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  • 1
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    Instrumentation, techniques and data reduction associated with airfoil testing programs at Wichita State University (1978)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: Two dimensional airfoil testing was conducted at the Wichita State University Beech Wind Tunnel for a number of years. The instrumentation developed and adapted during this period of testing for determination of flow fields along with traversing mechanisms for these probes are discussed. In addition, some of the techniques used to account for interference effects associated with the apparatus used for this two dimensional testing are presented. The application of a minicomputer to the data reduction and presentation is discussed.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1, Pt. 2; p 539-558
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Performance and aerodynamic braking of a horizontal-axis wind turbine from small-scale wind tunnel tests (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Wind tunnel tests of three 20" diameter, zero twist, zero pitch wind turbine rotor models were conducted in a 7' x 10' wind tunnel to determine the performance of such rotors with NACA 23024 and NACA 64 sub 3-621 airfoil sections. Aerodynamic braking characteristics of a 38% span, 30% chord, vented aileron configuration were measured on the NACA 23024 rotor. Surface flow patterns were observed using fluorescent mini-tufts attached to the suction side of the rotor blades. Experimental results with and without ailerons are compared to predictions using airfoil section data and a momentum performance code. Results of the performance studies show that the 64 sub 3-621 rotor produces higher peak power than the 23024 rotor for a given rotor speed. Analytical studies, however, indicate that the 23024 should produce higher power. Transition strip experiments show that the 23024 rotor is much more sensitive to roughness than the 64 sub 3-621 rotor. These trends agree with analytical predictions. Results of the aileron test show that this aileron, when deflected, produces a braking torque at all tip speed ratios. In free wheeling coastdowns the rotor blade stopped, then rotated backward at a tip speed ratio of -0.6.
    Keywords: ENERGY PRODUCTION AND CONVERSION
    Type: NASA-CR-180812 , DOE/NASA/3277-4 , NAS 1.26:180812
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Further results of natural laminar flow flight test experiments (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Flight test experiments were conducted to measure the extent and nature of natural laminar flow on a smoothed test region of a swept-wing business jet wing. Surface hot film anemometry and sublimating chemicals were used for transition detection. Surface pressure distributions were measured using pressure belts. Engine noise was monitored by a microphone attached to the wing surface to study possible acoustic effects on stability of the laminar boundary layer. Side-slip conditions were flown to simulate changes in effective wing sweep. Flight instrumentation and ground data analysis techniques and a method for measuring intermittency of turbulence are described. Correlation was obtained between the hot film gage signals and chemicals for transition detection. Cross-flow vortices were observed for some flight conditions. Results of spectral and statistical analysis of the hot film signals for various flight test conditions are presented.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAE PAPER 850862
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Wing-tip vanes as vortex attenuation and induced drag reduction devices (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Analytical studies have been conducted to examine the feasibility of utilizing wing tip turbines to remove swirl from the wing trailing vortex, and hence reduce the potential for upset of following aircraft. Energy recovery from the turbines is also analyzed. A computer routine has been developed to permit rapid parametric studies of various tip turbine designs. It is shown that the optimum turbine is a non-rotating set of vanes which reduce swirl and recover energy in the form of reduced overall configuration induced drag. A specific case study indicates a 23% reduction in induced drag for a rectangular wing of aspect ratio 5.33, operated at a lift coefficient at 1.0.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Kansas Univ. Proc. of the NASA, Ind., Univ., Gen. Aviation Drag Reduction Workshop; p 203-214
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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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
  • 6
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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
  • 7
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    Experimental Studies of Flow Separation of the NACA 2412 Airfoil at Low Speeds (1997)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Wind tunnel tests have been conducted on an NACA 2412 airfoil section at Reynolds number of 2.2 x 10(exp 6) and Mach number of 0.13. Detailed measurements of flow fields associated with turbulent boundary layers have been obtained at angles of attack of 12.4 degrees, 14.4 degrees, and 16.4 degrees. Pre- and post-separated velocity and pressure survey results over the airfoil and in the associated wake are presented. Extensive force, pressure, tuft survey, hot-film survey, local skin friction, and boundary layer data are also included. Pressure distributions and separation point locations show good agreement with theory for the two layer angles of attack. Boundary layer displacement thickness, momentum thickness, and shape factor agree well with theory up to the point of separation. There is considerable disparity between extent of flow reversal in the wake as measured by pressure and hot-film probes. The difference is attributed to the intermittent nature of the flow reversal.
    Keywords: AERODYNAMICS
    Type: NASA-CR-197497 , NAS 1.26:197497 , AR77-3
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Experimental studies of flow separation of the GA(W)-2 airfoil at low speeds (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Wind tunnel tests have been conducted on a NASA GA(W)-2 airfoil section at Reynolds number of 2.2 x 10(exp 6) and Mach number of 0.13. Detailed measurements of flow fields associated with turbulent boundary layers have been obtained at angles of attack of 10.3, 14.4, and 18.3 deg. Pre- and post-separated velocity and pressure survey results over the airfoil and in the associated wake are presented. Extensive force, pressure, tuft survey, hot-film survey, local skin friction, and boundary layer data are also included. Pressure distributions and separation point locations show good agreement with theory for the two lower angles of attack. Boundary layer displacement thickness, momentum thickness, and shape factor agree well with theory up to the point of separation. There is considerable disparity between extent of flow reversal in the wake as measured by pressure and hot-film probes. The difference is attributed to the intermittent nature of the flow reversal.
    Keywords: AERODYNAMICS
    Type: NASA-CR-197254 , NAS 1.26:197254 , AR77-4
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    An experimental investigation of the flow fields about delta and double-delta wings at low speeds (1966)
    In:  CASI
    Details
    Publication Date: 2019-05-30
    Description: Low speed wind tunnel analysis of flow fields about delta and double delta wings
    Keywords: AERODYNAMICS
    Type: NASA-CR-521
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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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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