Flow and acoustic properties of a jet at Reynolds number of 70,000 were studied at Mach 2.1. Measurements in a free jet test facility were made with pitot tubes and hot-wire anemometry. Center-line Mach number distributions for natural and excited jets were obtained. A slow initial growth rate was in the potential core region of the jet, indicating a transition from laminar to turbulent flow in moderate Reynolds number jets. The transition occurred within the first 2-3 diameters. Spectral components were calculated for the fluctuating flowfield, and sound pressure levels were measured for the overall near-field noise. The centroid of noise was located about 8 nozzle diameters downstream. The growth rates of instabilities were determined to be in agreement with linear stability theory predictions over a broad frequency range.

Investigation of jet noise using optical holography

Citations

Experiments on the flow and acoustic properties of a moderate-Reynolds-number supersonic jet

Hot-wire Measurements in a Supersonic Jet at Low Reynolds Numbers

Hot-Wire Measurements in a Supersonic Jet at Low

Related Papers (5)

Supersonic jet noise

The Generation and Radiation of Supersonic Jet Noise. Volume V. An Experimental Investigation of Jet Noise Variation with Velocity and Temperature.

The Generation and Radiation of Supersonic Jet Noise. Volume 1. Summary of Supersonic Jet Noise Studies

The Generation and Radiation of Supersonic Jet Noise. Volume V - Appendix I. Turbulence Mixing Region Noise Data.

Acoustical Holography-Based Analysis of Spatiospectral Lobes in High-Performance Aircraft Jet Noise