摘要
平尾纵向气动特性数据是直升机研制过程中飞行品质和载荷等计算的设计输入。采用CFD计算方法对某型无人直升机的机身气动特性进行了计算,包括无侧滑、小侧滑、中等侧滑和大侧滑状态;之后提取出单独平尾的纵向气动特性数据;然后对单独平尾纵向气动特性的CFD计算值与风洞试验结果进行了对比分析,分别采用增量法和比值法分析了两者的相关性。结果表明,平尾纵向气动特性CFD计算值的变化趋势与风洞试验结果一致。在大攻角范围内,两者的差值比较大,但是两者的比值比较稳定。在小侧滑和中等侧滑状态,两者的比值比较小。研究结果可为平尾气动设计和气动特性CFD计算结果的修正提供一定的参考。
The horizontal tail longitudinal aerodynamic characteristics data is the design input for the calculation of flight quality and load during the research and development of helicopter.CFD calculation was used to calculate the aerodynamic characteristics of the fuselage of one unmanned helicopter,and the calculation status included no sideslip,small sideslip,medium sideslip and large sideslip.Then extracted the longitudinal aerodynamic characteristics of horizontal tail only.The CFD calculation value of the longitudinal aerodynamic characteristics of horizontal tail only was compared with the wind test results.Finally,the incremental method and the ratio method were used to analyze the correlation between the two.The results showed that the change trend of the CFD calculation value of the longitudinal aerodynamic characteristics of horizontal tail only was consistent with the wind test results.In the range of a large angle of attack,the difference between the two was relatively large,but the ratio between the two was relatively stable.In the state of small and medium sideslip,the ratio of the two was relatively small.The research results could provide a certain reference for the aerodynamic design and the correction of the CFD calculation value of the aerodynamic characteristics of horizontal tail.
作者
龙海斌
吴裕平
LONG Haibin;WU Yuping(China Helicopter Research and Development Institute,Jingdezhen 333001,China)
出处
《直升机技术》
2021年第1期8-12,共5页
Helicopter Technique
关键词
直升机
平尾
纵向气动特性
CFD计算
风洞试验
helicopter
horizontal tail
longitudinal aerodynamic characteristics
CFD calculation
wind tunnel test
