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  • 1
    Publication Date: 2014-03-01
    Description: Understanding the spatial organization of gene expression with single-nucleotide resolution requires localizing the sequences of expressed RNA transcripts within a cell in situ. Here, we describe fluorescent in situ RNA sequencing (FISSEQ), in which stably cross-linked complementary DNA (cDNA) amplicons are sequenced within a biological sample. Using 30-base reads from 8102 genes in situ, we examined RNA expression and localization in human primary fibroblasts with a simulated wound-healing assay. FISSEQ is compatible with tissue sections and whole-mount embryos and reduces the limitations of optical resolution and noisy signals on single-molecule detection. Our platform enables massively parallel detection of genetic elements, including gene transcripts and molecular barcodes, and can be used to investigate cellular phenotype, gene regulation, and environment in situ.〈br /〉〈br /〉〈a href="https://www.ncbi.nlm.nih.gov/pmc/articles/PMC4140943/" target="_blank"〉〈img src="https://static.pubmed.gov/portal/portal3rc.fcgi/4089621/img/3977009" border="0"〉〈/a〉   〈a href="https://www.ncbi.nlm.nih.gov/pmc/articles/PMC4140943/" target="_blank"〉This paper as free author manuscript - peer-reviewed and accepted for publication〈/a〉〈br /〉〈br /〉〈span class="detail_caption"〉Notes: 〈/span〉Lee, Je Hyuk -- Daugharthy, Evan R -- Scheiman, Jonathan -- Kalhor, Reza -- Yang, Joyce L -- Ferrante, Thomas C -- Terry, Richard -- Jeanty, Sauveur S F -- Li, Chao -- Amamoto, Ryoji -- Peters, Derek T -- Turczyk, Brian M -- Marblestone, Adam H -- Inverso, Samuel A -- Bernard, Amy -- Mali, Prashant -- Rios, Xavier -- Aach, John -- Church, George M -- GM080177/GM/NIGMS NIH HHS/ -- MH098977/MH/NIMH NIH HHS/ -- P50 HG005550/HG/NHGRI NIH HHS/ -- RC2 HL102815/HL/NHLBI NIH HHS/ -- RC2HL102815/HL/NHLBI NIH HHS/ -- T32 GM007753/GM/NIGMS NIH HHS/ -- T32 GM080177/GM/NIGMS NIH HHS/ -- U01 MH098977/MH/NIMH NIH HHS/ -- New York, N.Y. -- Science. 2014 Mar 21;343(6177):1360-3. doi: 10.1126/science.1250212. Epub 2014 Feb 27.〈br /〉〈span class="detail_caption"〉Author address: 〈/span〉Wyss Institute, Harvard Medical School, Boston, MA 02115, USA.〈br /〉〈span class="detail_caption"〉Record origin:〈/span〉 〈a href="http://www.ncbi.nlm.nih.gov/pubmed/24578530" target="_blank"〉PubMed〈/a〉
    Keywords: Base Sequence ; Cell Line ; Cells, Cultured ; DNA, Complementary ; Fluorescence ; Gene Expression Profiling/*methods ; Humans ; Induced Pluripotent Stem Cells ; RNA, Messenger/genetics/metabolism ; Sequence Analysis, RNA/*methods ; Single-Cell Analysis ; Transcription Initiation Site ; *Transcriptome ; Wound Healing
    Print ISSN: 0036-8075
    Electronic ISSN: 1095-9203
    Topics: Biology , Chemistry and Pharmacology , Computer Science , Medicine , Natural Sciences in General , Physics
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  • 2
  • 3
    Publication Date: 2013-08-31
    Description: Helicopter rotor blade chordwise pressure distribution and two-dimensional airfoil characteristics
    Keywords: BIOSCIENCES
    Format: application/pdf
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  • 4
    Publication Date: 2016-06-07
    Description: A Laser Velocimetry (LV) seeding system was specifically developed for the Langley Low Turbulence Wind Tunnel (LTPT), and it has been successfully used for LV measurements in two major tests (Juncture Flow Experiment and Gortler Experiment). The LTPT is capable of operating at Mach numbers from 0.05 to 0.50 and unit Reynolds numbers from 100,000 to 15,000,000 per foot. The test section is 3 feet wide and 7.5 feet high. The turbulence level in the test section is relatively low because of the high contraction ratio and because of the nine turbulence reduction screens in the settling chamber. A primary requirement of the seeding system was that the seeding material not contaminate or damage in any way these screens. Both solid and liquid seeding systems were evaluated, and the results are presented. They can provide some guidelines for setting up seeding systems in other similar tunnels.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Wind Tunnel Seeding Systems for Laser Velocimeters; p 169-178
    Format: application/pdf
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  • 5
    Publication Date: 2019-06-28
    Description: A single axis, five beam, three component laser velocimeter system was used in a juncture flow experiment. A description of the seeding system developed for and used in this experiment is given. The performanace of the LV system was evaluated, and some of the problems associated with it were identified. Satisfactory results were obtained in the juncture flow experiments using this LV system.
