弹体脉动压力特征的实验研究  

Experimental research of fluctuating pressure on surface for a certain missile configuration

作　　者：王娜[1] 高超[1] 

机构地区：[1]西北工业大学翼型叶栅空气动力学国家级科技重点实验室,陕西西安710072

出　　处：《实验流体力学》2010年第1期30-35,共6页Journal of Experiments in Fluid Mechanics

基　　金：国家973计划资助项目(61355)

摘　　要：针对弹体模型进行了表面脉动压力特性实验研究,实验马赫数M∞=0.8、0.84、0.86、0.92、1.0、1.15、2.0、2.5,实验迎角α=-5°、-3°、0°、3°、5°,沿弹体轴向测量了14个特征点的脉动压力,得到了弹体表面测点的脉动压力系数、频谱曲线以及相关性系数等实验数据。结果表明:脉动压力系数总体上随马赫数增加而降低。不同马赫数,迎角α=0°的条件下沿轴向各测点压力脉动之间的空间相关性有类似的分布规律,且各测点脉动压力基本互不相关。在实验的迎角下,脉动压力系数在弹体表面曲率变化较小的位置基本上不随来流迎角的改变而变化,膨胀拐角肩部位置的脉动压力系数随着迎角的改变而变化较大。超声速来流的功率谱能量峰值所对应的主频出现明显的低频特征;跨音速来流时特征频率随着马赫数的增加而增大,功率谱能量峰值位于特征频率处。The characteristics of fluctuating pressure for a certain missile configuration are studied. TheMach number is M∞ =0.8、0.84、0.86、0.92、1.0、1.15、2.0、2.5,实验迎角α=5°3°、0°、3°、5°, there were 14 testing holes on the surface along the axes of this missile configuration. Dtailed information for fluctuating pressure coefficient, power spectrum density and spatial correlation has been acquired. The results of the experiment indicate that the fluctuating pressure coefficient reduced with the Math number increasing. The fluctuating pressure has the similar axial cross correlation for any two of the testing points along the axes of this missile configuration at different Mach number. The aixal cross correlation for different testing points along the axes of this missile configuration at zero angle of attack can be neglected. In the range of angle of attack, different angle of attack has little influence over the fluctuating pressure coefficient in the region of small curvature changes. The fluctuating pressure coefficient varies obviously under different angle of attack in the region of remarkable curvature changes. The power spectrum density shows that the character frequency is obvious low at supersonic, and the character frequency increases with the Math number increasing, and the maximum power spectrum density located at the location of character frequency.

关 键 词：飞行参数 脉动压力 特征频率 功率谱密度 相关性系数 

分 类 号：V211.753[航空宇航科学与技术—航空宇航推进理论与工程]