缝道流动的脉动参数对多段翼型升力特性的影响  

The influence of dynamic parameters of gap flow on lift characteristics of a multi-element airfoil

作　　者：高永卫[1] 朱奇亮[1] 罗凯[1] Gao, Yong-Wei[1]; Zhu, Qi-Liang[1]; Luo, Kai[1]

机构地区：[1]西北工业大学翼型研究中心111#,西安710072

出　　处：《实验流体力学》2012年第6期15-18,共4页Journal of Experiments in Fluid Mechanics

基　　金：国家自然科学基金资助项目(10972184)

摘　　要：采用风洞实验的方法,在不停风且固定迎角和几何构型的情况下,通过对比有、无人为脉动压力扰动时多段翼型升力特性的变化,证明多段翼型缝道流动的脉动参数(包括脉动速度和脉动压力)对其升力特性有着不可忽视的影响。人为扰动源为模型表面埋设的有源式蜂鸣器。蜂鸣器出口20mm处的声压级约为60dB。实验表明,在研究范围内,弱声学扰动可使翼型的升力系数降低。升力系数的减少量随扰动的位置、频率变化而变化,最大减少量为1.8%。提出在多段翼型的实验评估工作中需要注意风洞本底噪声、模型尺度、加工质量对缝道脉动压力和脉动速度等参数的影响以及相应升力特性的变化。The dynamic parameters of gap flow of a multi element airfoil have significant effect on its lift characteristics, Using wind tunnel experiments, the authors compared the changes of lift coefficients of a multi-element airfoil （GAW-1） under conditions of acoustic excitation on/off. The experiments were conducted in NF-3 wind tunnel. The sound pressure level （SPI,） of internal acoustic excitation was 60dB. The results showed that the lift coefficients of the airfoil were reduced when disturbance were appended. The most decrement of lift coefficient is-1.8%. This paper confirms that the designers should study the dynamic characteristics of flow near the gap. It should be noticed that the sources of error in experiment data analysis should include scale and quality of test model and the back ground sound pressure level of the wind tunnel.

关 键 词：多段翼型 升力特性 风洞实验 缝道流动 脉动参数 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]