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.
J. Huang et al., "Direct Numerical Simulation of Acoustic Noise Generation from the Nozzle Wall of a Hypersonic Wind Tunnel," Proceedings of the 47th Fluid Dynamics Conference (2017, Denver, CO), American Institute of Aeronautics and Astronautics (AIAA), Jun 2017.
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
International Standard Book Number (ISBN)
Article - Conference proceedings
© 2017 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.
01 Jun 2017