Experimental determination of sound and high-speed flow interactionAn experimental facility for measuring the attenuation of sound at various frequencies and modes in a finite duct with high-speed flow (with or without an axial pressure gradient) is described. The facility consists of an anechoic chamber transonic compressor with inlets of different area variations (or axial gradients); sound of selected frequencies and modes is produced with eight circumferential acoustic drivers. The experimental results indicate that high Mach number inlets can increase noise propagation. In addition, an inlet with a constant axial gradient is found to have a better acoustic and aerodynamic performance than inlets of the same area ratio with steep gradients near the throat or exit.
Document ID
19780028907
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Lumsdaine, E. (Tennessee, University Knoxville, Tenn., United States)
Silcox, R. (NASA Langley Research Center Acoustics Branch, Hampton, Va., United States)
Date Acquired
August 9, 2013
Publication Date
January 1, 1977
Subject Category
Acoustics
Meeting Information
Meeting: International Conference on Inter-noise 77: Noise control - The engineers responsibility