Analysis of Numerical Simulation Database for Pressure Fluctuations Induced By High-Speed Turbulent Boundary Layers
Direct numerical simulations (DNS) of Mach 6 turbulent boundary layer with nominal freestream Mach number of 6 and Reynolds number of ReT ≈ 460 are conducted at two wall temperatures (Tω=Tr = 0:25, 0:76) to investigate the generated pressure uctuations and their dependence on wall temperature. It is shown that the mean flow predictions and computed frequency spectrum of wall-pressure fluctuations are in good agreement with the measurements in the Boeing/AFOSR Mach 6 Quiet Tunnel at Purdue University. Simulations indicate that the inuence of wall temperature on pressure fluctuations is largely limited to the near-wall region, with the characteristics of wall-pressure fluctuations showing a strong temperature dependence. Wall temperature has little inuence on the propagation speed of the freestream pressure signal. The freestream radiation intensity compares well between wall-temperature cases when normalized by the local wall shear; the propagation speed of the freestream pressure signal and the orientation of the radiation wave front show little dependence on the wall temperature.
L. Duan and M. M. Choudhari, "Analysis of Numerical Simulation Database for Pressure Fluctuations Induced By High-Speed Turbulent Boundary Layers," Proceedings of the 20th AIAA/CEAS Aeroacoustics Conference (2014, Atlanta, GA), American Institute of Aeronautics and Astronautics (AIAA), Jan 2014.
20th AIAA/CEAS Aeroacoustics Conference (2014: Jun. 16-20, Atlanta, GA)
Mechanical and Aerospace Engineering
Center for High Performance Computing Research
Keywords and Phrases
Aeroacoustics; Boundary Layer Flow; Computer Simulation; Reynolds Number; Turbulence; Freestream Mach Number; Freestream Pressure; Frequency Spectra; Pressure Fluctuation; Propagation Speed; Radiation Intensity; Temperature Dependence; Turbulent Boundary Layers; Computational Fluid Dynamics
International Standard Book Number (ISBN)
Article - Conference proceedings
© 2014 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.