Aeroacoustics of High-Speed Jet Impingement

Award Information
Agency:
Department of Defense
Branch
Navy
Amount:
$79,995.00
Award Year:
2010
Program:
SBIR
Phase:
Phase I
Contract:
N68335-10-C-0464
Agency Tracking Number:
N102-133-0356
Solicitation Year:
n/a
Solicitation Topic Code:
NAVY 10-133
Solicitation Number:
n/a
Small Business Information
Combustion Research and Flow Technology, Inc.
6210 Kellers Church Road, Pipersville, PA, 18947
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
929950012
Principal Investigator:
Neeraj Sinha
Vice President & Technica
(215) 766-1520
sinha@craft-tech.com
Business Contact:
Brian York
Treasurer & Principal Sci
(215) 766-1529
york@craft-tech.com
Research Institution:
n/a
Abstract
The noise from the turbulent, hot, supersonic jets at take-offs and landings dominates noise emanating from other powerplant components and has significant safety implications for launch personnel, as well as by the integrity of the structural components of the deck itself. With the impending induction of the JSF/F-35B into the US Navy in the near-future, concerns regarding noise emissions have taken added prominence. Unique to the JSF/F-35B is the requirement for it to operate in short takeoff and vertical landing (STOVL) mode on smaller ships, with the exhaust nozzle being vectored vertically downwards to produce lift. Jet impingement on the deck gives rise to resonant tones that are produced by a powerful acoustic feedback loop formed between the ground plane and trailing edge of the exhaust nozzle via the ambient medium. Similar noise issues also exist with regards to exhaust impingement on the jet blast deflector (JBD) on carriers. CRAFT Tech and Purdue University will extend and demonstrate an innovative high-fidelity LES method towards characterization of the noise sources associated with high-speed impinging jets. The farfield noise emissions will be obtained with integral techniques that will be extended for jet impingement. The model will be validated against laboratory data.

* information listed above is at the time of submission.

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