战斗机模型大迎角风洞实验的雷诺数影响实验研究  

The Experimental Investigation on Reynolds Number Effects on Aerodynamics Data of Fighter Models in Wind Tunnels at High Angles of Attack

作　　者：程厚梅[1,2] 杨希明[1,2] 孙绍鹏[1,2] 

机构地区：[1]沈阳空气动力研究所 [2]中国空气动力研究与发展中心

出　　处：《流体力学实验与测量》1999年第2期30-37,共8页Experiments and Measurements in Fluid Mechanics

摘　　要：介绍了两个战斗机模型大迎角风洞实验雷诺数对实验数据的影响，分析了造成这种影响的原因以及为获得能反映高雷诺数流动特点的稳定气动数据所采用的实验模拟技术，重点描述了雷诺数对大迎角俯仰力矩、零侧滑偏航力矩和滚转力矩的影响，探讨了零侧滑偏航力矩（Ｃｎ０）对不同的模型头部构型随侧滑角变化的迁移情况。对于大迎角飞行的歼击机，雷诺数的影响不只在风洞实验中存在，在飞机试飞过程中也存在，地面模拟设备应最大限度地提高模拟能力，准确预测雷诺数的影响，给出稳定可靠的实验数据。Reynolds number effects on experimental aerodynamics data of two fighter models in wind tunnels at high angels of attack are given in the paper.After analyzing the reasons resulting in unstable aerodynamics data,testing techniques were developed in order to obtain stable data which behave as high Reynolds number characteristics.The Reynolds number effects on the pitching and yawing moments at zero angles of sideslip and high angles of attack were paid important attention.The zero sideslip yawing moments moving with angles of sideslip at high angles of attack for two different models were described.As far as fighter with supermaneuvarability the Reynolds number effects not only exist in wind tunnel but also in flight testing.The simulation capabilities of wind tunnels should be as high as possible increased in order to forecast Reynolds number effects and supply accurate and reliable data.

关 键 词：雷诺数 歼击机 风洞实验 大迎角 

分 类 号：V211.4[航空宇航科学与技术—航空宇航推进理论与工程] V211.71