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  • 1980-1984  (10)
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  • 1
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    Analytical studies of new airfoils for wind turbines (1981)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Computer studies were conducted to analyze the potential gains associated with utilizing new airfoils for large wind turbine rotor blades. Attempts to include 3-dimensional stalling effects were inconclusive. It is recommended that blade pressure measurements be made to clarify the nature of blade stalling. It is also recommended that new laminar flow airfoils be used as rotor blade sections.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA. Lewis Research Center Wind Turbine Dyn.; p 41-49
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Dynamics of wakes downstream of wind turbine towers (1981)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The near field wakes downstream of circular cylinders and of 12 sided cylinders were surveyed in a wind tunnel. Local velocity and velocity deficit diagrams are presented. The variation of turbulence in the wake was surveyed and the frequency of the periodic component of wake motion was determined. Differences between wakes of circular cylinders and of 12 sided cylinders are discussed. Also effects of strakes, orientation of the 12 sided cylinders, and rounding of the corners are noted.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA. Lewis Research Center Wind Turbine Dyn.; p 369-373
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Additional flow field studies of the GA(W)-1 airfoil with 30-percent chord Fowler flap including slot-gap variations and cove shape modifications (1983)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Experimental measurements were made to determine the effects of slot gap opening and flap cove shape on flap and airfoil flow fields. Test model was the GA(W)-1 airfoil with 0.30c Fowler flap deflected 35 degrees. Tests were conducted with optimum, wide and narrow gaps, and with three cove shapes. Three test angles were selected, corresponding to pre-stall and post-stall conditions. Reynolds number was 2,200,000 and Mach number was 0.13. Force, surface pressure, total pressure, and split-film turbulence measurements were made. Results were compared with theory for those parameters for which theoretical values were available.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3687 , NAS 1.26:3687 , AR-79-3
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Experimental studies of flow separation of three airfoils at low speeds (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Wind tunnel tests were conducted on the NASA LS(1)-0421 Mod, NACA 2412 and NASA GA(W)-2 airfoil sections at a Reynolds number of 2.2 x 10(6) and a Mach number of 0.13. Detailed measurements of flow fields associated with turbulent boundary layers of these airfoils were obtained at pre-stall, near-stall, and post-stall angles of attack. Velocity and pressure survey results over the airfoil and in the associated wake, are presented for fully attached flow conditions through the stalled flow condition. Extensive force, pressure, tuft survey, hot-film survey, local skin friction and boundary layer data are also included.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3530 , NAS 1.26:3530 , AR-79-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Studies of light-twin wing-body interference (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The results of an analytical study of aerodynamic interference effects for a light twin aircraft are presented. The data presented concentrates on the influence of a wing on a body (the fuselage). Wind tunnel comparisons of three fillets are included, with corresponding computational analysis. Results indicate that potential flow analysis is useful to guide the design of intersection fairings, but experimental tuning is still required. While the study specifically addresses a light twin aircraft, the methods are applicable to a wide variety of aircraft.
    Keywords: AERODYNAMICS
    Type: SAE PAPER 830709
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Feasibility study of aileron and spoiler control systems for large horizontal axis wind turbines (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The feasibility of using aileron or spoiler controls as alternates to pitch control for large horizontal axis wind turbines was studied. The NASA Mod-0 100 kw machine was used as the basis for the study. Specific performance studies were conducted for 20% chord ailerons over the outboard 30% span, and for 10% chord spoilers over the same portion of the span. Both control systems utilized control deflections up to 60 deg. Results of the study show that either ailerons or spoilers can provide the control necessary to limit turbine power in high wind conditions. The aileron system, as designed, provides overspeed protection at hurricane wind speeds, low wind speed starting torque of 778 N-m (574 ft. lb) at 3.6 m/sec, and a 1.3 to 1.5% increase in annual energy compared to a fixed pitch rotor. The aileron control system preliminary design study includes aileron loads analysis and the design of a failsafe flyweight actuator for overspeed protection in the event of a hydraulic system failure.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-159856 , DOE/NASA/3277-1 , WER-10
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Computational and experimental studies of light twin aerodynamic interference (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The results of an analytical and experimental study of aerodynamic interference effects for a light twin aircraft are presented. Both the influence of a body (either fuselage or nacelle) on a wing and the influence of a wing on a body are studied. The wing studied uses a new natural laminar flow airfoil with variable camber movable trailing edge. A three-dimensional panel method program utilizing surface source and surface doublet singularities was used to design wing-nacelle and wing-fuselage fairings. Experiments were conducted using a 1/6 scale reflection plane model. Forces, pressures, and surface flow visualization results are presented. Results indicate that potential flow analysis is useful to guide the design of intersection fairings, but experimental tuning is still required. While the study specifically addressed a light twin aircraft, the methods are applicable to a wide variety of aircraft.
    Keywords: AERODYNAMICS
    Type: International Council of the Aeronautical Sciences; Aug 22, 1982 - Aug 27, 1982; Seattle, WA
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Natural laminar flow flight experiments on a swept-wing business jet (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Flight test experiments have been conducted to measure the extent and nature of laminar flow on a smoothed test region of a swept-wing business jet. Surface hot film anemometers and sublimating chemicals were used for transition detection. Surface pressure distributions were measured using pressure belts. Instrumentation techniques and problems are presented. Correlation was obtained between the hot film and sublimating chemicals for transition detection. Taylor-Goertler vortices were observed for some flight conditions. Boundary layer stability analysis is being conducted using measured pressure distributions to determine the correlation possible for transition prediction on swept wings.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-2189
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Wind tunnel force and pressure tests (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Force and surface pressure distributions were measured for a 13% medium speed (NASA MS(1)-0313) airfoil fitted with 20% aileron, 25% slotted flap and 10% slot lip spoiler. All tests were conducted in the Walter Beech Memorial Wind Tunnel at a Reynolds number of 2.2 million and a Mach number of 0.13. Results include lift, drag, pitching moments, control surface normal force and hinge moments, and surface pressure distributions. The basic airfoil exhibits low speed characteristics similar to the GA(W)-2 airfoil. Incremental aileron and spoiler performance are quite comparable to that obtained on the GA(W)-2 airfoil. Slotted flap performance on this section is reduced compared to the GA(W)-2, resulting in a highest c sub l max of 3.00 compared to 3.35 for the GA(W)-2.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3439 , NAS 1.26:3439 , WSU-AR-78-4
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Summary of high-lift and control surface research on NASA general aviation airfoils (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Summary findings and bibliographical information are presented for airfoil and airfoil-related research conducted at Wichita State University during the past decade. Topics include flap, aileron, and spoiler design data for new airfoils, extensive flow measurements, modifications to older airfoils, new symmetrical sections and contributions to analytical methods for cases with partial separation.
    Keywords: AERODYNAMICS
    Type: SAE PAPER 810629 , Business Aircraft Meeting and Exposition; Apr 07, 1981 - Apr 10, 1981; Wichita, KS
    Format: text
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