Spectral Characteristics of Separation Shock Unsteadiness

被引:35
作者
Poggie, Jonathan [1 ]
Bisek, Nicholas J. [1 ]
Kimmel, Roger L. [1 ]
Stanfield, Scott A. [2 ]
机构
[1] US Air Force, Res Lab, RQHF, Wright Patterson AFB, OH 45433 USA
[2] Spectral Energies LLC, Dayton, OH 45431 USA
关键词
TURBULENT-BOUNDARY-LAYER; LARGE-EDDY SIMULATION; DIRECT NUMERICAL-SIMULATION; COMPRESSION RAMP INTERACTION; LOW-FREQUENCY UNSTEADINESS; FLUCTUATING WALL PRESSURE; HIGH-ORDER METHOD; WAVE STRUCTURE; VELOCITY FLUCTUATIONS; SPACED DATA;
D O I
10.2514/1.J053029
中图分类号
V [航空、航天];
学科分类号
08 ; 0825 ;
摘要
Spectra of wall-pressure fluctuations caused by separation shock unsteadiness were compared for data obtained from wind-tunnel experiments, the Hypersonic International Flight Research Experimentation flight test 1, and large-eddy simulations. The results were found to be in generally good agreement, despite differences in Mach number and two orders of magnitude difference in Reynolds number. Relatively good agreement was obtained between these spectra and the predictions of a theory developed by Plotkin. The predictions of this theory are also qualitatively consistent with the results of experiments in which the shock motion was synchronized to controlled perturbations. The results presented here support the idea that separation unsteadiness has common features across a broad range of compressible flows and that it behaves as a selective amplifier of large-scale disturbances in the incoming flow.
引用
收藏
页码:200 / 214
页数:15
相关论文
共 67 条