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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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    Wind tunnel studies of nacelle interference drag at high subsonic speeds including the effect of powered jets (1966)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Keywords: GENERAL
    Type: Conf. on Aircraft Aerodynamics; p 259-270
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Investigation of powered nacelles on a high aspect ratio NASA supercritical wing, phase 2 (1981)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A modified wing with the long core separate flow nacelle and several E(3) nacelles was utilized. The effects of nacelle and pylon cant angles and nacelle longitudinal and vertical location were investigated over a Mach number range from 0.70 to 0.83. The results at the cruise condition 0.82 Mach number and 0.55 lift coefficient are presented.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Advan. Aerodyn. and Active Controls; p 105-122
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Effect of underwing aft-mounted nacelles on the longitudinal aerodynamic characteristics of a high-wing transport airplane (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: As part of a propulsion/airframe integration program, tests were conducted in the Langley 16-Foot Transonic Tunnel to determine the longitudinal aerodynamic effects of installing flow through engine nacelles in the aft underwing position of a high wing transonic transfer airplane. Mixed flow nacelles with circular and D-shaped inlets were tested at free stream Mach numbers from 0.70 to 0.85 and angles of attack from -2.5 deg to 4.0 deg. The aerodynamic effects of installing antishock bodies on the wing and nacelle upper surfaces as a means of attaching and supporting nacelles in an extreme aft position were investigated.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2447 , L-15664 , NAS 1.60:2447
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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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
  • 6
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    Aerodynamic characteristics of a 0.0667-scale model of the X-15A-2 research airplane at transonic speeds (1966)
    In:  CASI
    Details
    Publication Date: 2019-05-29
    Description: Aerodynamic characteristics of scale model of X-15 research aircraft determined in transonic pressure tunnel
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-1198
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Nacelle/pylon/wing integration on a transport model with a natural laminar flow nacelle (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests were conducted in the Langley 16-Foot Transonic Tunnel at free-stream Mach numbers from 0.70 to 0.82 and angles of attack from -2.5 deg to 4.0 deg to determine if nacelle/pylon/wing integration affects the achievement of natural laminar flow on a long-duct flow-through nacelle for a high-wing transonic transport configuration. In order to fully assess the integration effect on a nacelle designed to achieve laminar flow, the effects of fixed and free nacelle transitions as well as nacelle longitudinal position and pylon contouring were obtained. The results indicate that the ability to achieve laminar flow on the nacelle is not significantly altered by nacelle/pylon/wing integration. The increment in installed drag between free and fixed transition for the nacelles on symmetrical pylons is essentially the calculated differences between turbulent and laminar flow on the nacelles. The installed drag of the contoured pylon is less than that of the symmetrical pylon. The installed drag for the nacelles in a rearward position is greater than that for the nacelles in a forward position.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2439 , L-15907 , NAS 1.60:2439
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Effect of a wing-tip mounted pusher turboprop on the aerodynamic characteristics of a semi-span wing (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An exploratory investigation has been conducted at the NASA Langley Research Center to determine the installed performance of a wing tip-mounted pusher turboprop. Tests were conducted using a semispan model having an unswept, untapered wing with a air-driven motor located on the tip of the wing, with an SR-2 design high speed propeller installed on the rear shaft of the motor. All tests were conducted at a Mach number of 0.70, at angles of attack of approximately -2 to +4 deg, and at a Reynolds number of 3.82 million based on the wing chord of 13 inches. The data indicate that, as a result of locating the propeller behind the wing trailing edge, at the wingtip, in the cross flow of the tip vortex, it is possible to recover part of the vortex energy as an increase in propeller thrust and, therefore, a reduction in the lift-induced drag as well.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 85-1286
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Exploratory wind-tunnel investigation of a wingtip-mounted vortex turbine for vortex energy recovery (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Langley 8-foot transonic pressure tunnel was used for tests to determine the possibility of recovering, with a turbine-type device, part of the energy loss associated with the lift-induced vortex system. Tests were conducted on a semispan model with an unswept, untapered wing, with and without a wingtip-mounted vortex turbine. Three sets of turbine blades were tested to determine the effect of airfoil section shape and planform. The tests were conducted at a Mach number of 0.70 over an angle-of-attack range from 0 deg. to 4 deg. at a Reynolds number of 3.82 x 10 to the 6th power based on the wing reference chord of 13 in.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2468 , L-15795 , NAS 1.60:2468
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Tabulated pressure measurements on a large subsonic transport model airplane with high bypass ratio, powered, fan jet engines (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental wind-tunnel investigation to determine the aerodynamic interference and the jet-wake interference associated with the wing, pylon, and high-bypass-ratio, powered, fan-jet model engines has been conducted on a typical high-wing logistics transport airplane configuration. Pressures were measured on the wing and pylons and on the surfaces of the engine fan cowl, turbine cowl, and plug. Combinations of wing, pylons, engines, and flow-through nacelles were tested, and the pressure coefficients are presented in tabular form. Tests were conducted at Mach numbers from 0.700 to 0.825 and angles of attack from -2 to 4 deg.
    Keywords: AIRCRAFT
    Type: NASA-TM-X-2530 , L-8182
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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