NASA LogoNTRSNTRS - NASA Technical Reports ServerSearchmore_vertCollectionsAboutNewsHelpLogin Back to ResultsThe Effect of Incoming Boundary Layer Characteristics on the Performance of a Distributed Propulsion SystemAn experimental study is conducted in an effort to advance the understanding of flow physics associated with a boundary layer ingesting, distributed propulsion system. The influence of incoming boundary layer thickness and flow distortions are studied on the flow downstream and the overall performance of the system. The propulsion model, fabricated using additive manufacturing and integrated with electrical fans, is mounted on a flat plate and tested at subsonic speeds. Detailed characterization of the incoming boundary layer and subsequent assessment of the downstream flow field is performed using hotwire anemometry. Modification of the incoming boundary layer is achieved by placing tripping devices, such as rods and vortex generating ramps, near the leading edge of the flat plate. The overall performance of the system for different incoming flow conditions is analyzed by comparing magnitudes of exhaust velocities as well as estimated propulsive power to the corresponding baseline values. For a constant input power to the fans, smaller upstream flow distortions and moderately thickened boundary layers result in marginal changes in the flow field downstream. On the other hand, notable reductions in downstream flow velocities and propulsive power are observed in the case of a significantly thicker and/or distorted incoming boundary layer. It is hoped that this study will serve as a database for this technologically relevant flow field that has not been explored adequately before.Document ID20190004930Acquisition SourceGlenn Research CenterDocument TypeTechnical Memorandum (TM)AuthorsUpadhyay, Puja*(Universities Space Research Association (USRA) Cleveland, OH, United States)*Zaman, K. B. M. Q.*(NASA Glenn Research Center Cleveland, OH, United States)*Date AcquiredMay 2, 2019Publication DateMarch 1, 2019Subject CategoryAircraft Propulsion And PowerReport/Patent NumberE-19658NASA/TM—2019-220068GRC-E-DAA-TN65193Meeting InformationMeeting: 2019 Science and Technology Forum (SciTech)Location: San Diego, CACountry: United StatesStart Date: January 7, 2019End Date: January 11, 2019Sponsors:American Institute of Aeronautics and Astronautics (AIAA)Funding Number(s)CONTRACT_GRANT: NNH15CO48BWBS: 109492.02.01.01.05Distribution LimitsPublicCopyrightPublic Use Permitted.Technical ReviewSingle ExpertKeywordsPropulsionturbulencevorticityBoundary layer ingestionAvailable DownloadsNameType20190004930.pdfSTIcloud_downloadcontent_copyvisibilityRelated RecordsThere are no records associated with this record.visibility_offNo Preview Available
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