2 edition of The NASA Langley laminar-flow-control experiment on a swept, supercritical airfoil found in the catalog.
The NASA Langley laminar-flow-control experiment on a swept, supercritical airfoil
by National Aeronautics and Space Administration, Scientific and Technical Information Office in [Washington, DC]
Written in English
|Other titles||NASA Langley laminar flow control experiment on a swept, supercritical airfoil.|
|Statement||Charles D. Harris ... [et al.].|
|Series||NASA technical memorandum -- 4309.|
|Contributions||Harris, Charles D., 1952-|
|The Physical Object|
Full text of "NASA Technical Reports Server (NTRS) Transonic Symposium: Theory, Application, and Experiment, volume 1, part 2" See other formats. Jun 14, · An airfoil having a fore airfoil element, an aft airfoil element, and a slot region in between them. These elements induce laminar flow over substantially all of the fore airfoil element and also provide for laminar flow in at least a portion of the slot region. The method of the invention is one for inducing natural laminar flow over an airfoil.
High Reynolds Number Hybrid Laminar Flow Control (HLFC) Flight Experiment. Apr 1, 04/ by NON. texts. The model was tested with four-engine simulators mounted on pylons under the percent-thick supercritical airfoil wing. Two sets of air ejectors were used to provide data with large and small engines. of the NASA Langley. The system is applied to carry out robust design about the uncertainty of lift coefficient and Mach number for NASA NLF airfoil. The data of optimized airfoil aerodynamic characteristics indicates that the optimized airfoil can maintain laminar flow stably in an uncertain range and has a wider range of low innovationoptimiser.com by:
Charles D. Harris, Cuyler W. Brooks Jr., Patricia G. Clukey and John P. Stack, The NASA Langley Laminar-Flow-Control Experiment on a Swept, Supercritical Airfoil Evaluation of Initial Perforated Configuration, NASA TM, April , pp. Optimized Natural-Laminar-Flow Airfoils J. Driver and D. W. Zinggy University of Toronto Institute for Aerospace Studies Du erin Street, Toronto, Ontario Canada, M3H 5T6 A two-dimensional Newton-Krylov aerodynamic shape optimization algorithm has been modi ed to incorporate the prediction of laminar-turbulent transition. Modi cations to.
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NASA Technical Memorandum The NASA Langley Larninar- Flow-Control Experiment) on a Swept, Supercritical Airfoil Drug Equdtiolzs Cuyler W.
Brooks, Jr., Charles D. Harris, and William D. Harvey Langley Research Center Hampton, Virginia. Get this from a library. The NASA Langley laminar-flow-control experiment on a swept, supercritical airfoil: suction coefficient analysis.
[Cuyler W Brooks; Charles D Harris; William D. DESIGN OF A LAMINAR-FLOW-CONTROL SHPERCRITICAL AIRFOIL FOR A SWEPT WING Dennis 0. Allison and John R. Dagenhart NASA Langley Research Center SUMMARY An airfoil was analytically designed and analyzed for a combination of supercritical flow and laminar flow control (LFC) by boundary-layer suction.
Get this from a library. The NASA Langley laminar-flow-control experiment on a swept supercritical airfoil: basic results for slotted configuration. [Charles D Harris; United States. National Aeronautics and Space Administration.
Scientific and Technical Information Division.;]. This paper concerns one of the NASA in-house activities, the Langley Laminar Flow Control (LFC) Project, which was carried out in the Langley 8-foot Transonic Pressure Tunnel (8-ft TPT). The idea for such an undertaking came from Dr. Werner Pfenninger in and stemmed, primarily, from a desire to know more about the compatability of a high Cited by: 3.
Brooks, C. and Harris, C.,Results of LFC experiment on slotted, swept supercritical airfoil in Langley’s 8-Foot Transonic Pressure Tunnel, NASA Symposium on NLF and LFC Research, NASA CPpp. – Google ScholarCited by: 2. *** NOTE: The NASA HSR Program was phased out in fiscal year *** Supersonic Laminar Flow Control One goal of NASA's High-Speed Research (HSR) program is to achieve laminar, or smooth, airflow over the surface of an aircraft's wing while flying at supersonic speeds.
