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  • 1
    Electronic Resource
    Electronic Resource
    SPECIAL PEDIATRIC PROBLEMS IN FLUID AND ELECTROLYTE THERAPY IN SURGERY (1957)
    Oxford, UK : Blackwell Publishing Ltd
    Annals of the New York Academy of Sciences 66 (1957), S. 0 
    Details
    ISSN: 1749-6632
    Source: Blackwell Publishing Journal Backfiles 1879-2005
    Topics: Natural Sciences in General
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1111/j.1749-6632.1957.tb40782.x
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    Paper (German National Licenses)
    Fulltext
  • 2
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    Corporate Strategy: A Point of View (1971)
    Berkeley, Calif. : Periodicals Archive Online (PAO)
    California Management Review. 13:3 (1971:Spring) 
    Details
    ISSN: 0008-1256
    Topics: Economics
    URL: http://gateway.proquest.com/openurl?url_ver=Z39.88-2004&res_dat=xri:pao:&rft_dat=xri:pao:article:5018-1971-013-03-000001
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    Paper (German National Licenses)
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  • 3
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    A Separation Control CFD Validation Test Case (2004)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Low speed flow separation over a wall-mounted hump, and its control using steady suction, were studied experimentally in order to generate a data set for a workshop aimed at validating CFD turbulence models. The baseline and controlled data sets comprised static and dynamic surface pressure measurements, flow field measurements using Particle Image Velocimetry (PIV) and wall shear stress obtained via oil-film interferometry. In addition to the specific test cases studied, surface pressures for a wide variety of conditions were reported for different Reynolds numbers and suction rates. Stereoscopic PIV and oil-film flow visualization indicated that the baseline separated flow field was mainly two- dimensional. With the application of control, some three-dimensionality was evident in the spanwise variation of pressure recovery, reattachment location and spanwise pressure fluctuations. Part 2 of this paper, under preparation for the AIAA Meeting in Reno 2005, considers separation control by means of zero-efflux oscillatory blowing.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: AIAA Paper 2004-2220-Pt-1 , 2nd AIAA Flow Control Conference; Jun 28, 2004 - Jul 01, 2004; Portland, OR; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Synthetic Jet Flow Field Database for CFD Validation (2004)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An oscillatory zero net mass flow jet was generated by a cavity-pumping device, namely a synthetic jet actuator. This basic oscillating jet flow field was selected as the first of the three test cases for the Langley workshop on CFD Validation of Synthetic Jets and Turbulent Separation Control. The purpose of this workshop was to assess the current CFD capabilities to predict unsteady flow fields of synthetic jets and separation control. This paper describes the characteristics and flow field database of a synthetic jet in a quiescent fluid. In this experiment, Particle Image Velocimetry (PIV), Laser Doppler Velocimetry (LDV), and hot-wire anemometry were used to measure the jet velocity field. In addition, the actuator operating parameters including diaphragm displacement, internal cavity pressure, and internal cavity temperature were also documented to provide boundary conditions for CFD modeling.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: AIAA Paper 2004-2218 , 2nd AIAA Flow Control Conference; Jun 28, 2004 - Jul 01, 2004; Portland, OR; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    A Separation Control CFD Validation Test Case (2004)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Low speed flow separation over a wall-mounted hump, and its control using steady suction, were studied experimentally in order to generate a data set for a workshop aimed at validating CFD turbulence models. The baseline and controlled data sets comprised static and dynamic surface pressure measurements, flow field measurements using Particle Image Velocimetry (PIV) and wall shear stress obtained via oil-film interferometry. In addition to the specific test cases studied, surface pressures for a wide variety of conditions were reported for different Reynolds numbers and suction rates. Stereoscopic PIV and oil-film flow visualization indicated that the baseline separated flow field was mainly two-dimensional. With the application of control, some three-dimensionality was evident in the spanwise variation of pressure recovery, reattachment location and spanwise pressure fluctuations. Part 2 of this paper, under preparation for the AIAA Meeting in Reno 2005, considers separation control by means of zero-efflux oscillatory blowing.
    Keywords: Fluid Mechanics and Thermodynamics
    Type: AIAA Paper 2004-2220 , 2nd AIAA Flow Control Conference; Jun 28, 2004 - Jul 01, 2004; Portland, OR; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Active Flow Control at Low Reynolds Numbers on a NACA 0015 Airfoil (2008)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Results from a low Reynolds number wind tunnel experiment on a NACA 0015 airfoil with a 30% chord trailing edge flap tested at deflection angles of 0, 20, and 40 are presented and discussed. Zero net mass flux periodic excitation was applied at the ap shoulder to control flow separation for flap deflections larger than 0. The primary objective of the experiment was to compare force and moment data obtained from integrating surface pressures to data obtained from a 5-component strain-gage balance in preparation for additional three-dimensional testing of the model. To achieve this objective, active flow control is applied at an angle of attack of 6 where published results indicate that oscillatory momentum coefficients exceeding 1% are required to delay separation. Periodic excitation with an oscillatory momentum coefficient of 1.5% and a reduced frequency of 0.71 caused a significant delay of separation on the airfoil with a flap deflection of 20. Higher momentum coefficients at the same reduced frequency were required to achieve a similar level of flow attachment on the airfoil with a flap deflection of 40. There was a favorable comparison between the balance and integrated pressure force and moment results.
