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  • 1
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    Vortex flap flow reattachment line and subsonic longitudinal aerodynamic data on 50 deg to 74 deg Delta wings on common fuselage (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Positions of the primary vortex flow reattachment line and longitudinal aerodynamic data were obtained at Mach number 0.3 for a systematic series of vortex flaps on delta wing body configurations with leading edge sweeps of 50, 58, 66, and 74 deg. The investigation was performed to study the parametric effects of wing sweep, vortex flap geometry and deflection, canards, and trailing edge flaps on the location of the primary vortex reattachment line relative to the flap hinge line. The vortex reattachment line was located via surface oil flow photographs taken at selected angles of attack. Force and moment measurements were taken over an angle of attack range of -1 deg to 22 deg at zero sideslip angle for many configurations to further establish the data base and to assess the aforementioned parametric effects on longitudinal aerodynamics. Both the flow reattachment and aerodynamic data are presented.
    Keywords: AERODYNAMICS
    Type: NASA-TM-84618 , L-15702 , NAS 1.15:84618
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Review of vortex flow flight projects on the F-106B (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: NASA-Langley's F-106B research aircraft is being used in vortex flow-research flight experiments in order to determine the effects of Re number and Mach number on the lee-side vortex system generated at angles-of-attack up to maneuver condition, as well as to evaluate the aerodynamic characteristics of a sharp leading-edge vortex flap system. The wing vortex system is visualized at a fixed position by means of the vapor-screen technique. Comparisons are made between a measured value and two theoretical estimates of a pertinent vortex system property, core location.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 87-2346
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Subsonic pitch-up alleviation on a 74 deg delta wing (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Fixed leading-edge devices were investigated for alleviating the low speed pitch-up and longitudinal instability of a 74 deg delta wing model. In wind-tunnel tests, Pylon Vortex Generators were shown to be highly effective, compared to leading-edge fences and slots, in raising the pitch-up angle of attack from 8 deg to 28 deg. The subsonic drag penalty was negligible.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-CR-165749
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Experimental study of delta wing leading-edge devices for drag reduction at high lift (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The drag reduction devices selected for evaluation were the fence, slot, pylon-type vortex generator, and sharp leading-edge extension. These devices were tested on a 60 degree flatplate delta (with blunt leading edges) in the Langley Research Center 7- by 10-foot high-speed tunnel at low speed and to angles of attack of 28 degrees. Balance and static pressure measurements were taken. The results indicate that all the devices had significant drag reduction capability and improved longitudinal stability while a slight loss of lift and increased cruise drag occurred.
    Keywords: AERODYNAMICS
    Type: NASA-CR-165846
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Experimental investigation of the aerodynamic effects of distributed spanwise blowing on a fighter configuration (1948)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The results of wind tunnel tests at NASA Langley targeted at the performance and configurational characteristics of 0.1 and 0.13 scale model spanwise blowing (SWB) jet wing concepts are reported. The concept involves redirection of engine compressor bleed air to provide SWB at the fuselage-wing juncture near the wing leading edge. The tests covered the orientation of the outer panel nozzles, the effects of SWB operation on the performance of leading and trailing edge flaps and the effects of SWB on lateral stability. The trials were run at low speeds and angles of attack from 24-45 deg (landing). Both lift and longitudinal stability improved with the SWB, stall and leading edge vortex breakdown were delayed and performance increased with the SWB rate. Lateral stability was degraded below 20 deg angle of attack while instabilities were delayed above 20 deg due to roll damping.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-2195
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Subsonic wind-tunnel investigation of leading-edge devices on delta wings (data report) (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The drag reduction potential of leading edge devices on delta wings at high lift is presented. Fences, pylon type vortex generators, chordwise slots, and sharp plate extensions were tested on wing models with 60 and 74 degree swept blunt leading edges at angles of attack to 32 degrees. Six component balance and leading edge surface pressure measurements were taken with various geometry and spanwise arrangements of the devices. Tables listing the data, without analysis, are presented.
    Keywords: AERODYNAMICS
    Type: NASA-CR-159120
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Alleviation of the subsonic pitch-up of delta wings (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A 'pylon vortex generator' concept has been proposed for alleviating the subsonic pitch-up instability of highly swept supersonic-cruise wings. Fixed at a part-span location, this leading-edge device utilizes the lateral velocity component in the flow approaching the swept leading edge to generate a streamwise vortex, opposite in sense to the tip vortex. The vortex-induced downwash outboard of the device serves to control the leading-edge stall development in the wing-tip regions. Wind-tunnel results on 60-deg and 74-deg flat-plate delta wings are presented to illustrate the operation of the pylon vortex generator in modifying the spanwise leading-edge separation characteristics resulting in effective alleviation of the pitch-up.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 82-0129 , Aerospace Sciences Meeting; Jan 11, 1982 - Jan 14, 1982; Orlando, FL
    Format: text
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    NASA TECHNICAL REPORTS
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