Theoretical Considerations of Sidewall Interference Corrections for Transonic Shock Tube Airfoil Testing
Theoretical Considerations of Sidewall Interference Corrections for Transonic Shock Tube Airfoil Testing
复制标题
跨音速激波管翼型测试侧壁干扰修正的理论思考
DOI：
10.2322/tjsass.52.193
复制
发表时间：
2010
影响因子：
1.1
通讯作者：
H. Kitano
中科院分区：
文献类型：
--
作者：
M. Kashitani;Y. Yamaguchi;Eisaku Sunahara;H. Kitano
研究了跨音速激波管翼型流动中侧壁边界层的影响。我们试图用激波管边界层的Barnwell-Sewall和Murthy方法来修正侧壁边界层的影响。本文采用Petersen的边界层理论计算激波管壁面摩擦系数，结果表明，在激波管作用时间一定的情况下，马赫数修正M（自由流马赫数（热气马赫数）与修正马赫数之差）随热气马赫数M2的增大而增大。这是由附面层发展引起的，附面层随着热气马赫数的增加而变厚。此外，当在恒定位移厚度2 =B的条件下进行分析时，马赫数修正M随着热气马赫数的增加而逐渐增加。随着位移厚度的增加，这种趋势变得非常明显。此外，在进行比较后，我们发现，修正的冲击波的位置是在改进的方向与二维CFD结果时，应用于激波管实验的协议。
The effects of the sidewall boundary layers in transonic shock tube airfoil flow were investigated. We attempted to correct the effects of the sidewall boundary layers using the Barnwell-Sewall and Murthy methods for shock tube boundary layers. Petersen’s boundary layer theory, which evaluates the modern wall-skin friction coefficients for shock tubes, was used in this analysis, and the results showed that the Mach number correction M (the difference between the free stream Mach number (hot gas Mach number) and the corrected Mach number) increases as the hot gas Mach numberM2 increases under the condition of fixed time for the shock tube. This is caused by the boundary layer development, which grows thicker as the hot gas Mach number increases. Furthermore, when analysis is performed under the condition of constant displacement thickness 2 =b, the Mach number correction M gradually increases with an increase in the hot gas Mach number. This trend becomes very pronounced with increasing displacement thickness. In addition, after performing a comparison, we found that the correction of the shock wave location is in the direction of the improved agreement with the 2D CFD results when applied to the shock tube experiment.