Gas Turbine Engine Exhaust Jet Shear-layer Pressure Measurement System

Period of Performance: 05/01/2013 - 04/30/2014


Phase 2 SBIR

Recipient Firm

Aero Systems Engineering, Inc.
358 East Fillmore Avenue
St. Paul, MN 55107
Principal Investigator

Research Topics


A microphone array system for studying the near field hydrodynamic region adjacent to the supersonic exhaust plume of a tactical aircraft engine in a ground test fixture at approximately 20 feet above the ground. It will consist of approximately 160 microphones aimed radially inward at the edge of the shear layer and extending to 20 diameters downstream of the nozzle exit. A mobile scissors jack will aid positioning. Data will be processed and analyzed using techniques derived from prior work to elucidate the large scale structure and estimate the noise radiated to the far field.