SPECIAL NOTICE
99 -- TECHNOLOGY TRANSFER OPPORTUNITY OPTIMAL FLOW CONTROL DESIGN FOR QUIETERAND MORE ENVIRONMENTALLY FRIENDLY TRANSPORT AIRCRAFT.
- Notice Date
- 8/27/2014
- Notice Type
- Special Notice
- NAICS
- 927110
— Space Research and Technology
- Contracting Office
- NASA/Langley Research Center, Mail Stop 12, Industry Assistance Office, Hampton,VA 23681-0001
- ZIP Code
- 23681-0001
- Solicitation Number
- TT01069
- Archive Date
- 8/27/2015
- Point of Contact
- Jesse C Midgett, Program Specialist, Phone 757-864-3936, Fax 757-864-8314, Email j.midgett@nasa.gov
- E-Mail Address
-
Jesse C Midgett
(j.midgett@nasa.gov)
- Small Business Set-Aside
- N/A
- Description
- NASA Langley Research Center in Hampton, VA solicits inquiries from companies interested in obtaining license rights to commercialize, manufacture and market the following technology. License rights may be issued on an exclusive or nonexclusive basis and may include specific fields of use. NASA provides no funding in conjunction with these potential licenses. THE TECHNOLOGY: In support of the Blended-Wing-Body aircraft concept, researchers at NASAs Langley Research Center have developed a new flow control hybrid vane/jet design for use in a boundary-layer-ingesting (BLI) offset inlet in transonic flows. This concept represents a potentially enabling technology for quieter and more environmentally friendly transport aircraft. An optimum vane design was found by minimizing the engine fan-face distortion, DC60, and the first five Fourier harmonic half amplitudes while maximizing the total pressure recovery. The optimal vane design was then used in a BLI inlet wind tunnel experiment at NASA Langleys 0.3-meter transonic cryogenic tunnel. The experimental results demonstrated an 80% decrease in the circumferential distortion levels at an inlet mass flow rate corresponding to the middle of the operational range at the cruise condition. Even though the vanes were designed at a single inlet mass flow rate, they performed very well over the entire inlet mass flow range tested in the wind tunnel experiment with the addition of a small amount of jet flow control. While the circumferential distortion was decreased, the radial distortion on the outer rings at the aerodynamic interface plane (AIP) increased. This was a result of the large boundary layer being distributed from the bottom of the AIP in the baseline case to the outer edges of the AIP when using the vortex generator (VG) vane flow control. To express interest in this opportunity, please respond to LaRC-PatentLicensing@mail.nasa.gov with the title of this Technology Transfer Opportunity as listed in this FBO notice and your preferred contact information. Please also provide the nature of your interest in the technology along with a brief background of your company. For more information about licensing other NASA-developed technologies, please visit the NASA Technology Transfer Portal at http://technology.nasa.gov/. These responses are provided to members of NASA Langleys Office of Strategic Analysis and Business Development OSACB for the purpose of promoting public awareness of NASA-developed technology products, and conducting preliminary market research to determine public interest in and potential for future licensing opportunities. If direct licensing interest results from this posting, OSACB will follow the required formal licensing process of posting in the Federal Register. No follow-on procurement is expected to result from responses to this Notice.
- Web Link
-
FBO.gov Permalink
(https://www.fbo.gov/spg/NASA/LaRC/OPDC20220/TT01069/listing.html)
- Record
- SN03482803-W 20140829/140828022226-74076a0bdd712e7d8925ef38a62489a5 (fbodaily.com)
- Source
-
FedBizOpps Link to This Notice
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