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  • 1
    facet.materialart.
    Unknown
    In-flight measurements of wing ice shapes and wing section drag increases caused by natural icing conditions (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Aircraft icing flight research was performed in natural icing conditions with a twin engine computer type STOL aircraft. In-flight measurements were made of the icing cloud environment, the shape of the ice accretion on the wing, and the corresponding increase in the wing section drag. Results are presented for three icing encounters. On one flight, the wing section drag coefficient increased 35 percent over the uniced baseline for cruise conditions while a 43 percent increase was observed at an aircraft angle of attack of 6.2 degrees.
    Keywords: AERODYNAMICS
    Type: NASA-TM-87301 , E-3013 , NAS 1.15:87301
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Unknown
    Development of a laser velocimeter for a large transonic wind tunnel (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: On a 8 x 6 Foot Supersonic Wind Tunnel a laser velocimeter was utilized in the testing of advanced high speed turbopropellers. The system, using a 15-W argon-ion laser, a 3-beam 2-axis transmitting-receiving optics package, a zoom lens with 1- to 4-m focal lengths, and a 0.4-m corner mirror was initially assembled and tested in the checkout room. During the time the system was located in the checkout area, experience was acquired in the alignment and operation of the system and the data acquisition system and software were developed. By using air jets to simulate tunnel air flow, the system worked quite well. However, problems with beam alignment arose because of reduced atmospheric pressure. Mounting the laser into a vessel maintained at atmospheric pressure with deflectors mounted to the external walls improved operation for about 2 hours before misalignment reoccurred. The system was remounted to the positioning platform in an enclosure that provides both thermal and acoustic isolation.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA. Langley Research Center Flow Visualization and Laser Velocimetry for Wind Tunnels; p 243-247
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Unknown
    Propeller flow visualization techniques (1982)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Propeller flow visualization techniques were tested. The actual operating blade shape as it determines the actual propeller performance and noise was established. The ability to photographically determine the advanced propeller blade tip deflections, local flow field conditions, and gain insight into aeroelastic instability is demonstrated. The analytical prediction methods which are being developed can be compared with experimental data. These comparisons contribute to the verification of these improved methods and give improved capability for designing future advanced propellers with enhanced performance and noise characteristics.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA. Langley Research Center Flow Visualization and Laser Velocimetry for Wind Tunnels; p 75-89
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Unknown
    Development and utilization of a laser velocimeter system for a large transonic wind tunnel (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The need for measurements of the velocity flow field about spinner propeller nacelle configurations at Mach numbers to 0.8 was met by a specially developed laser velocimeter system. This system, which uses an argon ion laser and 4 beam 2 color optics, was required to operate in the hostile environment associated with the operation of a large transonic wind tunnel. To overcome the conditions present in locating the sensitive optics in close proximity to the wind tunnel, an isolation system was developed. The system protects the velocimeter from the high vibrations, elevated temperatures, destructive acoustic pressures and low atmospheric pressures attendant with the operation of the wind tunnel. The system was utilized to map the flow field in front of, behind and in between the rotating blades of an advanced swept blade propeller model at a Mach number of 0.8. The data collected by the system will be used to correlate and verify computer analyses of propeller nacelle flow fields and propeller performance.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-TM-82886 , E-1264 , NAS 1.15:82886
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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