Jet Aeroacoustics

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





Initial theories of jet noise were formulated at a time when turbulent flows were viewed as an 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.  The initial development of Lighthill’s acoustic analogy was formulated in this era and the components of the “source terms” were viewed in this context.    



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 


In the streamwise aligned plane the figure below shows the growth of the jet’s mean velocity field along with the turbulent fluctuations.  The measurement domain extended through the noise producing region from 3 to 8 jet diameters downstream of the jet exit plane.  These measurements show the collapse of the jet potential core as well as the development of the shear layers.   


Mean Streamwise Velocity Mean Square Fluctuating Streamwise Velocity 
Mean Square Fluctuating Radial Velocity Shear Component of the Reynolds Stress
Velocity Fields from Streamwise Aligned PIV Measurements


Velocity measurements in the cross stream plan (shown below) show the axisymmetric nature of the jet and how the velocity field evolve.  It should be noted that in this plane we have interpolated the PIV measurements onto a cylindrical grid.  

Velocity Fields from Cross Plane PIV Measurements


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