Oct 22, · Help NASA SBIR/STTR Program Support For questions about the NASA SBIR/STTR solicitations, the proposal preparation and electronic submission process, and other program related areas, please contact the NASA SBIR/STTR Program Support Office.
Phone: Email: [email protected] NASA SBIR/STTR Program Support is available Monday through Friday from. Dec 01, · This NASA Facts explores the history of NASA Langley Research Center in Hampton, Virginia, this country's first civilian aeronautics laboratory.
Several major episodes in the epic story of American aerospace have their roots in the research contributions made by Langley since its establishment in The NASA Langley laminar-flow-control experiment on a swept, supercritical airfoil: evaluation of initial perforated configuration / (Washington, D.C.: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, ), by Charles D.
Harris and Langley Research Center (page images at. Exploration of a Slotted Airfoil Laminar-Flow-Control Concept NASA Aeronautics Research Mission Directorate (ARMD) NASA Langley Low-Turbulence Pressure Tunnel Theory vs. Experiment October 22–24, NASA Aeronautics Research Mission Directorate FY12 LEARN Phase I.
High Reynolds number investigation of a flush-mounted, S-duct inlet with large amounts of boundary layer ingestion. The NASA Langley laminar-flow-control experiment on a swept, supercritical airfoil: suction coefficient analysis / (Washington, D.C.: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program ; Springfield, Va.
Design of a Swept-Wing Laminar Flow Control Flight Experiment for Transonic Aircraft A laminar flow, swept airfoil was designed to operate at conditions of Mach number M = candidate aircraft selections nor the objectives of the experiment.
Figure 1. The NASA G-II/SP (NNA) on a tarmac in El Paso, TX. Exploration of a Slotted Laminar-Flow-Control Airfoil Concept Final Technical Report - NASA Grant No. NNX13AB86A Mark D. Maughmer and Amandeep Premi Department of Aerospace Engineering Penn State University Dan M.
Somers Airfoils, Incorporated Abstract The S, slotted, natural-laminar-flow (SNLF) airfoil was investigated in the. Airfoils and Wings in Compressible Flow. supersonic linearized theory such as symmetrical double wedge airfoil in supersonic flow, supersonic biconvex circular arc airfoil in supersonic flow.
Roughness in the High-Crossflow Region of a Swept Wing with Laminar-Flow Control (Washington, DC: NASA TMOctober ); Albert L. Braslow and Dal V. Maddalon, Flight Tests of Surface Roughness Representative of Construction Rivets on a Swept Wing with Laminar-Flow Control (Washington, DC: NASA TMApril ).
Jun 03, · Laminar flow airfoils are designed to have long favorable pressure gradients. All airfoils must have adverse pressure gradients on their aft end. The usual definition of a laminar flow airfoil is that the favorable pressure gradient ends somewhere between 30% and 75% of chord.
Now consider the finish on your car in non-rainy conditions. Experimental Investigation of Laminar Flow Control on a Supersonic Swept Wing by Suction Erich Schulein¨∗ German Aerospace Center DLR, Institute of Aerodynamics and Flow Technology. Aug 20, · A fast approach to designing airfoils from given pressure distribution in compressible flows.
A large-chord, swept, supercritical, laminar-flow-control LFC airfoil was designed and constructed and is currently undergoing tests in the Langley 8 ft Transonic Pressure Tunnel. Fo re w o rd At NASA’s Langley Research Center, we are proud to carry forward a legacy of innovation and technical excellence.
This pictorial history, our th Anniversary book, uses images to.Taking off into the. Next Years. An F/A E/F model tested in NASA Langley Research Center’s Transonic Dynamics Tunnel. Since its inception, NASA has soared at the forefront of aerospace.Natural-Laminar-Flow Airfoil Development for a Lightweight Business Jet cations is the NASA HSNLF(1) airfoil.4¡6This airfoil has a high drag-divergence Mach number and small nose-down pitching moment.
Its maximum lift coef” cient at low Reynolds numbers is, for both the subcritical and supercritical cases. The MSES code.