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  • 1
    Publication Date: 1989-06-01
    Description: An experiment has been conducted to study the occurrence, configuration and dynamics of large-scale coherent vortical motions in the fully developed region of a turbulent axisymmetric jet. The key idea is to use vorticity signals from a spatial grid to detect and sample large-scale vortical structures and then use the (smoothed) vorticity peaks of spatial vorticity patterns to align and ensemble average successive realizations to determine structure configuration and dynamics. Measurements were made in an air jet at ReD = 69000 by employing a radial rake of seven x-wires-wires to obtain the azimuthal vorticity map. Two additional conditioning probes were placed ±90° away from the rake to determine the three-dimensional phase and hence the structure configuration. Structures with axisymmetric, helical and double helical configurations have been educed. Among them, the helical structures are far more dominant than the others, and the jet dynamics are thus discussed in terms of these helical structures. Helical structures move radially outward as they advect downstream. This radial movement, in conjunction with simultaneous local ejection of turbulent fluid and subsequent entrainment of the ejected fluid with ambient fluid, appears to be a major means of jet spreading. The shear strain rate is strong on the downstream side of the structure, causing intense small-scale turbulence production and mixing there. © 1989, Cambridge University Press. All rights reserved.
    Print ISSN: 0022-1120
    Electronic ISSN: 1469-7645
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics , Physics
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  • 2
    Publication Date: 2017-10-02
    Description: The flowfield induced by a single, subsonic jet exhausting perpendicularly from a flat plate into a subsonic crossflow has been numerically investigated. The test case was chosen to match available experimental data where the jet Mach number was 0.78, and the freestream Mach number was 0.13. Time-averaged solutions were obtained using the thin-layer Navier-Stokes equations and two overlapping grids. The solutions were sensitive to the radial grid clustering near the edge of the jet and to the far-field boundary conditions. Experimental data comparisons were required to determine the most appropriate jet grid and satisfactory boundary conditions. Globally, the solutions converged in about 6000 iterations. The computational results accurately showed the deflected jet and associated contrarotating vortices. The fine clustered grid in the region upstream of the jet exit allowed the horseshoe vortex in the boundary layer near the jet exit to be captured. Most importantly for aircraft applications, the computed plate pressure distributions compared favorably with the experimental data over most of the surface. However, in the wake region immediately downstream of the jet exit, where there is extensive flow separation, some discrepancies with experimental data were observed. Two turbulence models were used in this study: (1) the zero-equation, two layer Baldwin-Lomax turbulence model; and (2) one-equation Baldwin-Barth turbulence model. The turbulence models gave results which generally compared no better with experimental data than the laminar computation results.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AGARD, Computational and Experimental Assessment of Jets in Cross Flow; 14 p
    Format: text
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  • 3
    Publication Date: 2019-07-27
    Description: The use of suction to trap a vortex is investigated experimentally. Vortex trapping using a finite sink and cross-flow obstructions is shown to be viable in the case of low-speed flow over a flat plate airfoil. A dual-fence geometry is found to be more efficient than a backward-facing step due to the greater restriction of vortex movement in the streamwise direction. The backward-facing step geometry provides for an increase in the sink strength required for trapping, while the more efficient dual-fence geometry permits the use of a lower suction force for trapping.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 91-3271 , AIAA Applied Aerodynamics Conference; Sept. 23-25, 1991; Baltimore, MD; United States
    Format: text
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  • 4
    Publication Date: 2019-07-13
    Description: The flowfield induced by a single, subsonic jet exhausting perpendicularly from a flat plate into a subsonic crossflow has been numerically investigated. Time-averaged solutions were obtained using the thin-layer Navier-Stokes equations and two overlapping grids. Test cases were chosen to match available experimental data where the jet Mach number was 0.78 and the freestream Mach number was varied to represent effective velocity ratios R from 4 to 12. Comparisons of the pressures induced on the flat plate are presented. The results show that the best agreement is obtained for R of 4 and 6, R of 8 is more difficult to resolve, and the R of 12 solution was not satisfactory. It is anticipated that the resolution could be improved by using either smaller time steps or finer grid spacing as R increases.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 93-4860 , ; 12 p.|Dec 01, 1993 - Dec 03, 1993; Santa Clara, CA; United States
    Format: text
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  • 5
    Publication Date: 2019-07-13
    Description: An experimental investigation of the effect of upper surface blowing on dynamic stall was conducted. Progress made during the period from Jun. to Dec. 1993 is summarized. Topics covered include VR-7 wing model, pulse valve, and wing/load cell junction.
    Keywords: AERODYNAMICS
    Type: NASA-CR-194863 , NAS 1.26:194863
    Format: application/pdf
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  • 6
    Publication Date: 2019-07-13
    Description: A numerical analysis is presented of the flowfield induced by a single subsonic jet exhausting perpendicularly from a flat plate into a subsonic crossflow. The analysis used available experimental data from a test case where the jet Mach number was 0.78 and the freestream Mach number was 0.13. Time-averaged solutions were obtained using the thin-layer Navier-Stokes equations and two overlapping grids. The effect of turbulence model on the solutions was evaluated using two turbulence models: the zero-equation two-layer Baldwin-Lomax (1978) turbulence model and the one-equation Baldwin-Barth (1990) turbulence model. It was found that, for some conditions, the zero-equation Baldwin-Lomax turbulence model gave better results than the one-equation Baldwin-Barth model or the laminar case.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 93-0870 , ; 21 p.|AIAA, Aerospace Sciences Meeting and Exhibit; Jan 11, 1993 - Jan 14, 1993; Reno, NV; United States
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  • 7
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    In:  Other Sources
    Publication Date: 2019-07-13
    Description: An experiment was conducted to examine the vortex trapping concept on a 60 deg sweep delta wing at low angles of attack. Using tapered leading edge fences, stable vortices have been successfully trapped. The resulting increase in lift coefficient can be as high as 0.4, which amounts to a 6.5 deg shift in the lift coefficient curve of the delta wing. The corresponding increase in drag coefficient, however, is also significant.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 92-2639 , AIAA Applied Aerodynamics Conference; Jun 22, 1992 - Jun 24, 1992; Palo Alto, CA; United States
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  • 8
    Publication Date: 2019-07-13
    Description: Wind tunnel tests have been conducted on two devices for the purpose of lift augmentation on a 60 deg delta wing at low speed. Lift, drag, pitching moment, and surface pressures were measured. Detailed flow visualization was also obtained. Both the leading edge fence and the Gurney flap are shown to increase lift. The fences and flap shift the lift curve by as much as 5 deg and 10 deg, respectively. The fences aid in trapping vortices on the upper surface, thereby increasing suction. The Gurney flap improves circulation at the trailing edge. The individual influences of both devices are roughly additive, creating high lift gain. However, the lower lift to drag ratio and the precipitation of vortex burst caused by the fences, and the nose down pitching moment created by the flap are also significant factors.
    Keywords: Aerodynamics
    Type: NASA-CR-203750 , NAS 1.26:203750 , AIAA Paper 93-3513 , Applied Aerodynamics; Aug 09, 1993 - Aug 11, 1993; Monterey, CA; United States
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