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Advances in Acoustics and Vibration
Volume 2011 (2011), Article ID 573209, 9 pages
Research Article

A Theoretical Basis for the Scaling Law of Broadband Shock Noise Intensity in Supersonic Jets

ASRC Aerospace, NASA Kennedy Space Center, Merritt Island, FL 32899, USA

Received 8 September 2010; Accepted 27 January 2011

Academic Editor: Lars Hakansson

Copyright © 2011 Max Kandula. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.


A theoretical basis for the scaling of broadband shock noise intensity in supersonic jets was formulated considering linear shock-shear wave interaction. Modeling of broadband shock noise with the aid of shock-turbulence interaction with special reference to linear theories is briefly reviewed. A hypothesis has been postulated that the peak angle of incidence (closer to the critical angle) for the shear wave primarily governs the generation of sound in the interaction process with the noise generation contribution from off-peak incident angles being relatively unimportant. The proposed hypothesis satisfactorily explains the well-known scaling law for the broadband shock-associated noise in supersonic jets.