High Fidelity Simulation of Jet Noise Emissions from Rectangular Nozzles

Award Information
Agency:
National Aeronautics and Space Administration
Branch
n/a
Amount:
$899,965.00
Award Year:
2012
Program:
SBIR
Phase:
Phase II
Contract:
NNX12CA17C
Award Id:
n/a
Agency Tracking Number:
104174
Solicitation Year:
2010
Solicitation Topic Code:
A2.03
Solicitation Number:
n/a
Small Business Information
PA, Pipersville, PA, 18947-1020
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
929950012
Principal Investigator:
Neeraj Sinha
Principal Investigator
(215) 766-1520
sinha@craft-tech.com
Business Contact:
Katherine Young
Business Official
(215) 766-1520
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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