旋转流场下的振荡动导数试验技术研究  

Investigation of test technique of oscillatory dynamic derivative in rotational flow field

作　　者：吴金华[1] 孙海生[1] 沈志洪[1] 姜裕标[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：《实验流体力学》2014年第4期54-58,共5页Journal of Experiments in Fluid Mechanics

摘　　要：为研究飞机在旋转流场下的非定常气动特性,中国空气动力研究与发展中心低速所在Φ5m立式风洞开展了旋转流场下的振荡动导数试验技术研究。本文推导了在旋转流场下识别组合动导数的方法,介绍了试验设备,获得了在旋转的同时,由振荡产生的3个组合动导数,并对试验结果进行了分析与讨论。将单自由度动导数结果与Φ3.2m风洞试验结果进行了对比,旋转/振荡耦合试验结果表明:旋转运动使得俯仰组合动导数变得不稳定,而对于横向组合动导数,大转速则会显著增大非线性。该试验技术能够为研究旋转流场下的非定常气动特性提供一个有效的试验平台。In order to study the unsteady aerodynamic characteristics of aircraft in spin,a kind of test technique of oscillatory dynamic derivatives in rotational flow field is developed in the low speed institute of China Aerodynamics Research and Development Center.The method of acqui-ring combined dynamic derivatives is deduced,the description of test facilities is given,the com-bined dynamic derivatives due to oscillation are measured,and test results are analyzed and dis-cussed.The results of single-degree-of-freedom dynamic derivatives are compared to the results obtained in Φ3.2m wind tunnel.The results acquired in those rotation/oscillation coupling tests indicate that：rotary movement make the pitching combined dynamic derivative unsteady,and high rotation speed increases the nonlinearity of horizontal combined dynamic derivative.This test technique provides an effective method for studying unsteady dynamic characteristics of spin.

关 键 词：旋转流场 振荡 动导数 尾旋 风洞试验技术 

分 类 号：V211.71[航空宇航科学与技术—航空宇航推进理论与工程]