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Aerodynamic Measurements On A Large Splitter Plate For The Nasa Langley Transonic Dynamics Tunnel
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Book Synopsis Aerodynamic Measurements on a Large Splitter Plate for the NASA Langley Transonic Dynamics Tunnel by : David M. Schuster
Download or read book Aerodynamic Measurements on a Large Splitter Plate for the NASA Langley Transonic Dynamics Tunnel written by David M. Schuster and published by . This book was released on 2001 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781720372967 Total Pages :42 pages Book Rating :4.3/5 (729 download)
Book Synopsis Aerodynamic Measurements on a Large Splitter Plate for the NASA Langley Transonic Dynamics Tunnel by : National Aeronautics and Space Administration (NASA)
Download or read book Aerodynamic Measurements on a Large Splitter Plate for the NASA Langley Transonic Dynamics Tunnel written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-05-29 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests conducted in the NASA Langley Research Center Transonic Dynamics Tunnel (TDT) assess the aerodynamic characteristics of a splitter plate used to test some semispan models in this facility. Aerodynamic data are analyzed to determine the effect of the splitter plate on the operating characteristics of the TDT, as well as to define the range of conditions over which the plate can be reasonably used to obtain aerodynamic data. Static pressures measurements on the splitter plate surface and the equipment fairing between the wind tunnel wall and the splitter plate are evaluated to determine the flow quality around the apparatus over a range of operating conditions. Boundary layer rake data acquired near the plate surface define the viscous characteristics of the flow over the plate. Data were acquired over a range of subsonic, transonic and supersonic conditions at dynamic pressures typical for models tested on this apparatus. Data from this investigation should be used as a guide for the design of TDT models and tests using the splitter plate, as well as to guide future splitter plate design for this facility.Schuster, David M.Langley Research CenterTRANSONIC WIND TUNNELS; AERODYNAMIC CHARACTERISTICS; DYNAMIC PRESSURE; STATIC PRESSURE; VISCOUS FLOW; WIND TUNNEL TESTS; BOUNDARY LAYERS; SEMISPAN MODELS
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