Direct Numerical Simulation of Acoustic Noise Generation from the Nozzle Wall of a Hypersonic Wind Tunnel


The acoustic radiation from the turbulent boundary layer on the nozzle wall of a Mach 6 Ludwieg Tube is simulated using Direct Numerical Simulations (DNS), with the flow conditions falling within the operational range of the Mach 6 Hypersonic Ludwieg Tube, Braunschweig (HLB). 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 rms pressure uctuation p′rms/Ï"w plateaus in the freestream core of the nozzle. The intensity of the freestream noise within the nozzle is approximately 20% higher than that radiated from a single at pate with a similar freestream Mach number, potentially because of the contributions to the acoustic radiation from multiple azimuthal segments of the nozzle wall.

Meeting Name

47th AIAA Fluid Dynamics Conference, 2017 (2017: Jun. 5-9, Denver, CO)


Mechanical and Aerospace Engineering

Keywords and Phrases

Acoustic emissions; Acoustic radiators; Acoustic wave propagation; Acoustic wave transmission; Acoustic waves; Atmospheric thermodynamics; Boundary layers; Direct numerical simulation; Fluid dynamics; Hypersonic aerodynamics; Hypersonic boundary layers; Navier Stokes equations; Nozzles; Numerical models; Turbulence; Wind tunnels, Acoustic radiation; Freestream mach number; Hypersonic wind tunnels; Noise generation; Operational range; Reynolds-Averaged Navier-Stokes; Turbulence statistics; Turbulent boundary layers, Acoustic noise

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Document Type

Article - Conference proceedings

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© 2017 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.

Publication Date

01 Jun 2017

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