NASA LogoNTRSNTRS - NASA Technical Reports ServerSearchmore_vertCollectionsAboutNewsHelpLogin Back to ResultsRefined AFC-Enabled High-Lift System Integration StudyA prior trade study established the effectiveness of using Active Flow Control (AFC) for reducing the mechanical complexities associated with a modern high-lift system without sacrificing aerodynamic performance at low-speed flight conditions representative of takeoff and landing. The current technical report expands on this prior work in two ways: (1) a refined conventional high-lift system based on the NASA Common Research Model (CRM) is presented that is more representative of modern commercial transport aircraft in terms of stall characteristics and maximum Lift/Drag (L/D) ratios at takeoff and landing-approach flight conditions; and (2) the design trade space for AFC-enabled high-lift systems is expanded to explore a wider range of options for improving their efficiency. The refined conventional high-lift CRM (HL-CRM) concept features leading edge slats and slotted trailing edge flaps with Fowler motion. For the current AFC-enhanced high lift system trade study, the refined conventional high-lift system is simplified by substituting simply-hinged trailing edge flaps for the slotted single-element flaps with Fowler motion. The high-lift performance of these two high-lift CRM variants is established using Computational Fluid Dynamics (CFD) solutions to the Reynolds-Averaged Navier-Stokes (RANS) equations. These CFD assessments identify the high-lift performance that needs to be recovered through AFC to have the CRM variant with the lighter and mechanically simpler high-lift system match the performance of the conventional high-lift system. In parallel to the conventional high-lift concept development, parametric studies using CFD guided the development of an effective and efficient AFC-enabled simplified high-lift system. This included parametric trailing edge flap geometry studies addressing the effects of flap chord length and flap deflection. As for the AFC implementation, scaling effects (i.e., wind-tunnel versus full-scale flight conditions) are addressed, as are AFC architecture aspects such as AFC unit placement, number AFC units, operating pressures, mass flow rates, and steady versus unsteady AFC applications. These efforts led to the development of a novel traversing AFC actuation concept which is efficient in that it reduces the AFC mass flow requirements by as much as an order of magnitude compared to previous AFC technologies, and it is predicted to be effective in driving the aerodynamic performance of a mechanical simplified high-lift system close to that of the reference conventional high-lift system. Conceptual system integration studies were conducted for the AFC-enhanced high-lift concept applied to a NASA Environmentally Responsible Aircraft (ERA) reference configuration, the so-called ERA-0003 concept. The results from these design integration assessments identify overall system performance improvement opportunities over conventional high-lift systems that suggest the viability of further technology maturation efforts for AFC-enabled high lift flap systems. To that end, technical challenges are identified associated with the application of AFC-enabled high-lift systems to modern transonic commercial transports for future technology maturation efforts.Document ID20160006410Acquisition SourceLangley Research CenterDocument TypeContractor Report (CR)AuthorsHartwich, Peter M.*(Boeing Co. Huntington Beach, CA, United States)*Shmilovich, Arvin*(Boeing Co. Huntington Beach, CA, United States)*Lacy, Douglas S.*(Boeing Co. Huntington Beach, CA, United States)*Dickey, Eric D.*(Boeing Co. Huntington Beach, CA, United States)*Scalafani, Anthony J.*(Boeing Co. Huntington Beach, CA, United States)*Sundaram, P.*(Boeing Co. Huntington Beach, CA, United States)*Yadlin, Yoram*(Boeing Co. Huntington Beach, CA, United States)*Date AcquiredMay 19, 2016Publication DateMarch 1, 2016Subject CategoryAerodynamicsFluid Mechanics And ThermodynamicsReport/Patent NumberNF1676L-23752NASA/CR-2016-219170Funding Number(s)CONTRACT_GRANT: NNL10AA05BWBS: WBS 081876.02.07.02.01.04CONTRACT_GRANT: NNL14AB98TDistribution LimitsPublicCopyrightPublic Use Permitted.Available DownloadsNameType20160006410.pdfSTIcloud_downloadcontent_copyvisibilityRelated RecordsThere are no records associated with this record.visibility_offNo Preview Available
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