High Fidelity Simulation of Jet Noise Emissions from Rectangular Nozzles

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNX12CA17C
Agency Tracking Number: 104174
Amount: $899,965.00
Phase: Phase II
Program: SBIR
Awards Year: 2012
Solicitation Year: 2010
Solicitation Topic Code: A2.03
Solicitation Number: N/A
Small Business Information
Combustion Research and Flow Technology
6210 Keller's Church Road, Pipersville, PA, 18947-1020
DUNS: 929950012
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Neeraj Sinha
 Principal Investigator
 (215) 766-1520
 sinha@craft-tech.com
Business Contact
 Katherine Young
Title: Business Official
Phone: (215) 766-1520
Email: youngk@craft-tech.com
Research Institution
 Stub
Abstract
The proposed SBIR Phase II program will lead to the validation of a state-of-the-art Large Eddy Simulation (LES) model, coupled with a Ffowcs-Williams-Hawkings (FW-H) farfield acoustic solver, for supporting the development of advanced engine concepts, including innovative flow control strategies for attenuation of their jet noise emissions. During Phase I, the LES/FW-H model was validated against matched sets of flowfield and companion acoustic data acquired at NASA/GRC for round nozzles. The flowfield validation included detailed comparisons against imagery, mean flow measurements and turbulence statistics. During Phase II, the end-to-end LES/FW-H noise prediction model will be demonstrated and validated by applying it to high aspect-ratio rectangular nozzle designs, proposed for testing at NASA GRC under the Fundamental Aeronautics Program. The model will also be validated against acoustic and flowfield data from a realistic jet-pylon experiment, thereby significantly advancing the state-of-the-art for LES. This critical validation will provide the foundation for proceeding to application of this innovative methodology in supporting the design and optimization of control concepts, e.g. chevrons, bevels, etc., as well as ultimately performing predictions of noise emissions from full-scale, realistic nozzles with complex exhaust flowpaths, airframe/propulsive jet interactions, etc.

* information listed above is at the time of submission.

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