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  • 1
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    Aerodynamic characteristics of a propeller-powered high-lift semispan wing (1994)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A small-scale semispan high-lift wing-flap system equipped under the wing with a turboprop engine assembly was tested in the LaRC 14- by 22-Foot Subsonic Tunnel. Experimental data were obtained for various propeller rotational speeds, nacelle locations, and nacelle inclinations. To isolate the effects of the high lift system, data were obtained with and without the flaps and leading-edge device. The effects of the propeller slipstream on the overall longitudinal aerodynamic characteristics of the wing-propeller assembly were examined. Test results indicated that the lift coefficient of the wing could be increased by the propeller slipstream when the rotational speed was increased and high-lift devices were deployed. Decreasing the nacelle inclination (increased pitch down) enhanced the lift performance of the system much more than varying the vertical or horizontal location of the nacelle. Furthermore, decreasing the nacelle inclination led to higher lift curve slope values, which indicated that the powered wing could sustain higher angles of attack near maximum lift performance. Any lift augmentation was accompanied by a drag penalty due to the increased wing lift.
    Keywords: AERODYNAMICS
    Type: NASA-TM-4541 , L-17259 , NAS 1.15:4541
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Wind Tunnel Aerodynamic Characteristics of a Transport-type Airfoil in a Simulated Heavy Rain Environment (1992)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effects of simulated heavy rain on the aerodynamic characteristics of an NACA 64-210 airfoil section equipped with leading-and trailing-edge high-lift devices were investigated in the Langley 14- by 22-Foot Subsonic Tunnel. The model had a chord of 2.5 ft, a span of 8 ft, and was mounted on the tunnel centerline between two large endplates. Aerodynamic measurements in and out of the simulated rain environment were obtained for dynamic pressures of 30 and 50 psf and an angle-of-attack range of 0 to 20 degrees for the cruise configuration. The rain intensity was varied to produce liquid water contents ranging from 16 to 46 gm/cu m. The results obtained for various rain intensity levels and tunnel speeds showed significant losses in maximum lift capability and increases in drag for a given lift as the liquid water content was increased. The results obtained on the landing configuration also indicate a progressive decrease in the angle of attack at which maximum lift occurred and an increase in the slope of the pitching-moment curve as the liquid water content was increased. The sensitivity of test results to the effects of the water surface tension was also investigated. A chemical was introduced into the rain environment that reduced the surface tension of water by a factor of 2. The reduction in the surface tension of water did not significantly alter the level of performance losses for the landing configuration.
    Keywords: AERODYNAMICS
    Type: NASA-TP-3184 , L-16959 , NAS 1.60:3184
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    The Langley 14- by 22-Foot Subsonic Tunnel: Description, Flow Characteristics, and Guide for Users (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Langley 14- by 22-foot Subsonic Tunnel is a closed circuit, single-return atmospheric wind tunnel with a test section that can be operated in a variety of configurations (closed, slotted, partially open, and open). The closed test section configuration is 14.5 ft high by 21.75 ft wide and 50 ft long with a maximum speed of about 338 ft/sec. The open test section configuration has a maximum speed of about 270 ft/sec, and is formed by raising the ceiling and walls, to form a floor-only configuration. The tunnel may be configured with a moving-belt ground plane and a floor boundary-layer removal system at the entrance to the test section for ground effect testing. In addition, the tunnel had a two-component laser velocimeter, a frequency modulated (FM) tape system for dynamic data acquisition, flow visualization equipment, and acoustic testing capabilities. Users of the 14- by 22-foot Subsonic Tunnel are provided with information required for planning of experimental investigations including test hardware and model support systems.
    Keywords: AERODYNAMICS
    Type: NASA-TP-3008 , L-16731 , NAS 1.60:3008
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Wing pressure distributions from subsonic tests of a high-wing transport model (1995)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A wind tunnel investigation was conducted on a generic, high-wing transport model in the Langley 14- by 22-Foot Subsonic Tunnel. This report contains pressure data that document effects of various model configurations and free-stream conditions on wing pressure distributions. The untwisted wing incorporated a full-span, leading-edge Krueger flap and a part-span, double-slotted trailing-edge flap system. The trailing-edge flap was tested at four different deflection angles (20 deg, 30 deg, 40 deg, and 60 deg). Four wing configurations were tested: cruise, flaps only, Krueger flap only, and high lift (Krueger flap and flaps deployed). Tests were conducted at free-stream dynamic pressures of 20 psf to 60 psf with corresponding chord Reynolds numbers of 1.22 x 10(exp 6) to 2.11 x 10(exp 6) and Mach numbers of 0.12 to 0.20. The angles of attack presented range from 0 deg to 20 deg and were determined by wing configuration. The angle of sideslip ranged from minus 20 deg to 20 deg. In general, pressure distributions were relatively insensitive to free-stream speed with exceptions primarily at high angles of attack or high flap deflections. Increasing trailing-edge Krueger flap significantly reduced peak suction pressures and steep gradients on the wing at high angles of attack. Installation of the empennage had no effect on wing pressure distributions. Unpowered engine nacelles reduced suction pressures on the wing and the flaps.
