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  • 1
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    Three-component laser Doppler velocimeter measurements in a juncture flow (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A single-axis, five-beam, three-component laser velocimeter (LV) system was used in a major experiment. Satisfactory results were obtained with the LV system in the juncture flow. Limited optical access to the tunnel proved to be a problem for the three component LV system in determining the third component.
    Keywords: LASERS AND MASERS
    Type: Research in Natural Laminar Flow and Laminar-Flow Control, Part 2; p 389-400
    Format: application/pdf
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  • 2
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    Vortex dynamics (1986)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Vortex flows of interest to aerodynamicists cover a wide range of scales from a fraction of an inch in boundary layer flows to many feet in wake flows. In many applications these flows are poorly understood and, due to their complexity, present a challenge both analytically and experimentally. Four topics representing the spectrum of experimental and analytical vortex research are presented.
    Keywords: AERODYNAMICS
    Type: Langley Symposium on Aerodynamics, Volume 1; p 375-392
    Format: application/pdf
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  • 3
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    LDA seeding system for the Langley Low Turbulence Pressure Tunnel (1985)
    In:  CASI
    Details
    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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  • 4
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    The measurement of disturbance levels in the Langley Research Center 20-inch Mach 6 tunnel (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Constant-temperature anemometry was used to measure the disturbance levels in the Langley Research Center 20-inch Mach 6 Tunnel over a limited range of total pressures. The measurements were made using a dual wire probe where each wire was operated at a high but different overheat. The fluctuating voltages were digitized and a system of two equations was solved to obtain the instantaneous mass flow and total temperature fluctuations as a function of time. Statistical techniques were used to obtain statistical quantities of interest.
    Keywords: AERODYNAMICS
    Type: NASA-CR-4571 , NAS 1.26:4571
    Format: application/pdf
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  • 5
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    Juncture flow control using leading-edge fillets (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Flow measurements have been made in the wake region of a simulated wing-fuselage juncture, with and without leading-edge fillets, in order to assess the effect of leading-edge modifications on the flow field around the juncture. Preliminary results indicate that there is some reduction in juncture drag at moderate angles of attack with the use of leading-edge fillets. There is also evidence of improvement in the flow characteristics on the surface downstream of the juncture when fillets are used. As the fillet size is increased, flow characteristics start deteriorating at some point, and an optimum fillet size may be required to achieve an overall improvement in the flow field.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 85-4097
    Format: text
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  • 6
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    Experiments and code validation for juncture flows (1988)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The turbulent flow around a juncture formed by an unswept wing and a flat plate has been experimentally studied, and the effectiveness of modifications near the wing leading edge in controlling the juncture flow field has been evaluated. The results are compared with numerical solutions of the incompressible Reynolds-averaged Navier-Stokes equations. The Baldwin-Lomax turbulence model is used in the computations. The numerical code is very time efficient, and it predicts the flow behavior well, including the detection of leading-edge vortex formation. It tends to over-predict the boundary layer thickness and the location of the vortex. Both the experiment and computations indicate that the leading edge flow separation is eliminated by the use of a leading-edge fillet designed in this study, resulting in drag reduction.
    Keywords: AERODYNAMICS
    Type: AGARD, Validation of Computational Fluid Dynamics. Volume 2: Poster Papers; 11 p
    Format: text
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  • 7
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    A new approach to high-speed flow measurements using constant voltage anemometry (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The paper addresses the basic features of conventional instrumentation, such as the constant temperature (CTA) and the constant current (CCA) anemometers, their limitations, and describes a totally new approach to high-speed dynamic measurements using a constant voltage anemometer (CVA). The paper describes the design features of a newly developed CVA and compares preliminary results obtained with CVA and conventional anemometry in low- and high-speed flows.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: AIAA PAPER 92-3957
    Format: text
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  • 8
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    Laser velocimeter measurements in a wing-fuselage type juncture (1988)
    In:  CASI
    Details
    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
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  • 9
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    Flow control in a wing/fuselage-type juncture (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The laminar flow around a juncture formed by an unswept wing and a flat plate has been studied using a combination of smoke flow visualization, and velocity and pressure measurements. The effectiveness of swept leading-edge fillets in controlling the juncture flow field has been evaluated. Flow separation upstream of the wing leading edge is confined to a small region near the plate. This separation results in periodic shedding of horseshoe type vortices. The pressure gradient measured upstream of the leading edge in this laminar juncture is steeper than that of the turbulent flow case. The use of fillets eliminates the leading-edge flow separation and reduces the size of juncture wake, as observed from flow visualization. For one of the filleted cases, there is a significant increase in the extent of laminar flow in the juncture region, and a sizable reduction in the juncture drag.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 88-0614
    Format: text
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  • 10
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    Juncture flow measurements using laser velocimetry (1985)
    In:  Other Sources
    Details
    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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