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  • 1
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    Ground development and flight correlation of the vortex attenuating spline device (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Data presented indicate that the wing-mounted spline is a effective vortex-attenuating device. A comparison of the vortex induced rolling moment results at a separation scale distance of 0.70 km with those measured in full scale flight indicate good agreement for the unattenuated vortex configuration. The comparison also indicates that the spline effectiveness in flight was greater than in the ground facility test. The results of an applications study show that, for the heavy commercial jet aircraft studied, use of the splines does result in some degradation of the climb gradient and rate of climb, but the aircraft should meet certification requirements.
    Keywords: AERODYNAMICS
    Type: Wake Vortex Minimization; p 271-303
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Leading-edge design for improved spin resistance of wings incorporating conventional and advanced airfoils (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Discontinuous wing leading-edge droop designs have been evaluated as a means of modifying wing autorotative characteristics and thus improving airplane spin resistance. Addition of a discontinuous outboard wing leading-edge droop to three typical light airplanes having NACA 6-series wing sections produced significant improvements in stall characteristics and spin resistance. Wind tunnel tests of two wings having advanced natural laminar flow airfoil sections indicated that a discontinuous leading-edge droop can delay the onset of autorotation at high angles of attack without adversely affecting the development of laminar flow at cruise angles of attack.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAE PAPER 851816
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Thrust-augmented vortex attenuation (1977)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: An experimental investigation was conducted to determine the vortex attenuating effect of engine thrust. Tests were made using a 0.03-scale model of the Boeing 747 transport aircraft as a vortex generating model. A Learjet-class probe model was used to measure the vortex induced rolling moment at a scale separation distance of 1.63 km. These tests were conducted at a lift coefficient of 1.4 at a model velocity of 30.48 m/s. The data presented indicate that engine thrust is effective as a vortex attenuating device when the engines are operated at high thrust levels and are positioned to direct the high energy engine wake into the core of the vortex. The greatest thrust vortex attenuation was obtained by operating the inboard engine thrust reversers at one-quarter thrust and the outboard engines at maximum forward thrust.
    Keywords: AERODYNAMICS
    Type: Wake Vortex Minimization; p 251-270
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Subsonic wind-tunnel tests of a trailing-cone device for calibrating aircraft static pressure systems (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A trailing-cone device for calibrating aircraft static-pressure systems was tested in a transonic wind tunnel to investigate the pressure-sensing characteristics of the device including effects of several configuration changes. The tests were conducted at Mach numbers from 0.30 to 0.95 with Reynolds numbers from (0.9 x one million to 4.1 x one million per foot). The results of these tests indicated that the pressures sensed by the device changed slightly but consistently as the distance between the device pressure orifices and cone was varied from 4 to 10 cone diameters. Differences between such device-indicated pressures and free-stream static pressure were small, however, and corresponded to Mach number differences of less than 0.001 for device configurations with pressure orifices located 5 or 6 cone diameters ahead of the cone. Differences between device-indicated and free-stream static pressures were not greatly influenced by a protection skid at the downstream end of the pressure tube of the device nor by a 2-to-1 change in test Reynolds number.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7217 , L-8672
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    An investigation of the increase in vortex induced rolling moment associated with landing gear wake (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Flight tests were conducted to verify the results found in ground base facilities of the effect of span lift load variation as well as the vortex attentuation of the high energy jet engine exhaust through proper thrust programming. During these flight tests a large increase in vortex strength was experienced as a result of extending the landing gear. Tests in the Langley Vortex Research Facility indicate that the wake produced by the landing gear may possibly form an aerodynamic endplate or reflection plane at the inboard edge of each inboard flap which increases the effective aspect ratio of the flap and thereby increases the strength of the flap outer edge vortex.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-72786
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    A static air flow visualization method to obtain a time history of the lift-induced vortex and circulation (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A recently proposed method of flow visualization was investigated at the National Aeronautics and Space Administration's Langley Research Center. This method of flow visualization is particularly applicable to the study of lift-induced wing tip vortices through which it is possible to record the entire life span of the vortex. To accomplish this, a vertical screen of smoke was produced perpendicular to the flight path and allowed to become stationary. A model was then driven through the screen of smoke producing the circular vortex motion made visible as the smoke was induced along the path taken by the flow and was recorded by highspeed motion pictures.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-72769
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Flow visualization of the wake of a transport aircraft model with lateral-control oscillations (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An exploratory flow visualization study conducted in the Langley Vortex Research Facility to investigate the effectiveness of lateral control surface oscillations as a potential method for wake vortex attenuation on a 0.03 scale model of a wide body jet transport aircraft is described. Effects of both asymmetric surface oscillation (control surfaces move as with normal lateral control inputs) and symmetric surface oscillation (control surfaces move in phase) are presented. The asymmetric case simulated a flight maneuver which was previously investigated on the transport aircraft during NASA/FAA flight tests and which resulted in substantial wake vortex attenuation. Effects on the model wake vortex systems were observed by propelling the model through a two dimensional smoke screen perpendicular to the model flight path. Results are presented as photographic time histories of the wake characteristics recorded with high speed still cameras. Effects of oscillation on the wake roll up are described in some detail, and the amount of vortex attenuation observed is discussed in comparative terms. Findings were consistent with flight test results in that only a small amount of rotation was observed in the wake for the asymmetric case. A possible aerodynamic mechanism contributing to this attenuation is suggested.
    Keywords: AERONAUTICS (GENERAL)
    Type: NASA-TM-84623 , L-15106 , NAS 1.15:84623
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Development of test methods for scale model simulation of aerial applications in the NASA Langley Vortex Research Facility (1980)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: As part of basic research to improve aerial applications technology, methods were developed at the Langley Vortex Research Facility to simulate and measure deposition patterns of aerially-applied sprays and granular materials by means of tests with small-scale models of agricultural aircraft and dynamically-scaled test particles. Interactions between the aircraft wake and the dispersed particles are being studied with the objective of modifying wake characteristics and dispersal techniques to increase swath width, improve deposition pattern uniformity, and minimize drift. The particle scaling analysis, test methods for particle dispersal from the model aircraft, visualization of particle trajectories, and measurement and computer analysis of test deposition patterns are described. An experimental validation of the scaling analysis and test results that indicate improved control of chemical drift by use of winglets are presented to demonstrate test methods.
    Keywords: AERONAUTICS (GENERAL)
    Type: NASA-TM-81805 , AIAA 11th Aerodyn. Testing Conf.; Mar 18, 1980 - Mar 20, 1980; Colorado Springs, CO; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Status of aerial applications research in the Langley Vortex Research Facility and the Langley full-scale wind tunnel (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 78-1481 , Aircraft Systems and Technology Conference; Aug 21, 1978 - Aug 23, 1978; Los Angeles, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Investigation of a class of bodies that generate far-field sonic boom shock strength and impulse independent of body length and volume (1969)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Design method for far field sonic boom shock strength and impulse independent of body length and volume
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-5148
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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