    Keywords: AERODYNAMICS
    Type: NASA-TM-4583 , L-17380 , NAS 1.15:4583
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    The effect of solidity on propeller normal force (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Propeller normal force is a major contributor to pitch and yaw stability on propeller driven aircraft. While it is well known that propeller normal force is a function of the number of blades, there are no published data for the high numbers of blades that are used in the new designs such as the UDF. This paper presents the results of a test conducted in the NASA Langley 14- x 22-foot Subsonic Tunnel using a sting-mounted counter-rotation propeller and nacelle. The configurations tested were combinations of 0, 4, and 8 blades per hub. Tests were conducted for blade angle settings of 31.34, 36.34, and 41.34 deg over an angle-of-attack range from -10 to 90 deg and over a range of advance ratios from 0.8 to 1.4. The results show that propeller normal force varies with both solidity and angle of attack.
    Keywords: AERODYNAMICS
    Type: SAE PAPER 892205
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Effect of solidity and inclination on propeller-nacelle force coefficients (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A series of wind tunnel experiments were conducted to study the effect of propeller solidity and thrust axis inclination on the propeller normal force coefficient. Experiments were conducted in the Langley 14 by 22 foot Subsonic Tunnel with a sting mounted, counterrotation, scale model propeller and nacelle. Configurations had two rows of blades with combinations of 4 and 8 blades per hub. The solidity was varied by changing the number of blades on both rows. Tests were conducted for blade pitch setting of 31.34 deg, 36.34 deg, and 41.34 deg over a range of angle of attack from -10 deg to 90 deg and range of advance ratio from 0.8 to 1.4. The increase in propeller normal force with angle of attack is greater for propellers with higher solidity.
    Keywords: AERODYNAMICS
    Type: NASA-TM-4316 , L-16933 , NAS 1.15:4316
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Low-speed aerodynamic characteristics of a twin-engine general aviation configuration with aft-fuselage-mounted pusher propellers (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was conducted to determine the aerodynamic characteristics of an advanced turboprop aircraft model with aft-pylon-mounted pusher propellers. Tests were conducted through an angle-of-attack range of -8 to 28 degrees, and an angle-of-sideslip range of -20 to 20 degrees at free-stream conditions corresponding to Reynolds numbers of 0.55 to 2.14 x 10 to the 6th power based on mean aerodynamic chord. Test results show that for the unpowered configurations the maximum lift coefficients for the cruise, takeoff, and landing configurations are 1.45, 1.90, and 2.10, respectively. Nacelle installation results in a drag coefficient increase of 0.01. Increasing propeller thrust results in a significant increase in lift for angles of attack above stall and improves the longitudinal stability. The cruise configuration remains longitudinally stable to an angle of attack 5 degrees beyond the stall angle, the takeoff configuration is stable 4 degrees beyond stall angle, and the landing configuration is stable 3 degrees beyond stall angle. The predominant effect of symmetric thrust on the lateral-directional aerodynamic characteristics is in the post-stall region, where additional rudder control is available with power on.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2763 , L-16331 , NAS 1.60:2763
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Pressure distributions from subsonic tests of an advanced laminar-flow-control wing with leading- and trailing-edge flaps (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An unswept, semispan wing model equipped with full-span leading- and trailing-edge flaps was tested in the Langley 14- by 22-Foot Subsonic Tunnel to determine the effect of high-lift components on the aerodynamics of an advanced laminar-flow-control (LFC) airfoil section. Chordwise pressure distributions near the midsemispan were measured for four configurations: cruise, trailing-edge flap only, and trailing-edge flap with a leading-edge Krueger flap of either 0.10 or 0.12 chord. Part 1 of this report (under separate cover) presents a representative sample of the plotted pressure distribution data for each configuration tested. Part 2 presents the entire set of plotted and tabulated pressure distribution data. The data are presented without analysis.
    Keywords: AERODYNAMICS
    Type: NASA-TM-4040-PT-2 , L-16405 , NAS 1.15:4040-PT-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Effect of Pylon Wake with and Without Pylon Blowing on Propeller Thrust (1990)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Pylon trailing edge blowing was investigated as a means of alleviating the effects of the pylon wake on a pusher arrangement of an advanced single-rotation turboprop. Measurements were made of steady-state propeller thrust and pylon wake pressures and turbulence levels with and without blowing. Results show that the pylon trailing edge blowing practically eliminated the pylon wake, significantly reduced the pylon wake turbulence, and had a relatively small effect on the steady-state propeller thrust. The data are presented with a minimum of analysis.
    Keywords: AERODYNAMICS
    Type: NASA-TM-4162 , L-16645 , NAS 1.15:4162
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Pressure distributions from subsonic tests of an advanced laminar-flow-control wing with leading- and trailing-edge flaps (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An unswept, semispan wing model equipped with full-span leading- and trailing-edge flaps was tested in the Langley 14- by 22-Foot Subsonic Tunnel to determine the effect of high-lift components on the aerodynamics of an advanced laminar-flow-control (LFC) airfoil section. Chordwise pressure distributions near the midsemispan were measured for four configurations: cruise, trailing-edge flap only, and trailing-edge flap with a leading edge Kreuger flap of either 0.10 or 0.12 chord. Part 1 of this report presents a representative sample of the plotted pressure distribution data for each configuration tested. Part 2 (under separate cover) presents the entire set of plotted and tabulated pressure distribution data. The data are presented without analysis.
    Keywords: AERODYNAMICS
    Type: NASA-TM-4040-PT-1 , L-16405 , NAS 1.15:4040-PT-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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