    Keywords: Aircraft Stability and Control
    Type: 26th AIAA Applied Aerodynamics Conference; Aug 18, 2008 - Aug 21, 2008; Honolulu, HI; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Flow-Field Investigation of Gear-Flap Interaction on a Gulfstream Aircraft Model (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Off-surface flow measurements of a high-fidelity 18% scale Gulfstream aircraft model in landing configuration with the main landing gear deployed are presented. Particle Image Velocimetry (PIV) and Laser Velocimetry (LV) were used to measure instantaneous velocities in the immediate vicinity of the main landing gear and its wake and near the inboard tip of the flap. These measurements were made during the third entry of a series of tests conducted in the NASA Langley Research Center (LaRC) 14- by 22-Foot Subsonic Tunnel (14 x 22) to obtain a comprehensive set of aeroacoustic measurements consisting of both aerodynamic and acoustic data. The majority of the off-body measurements were obtained at a freestream Mach number of 0.2, angle of attack of 3 degrees, and flap deflection angle of 39 degrees with the landing gear on. A limited amount of data was acquired with the landing gear off. LV was used to measure the velocity field in two planes upstream of the landing gear and to measure two velocity profiles in the landing gear wake. Stereo and 2-D PIV were used to measure the velocity field over a region extending from upstream of the landing gear to downstream of the flap trailing edge. Using a special traverse system installed under the tunnel floor, the velocity field was measured at 92 locations to obtain a comprehensive picture of the pertinent flow features and characteristics. The results clearly show distinct structures in the wake that can be associated with specific components on the landing gear and give insight into how the wake is entrained by the vortex at the inboard tip of the flap.
    Keywords: Fluid Mechanics and Thermodynamics; Aircraft Design, Testing and Performance; Aerodynamics
    Type: NF1676L-17794 , AIAA Aviation and Aeronautics Forum and Exposition (AVIATION 2014); Jun 16, 2014 - Jun 20, 2014; Atlanta, GA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Navier-Stokes Simulation of a Heavy Lift Slowed-Rotor Compound Helicopter Configuration (2009)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Time accurate numerical simulations were performed using the Reynolds-averaged Navier-Stokes (RANS) flow solver OVERFLOW for a heavy lift, slowed-rotor, compound helicopter configuration, tested at the NASA Langley 14- by 22-Foot Subsonic Tunnel. The primary purpose of these simulations is to provide support for the development of a large field of view Particle Imaging Velocimetry (PIV) flow measurement technique supported by the Subsonic Rotary Wing (SRW) project under the NASA Fundamental Aeronautics program. These simulations provide a better understanding of the rotor and body wake flows and helped to define PIV measurement locations as well as requirements for validation of flow solver codes. The large field PIV system can measure the three-dimensional velocity flow field in a 0.914m by 1.83m plane. PIV measurements were performed upstream and downstream of the vertical tail section and are compared to simulation results. The simulations are also used to better understand the tunnel wall and body/rotor support effects by comparing simulations with and without tunnel floor/ceiling walls and supports. Comparisons are also made to the experimental force and moment data for the body and rotor.
    Keywords: Aerodynamics
    Type: LF99-7826 , AHS International 65th Forum and Technology Display; May 27, 2009 - May 29, 2009; Grapevine, TX; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Development of a Large Field-of-View PIV System for Rotorcraft Testing in the 14- x 22-Foot Subsonic Tunnel (2009)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A Large Field-of-View Particle Image Velocimetry (LFPIV) system has been developed for rotor wake diagnostics in the 14-by 22-Foot Subsonic Tunnel. The system has been used to measure three components of velocity in a plane as large as 1.524 meters by 0.914 meters in both forward flight and hover tests. Overall, the system performance has exceeded design expectations in terms of accuracy and efficiency. Measurements synchronized with the rotor position during forward flight and hover tests have shown that the system is able to capture the complex interaction of the body and rotor wakes as well as basic details of the blade tip vortex at several wake ages. Measurements obtained with traditional techniques such as multi-hole pressure probes, Laser Doppler Velocimetry (LDV), and 2D Particle Image Velocimetry (PIV) show good agreement with LFPIV measurements.
    Keywords: Aerodynamics
    Type: LF99-7824 , AHS International 65th Forum and Technology Display; May 27, 2009 - May 29, 2009; Grapevine, TX; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Resistance to Sulfanilyl Derivatives in Vitro and in Vivo (1940)
    American Association for the Advancement of Science
    Details
    Publication Date: 1940-07-05
    Print ISSN: 0036-8075
    Electronic ISSN: 1095-9203
    Topics: Biology , Chemistry and Pharmacology , Computer Science , Medicine , Natural Sciences in General , Physics
    Published by American Association for the Advancement of Science
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