Jet Aeroacoustics

The field of Aeroacoustics represents the study of the generation of sound by fluid flow and its propagation into its surroundings which places it at the union of acoustics and fluid dynamics. Jet flows are ubiquitous in engineering applications and are representative of a fundamental class of free shear flows. This site presents a discussion of the flow physics associated with the generation of noise which is radiated away from jet from both a historical perspective along with a new ongoing study.        



Ever since the advent of jet aircraft in the first half of the twentieth century researchers have sought to understand and control the generation of from aircraft engines.  Modern turbofan engines have many noise sources as depicted in the image below.  Although all of the components contribute to overall noise profile of an engine jet aeroacoustics is generally concerned with the mixing noise and shock noise. 

Noise sources in a typical turbofan engine (June, 2017)

The mixing noise downstream of the engine is associated turbulence generated noise is largely the main concern associated with jet noise with the jet under subsonic exit conditions.  When one examines the pressures associated with a jet flow it can be broken down into several regions which will be used throughout this discussion.  They are shown in the Schleiren image below as the hydrodynamic pressure (within the flow), the near field pressures and the far field pressures which represent the acoustics/noise one wishes to understand.  

Schlieren Photograph of Subsonic Jet





The earliest theories of jet noise were formulated at a time when turbulent flows were viewed as entirely chaotic phenomena. The turbulent jet was considered to comprise a disorganized ensemble of eddies of various scales, fluctuating energy being dissipated by means of an energy cascade from the largest scales to the smallest.



Present Study

The present study is being conducted in the the Anechoic Wind Tunnel in the Mechanical and Aerospace Department at the University of Florida and is designed to examine the sources within a moderate Mach number subsonic jet.  The study combines Particle Image Velocimetry (PIV) measurements with a novel pressure sensor to examine hydrodynamic pressure fluctuations and relate them to the radiated noise.        



PIV Measurements 

PIV measurements have been acquired in the orientations shown below to allow for investigation of both streamwise evolution as well as the azimuthal variation.  

PIV Configurations 



Pressure Sensor 



Requests for Information

All requests for information, comments on content or data regarding this project should be directed to Prof. Lawrence Ukeiley (ukeiley






This work is sponsored by NSF Grant # 1704768

PI’s L. Ukeiley and M. Sheplak