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.

Meeting Name

20th AIAA/CEAS Aeroacoustics Conference (2014: Jun. 16-20, Atlanta, GA)


Mechanical and Aerospace Engineering

Research Center/Lab(s)

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)


Document Type

Article - Conference proceedings

Document Version


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© 2014 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.

Publication Date

01 Jan 2014

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