Title

Direct Numerical Simulation of Nozzle-Wall Pressure Fluctuations in a Mach 8 Wind Tunnel

Abstract

Direct numerical simulations (DNS) of the full-scale axisymmetric nozzle of a Mach 8 wind tunnel are conducted with an emphasis on characterizing the properties of the pressure fluctuations induced by the turbulent boundary layer (TBL) along the nozzle wall. The axisymmetric nozzle geometry and the flow conditions of the DNS match those of the Sandia Hypersonic Wind Tunnel at Mach 8. The mean and turbulence statistics of the nozzle-wall boundary layer show good agreement with those predicted by Pate's correlation and Reynolds Averaged Navier-Stokes (RANS) computations. The wall-pressure intensity, power spectral density, and coherence predicted by DNS show good comparisons with those measured in the same tunnel. The Corcos model is found to deliver good prediction of wall pressure coherence over intermediate and high frequencies. The streamwise and spanwise decay constants at Mach 8 are similar to those predicted by DNS and experiments at lower supersonic Mach numbers.

Meeting Name

AIAA Scitech Forum, 2019 (2019: Jan. 7-11, San Diego, CA)

Department(s)

Mechanical and Aerospace Engineering

Comments

Financial support for the work is being provided by the Sandia National Laboratories under subcontract number PO-1885712. Partial support was also provided by the Office of Naval Research (under grant N00014-17-1-2347).

Keywords and Phrases

Atmospheric thermodynamics; Aviation; Boundary layer flow; Boundary layers; Direct numerical simulation; Navier Stokes equations; Nozzles; Numerical models; Spectral density; Turbulence, Axisymmetric nozzles; Decay constants; High frequency HF; Hypersonic wind tunnels; Pressure fluctuation; Reynolds-Averaged Navier-Stokes; Turbulence statistics; Turbulent boundary layers, Wind tunnels

International Standard Book Number (ISBN)

978-162410578-4

Document Type

Article - Conference proceedings

Document Version

Citation

File Type

text

Language(s)

English

Rights

© 2019 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.

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