Acoustic Radiation from a Mach 14 Turbulent Boundary Layer

Abstract

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.

Meeting Name

54th AIAA Aerospace Sciences Meeting, AIAA SciTech Forum (2016: Jan. 4-8, San Diego, CA)

Department(s)

Mechanical and Aerospace Engineering

Research Center/Lab(s)

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)

978-1624103933

Document Type

Article - Conference proceedings

Document Version

Citation

File Type

text

Language(s)

English

Rights

© 2016 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.

Publication Date

01 Jan 2016

This document is currently not available here.

Share

 
COinS