99--TECHNOLOGY TRANSFER OPPORTUNITY ADVANCED OVER-THE-WING NACELLE TRANSPORTCONFIGURATION: LAR-17478

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: Scientists at NASA Langley Research Center have NASA Langley has developed a new aircraft design with the engine nacelle over the wing, improving engine ground clearance and freeing landing gear design. While previous over-the-wing designs have produced unacceptably high drag conditions, the new NASA design reduces drag on the wing. By optimizing the nacelle design and the wing leading edge location, NASAs design confines the shock to the leading edge of the wing. Also, placing the exhaust nozzle over the wing reduces noise to the communities below. NASA developed the novel configuration to address the drag penalties associated with traditional over-the-wing nacelle designs. As shown in Figure 1, the novel features of the wing design include the unswept inboard wing section between the fuselage and the nacelle with an extended chord. The chord is extended so that it is almost in line with the front face of the nacelle, promoting near two-dimensional channel flow between the nacelle and the fuselage that pulls the standing shock wave farther forward. Confining the shock naturally enhances the leading edge suction and eliminates the shock traditionally located near the trailing edge. The net effect is reduced compressibility-based interference drag, as shown in Figure 2. Figure 3 shows the distribution of the drag coefficient, multiplied by wing chord, for the over-the-wing nacelle (OWN) compared to an under- wing nacelle (UWN) and a wing with no nacelle at all. Noise is reduced because the engine nozzle is tangential to the wing upper surface and near the middle of the wing chord to put the exhaust noise source in the best position to be shielded from the community by the wing below it. The configuration has been assessed using both inviscid Euler and viscous Navier-Stokes computational fluid dynamics (CFD) methods. U.S. patent 7,883,052. To express interest in this opportunity, please respond to contact@example.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.