    Keywords: AERODYNAMICS
    Type: NASA-TM-100588 , NAS 1.15:100588
    Format: application/pdf
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  • 6
    Publication Date: 2019-06-28
    Description: The turbulent flow in a simulated wing-fuselage juncture has been investigated using Laser Velocimetry. The juncture was simulated by a splitter plate with an unswept wing model mounted perpendicular to it. The use of sharp wing leading edge results in the elimination of separation ahead of leading edge, and hence the separation vortex. Secondary flow induced by Reynolds stress gradients is the main source of vortical motion in the juncture formed by the plate and the flat surface of the wing, whereas in the juncture formed by the plate and the circular arc surface of the wing, streamwise vorticity is generated because of the presence of lateral curvature in the flow field. The results of this study indicate that fillets in the juncture can improve the flow characteristics near the wing trailing edge.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 85-1612
    Format: text
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  • 7
    Publication Date: 2019-06-28
    Description: Tests were conducted on a half-scale model representing a 0.914-m (3.0-ft) square stream tube of the flow through the fourth corner and settling chamber of the Langley 8-Foot Transonic Pressure Tunnel. The model included the tube cooler 45 degree turning vanes, and the turbulence reduction screens and honeycomb, which were the subject of the tests. Hot-wire measurements of the turbulence reduction for various combinations of screens and honeycomb were made at various duct speeds. Of the four sizes of honeycomb cells tested, none were found to have a superior performance advantage. The effectiveness of screens and honeycomb in reducing turbulence is greatly affected by relatively minor physical damage; therefore, extreme care must be exercised in installing and maintaining honeycomb or screens if the turbulence reduction performance is to be maintained.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: NASA-TM-81868 , L-14109
    Format: application/pdf
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  • 8
    Publication Date: 2019-06-28
    Description: The device test model consisted of a cooler, turning vanes, and settling chamber (immediately upstream of the contraction) in which various combinations of screens and honeycomb were tested. Conventional hot wires were used to measure the axial and lateral turbulence reduction for the different turbulence reduction devices. The final configuration chosen consisted of a honeycomb followed by five screens.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: NASA-TM-81792 , L-14108
    Format: application/pdf
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  • 9
    Publication Date: 2019-06-28
    Description: Calibration tests using hot wires were conducted using a newly developed test rig that greatly reduced the data acquisition time. A comparison of measured and computed velocity vector magnitude and direction indicates the necessity of complete probe calibration to determine flow interference and/or operating limitation regions. Calibration results indicate that flow rates with 3 percent accuracy and flow angles with 5 deg accuracy are attainable.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-TM-83254 , NAS 1.15:83254 , L-14445
    Format: application/pdf
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  • 10
    Publication Date: 2019-06-27
    Description: An investigation was conducted in the Langley full-scale tunnel to study some factors affecting the tip vortex of a wing. It was found that there was a pronounced effect of Reynolds number on the tip-vortex core size. An attempt was made to determine what aerodynamic parameters, such as lift, drag, or induced drag, influence the size of the vortex core, but no particular function of the parameters was found to be superior to all others. Various spoilers placed on the upper and lower surfaces of the wing to increase the boundary-layer thickness resulted in a reduction in the vorticity as determined from the tuft grid. Various solid objects placed in the vortex core downstream of the wing tip seemed to decrease the vorticity within the vortex core.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2516 , L-8104
    Format: application/pdf
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