Acoustic Radiation from a Mach 14 Turbulent Boundary Layer
Direct numerical simulations (DNS) are used to examine the turbulence statistics and the radiation field generated by a high-speed turbulent boundary layer with a nominal free stream Mach number of 14 and wall temperature of 0: 18 times the recovery temperature. The flow conditions fall within the range of nozzle exit conditions of the Arnold Engineering Development Center (AEDC) Hypervelocity Tunnel No. 9 facility.
C. Zhang et al., "Acoustic Radiation from a Mach 14 Turbulent Boundary Layer," Proceedings of the 54th AIAA Aerospace Sciences Meeting, AIAA SciTech Forum (2016, San Diego, CA), American Institute of Aeronautics and Astronautics (AIAA), Jan 2016.
54th AIAA Aerospace Sciences Meeting, AIAA SciTech Forum (2016: Jan. 4-8, San Diego, CA)
Mechanical and Aerospace Engineering
Center for High Performance Computing Research
Keywords and Phrases
Aerodynamics; Aerospace Engineering; Aviation; Boundary Layer Flow; Boundary Layers; Heat Flux; Mach Number; Military Aviation; Reynolds Number; Shear Stress; Turbulence; Turbulent Flow; Arnold Engineering Development Center; Boundary Layer Thickness; Computational Results; Free Stream Mach Numbers; Pressure Fluctuation; Recovery Temperature; Turbulence Statistics; Turbulent Boundary Layers; Atmospheric Thermodynamics
International Standard Book Number (ISBN)
Article - Conference proceedings
© 2016 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.
01 Jan 2016