翼 Ｚ９ 机身组合模型在 Ｃ Ａ Ｒ Ｄ Ｃ８ｍ ×６ｍ 低速风洞的试验概况，给出了悬停及小速度前飞时旋翼对机身气动特性的影响，着重讨论了水平尾翼对机身纵向气动特性的贡献。机身横截面上的不对称压力分布测量结果，揭示了旋翼在机身表面诱导的附加横侧向气动载荷的机理。An experimental study was conducted in CARDC 8m×6m low speed wind tunnel using a research rotor/Z9 fuselage combination model.Effects of rotor on fuselage aerodynamics in hover and low speed forward flight are presented in this paper.Contributions of horizontal tail to fuselage longitudanal aerodynamic charactreristics are emphatically discussed.Asymmetric circumferential fuselage pressure distribution revealed the mechanism of additional aerodynymic loads induced by rotor on fuselage surface.

关 键 词：旋翼 风洞试验 旋翼-机身 气动力干扰 直升机 

分 类 号：V211.52[航空宇航科学与技术—航空宇航推进理论与工程]