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  • AERODYNAMICS  (4)
  • RESEARCH AND SUPPORT FACILITIES (AIR)  (2)
  • COMPOSITE MATERIALS  (1)
  • 1
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    Flow diagnostics and visualization in wind tunnels and flight (1986)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The Langley Research Center has a concentrated and directed effort under way to develop both conventional and non-intrusive diagnostic instrumentation. These instruments are being developed to operate over large Mach number, total temperature, and total pressure ranges. Efforts are being made to evaluate the measurements made by the various instruments to determine the most accurate and reliable instrument to be used under a given flow environment. Although only one flow visualization technique was described, there are many different types presently being used at Langley Research Center.
    Keywords: AERODYNAMICS
    Type: Langley Symposium on Aerodynamics, Volume 1; p 279-310
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    A study of laminar separation bubble in the concave region of an airfoil using laser velocimetry (1985)
    In:  Other Sources
    Details
    Publication Date: 2018-12-01
    Description: Laser velocimetry (LV) was used to study the nature of laminar separation bubbles in the concave region of a 1.83-meter airfoil model which was tested in the NASA Langley Low Turbulence Pressure Tunnel. Three component, coincident data from LV measurements including histograms of particle velocity, mean velocity profiles, turbulence intensity, and Reynolds stresses within the shear layer were used to determine the locations of laminar separation, transition, and turbulent reattachment. boundary-layer parameters determined from velocity profiles were used to compare the results with existing empirical relations for describing the laminar separation bubble.
    Keywords: AERODYNAMICS
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    The Goertler instability on an airfoil (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Goertler vortices arise in boundary layers along concave surfaces due to centrifugal effects. This paper presents some results of an experiment conducted to study the development of these vortices on an airfoil with a pressure gradient in the concave region where an attached laminar boundary layer was insured with suction through a perforated panel. The sublimating chemical technique was used to visualize Goertler vortices and the velocity field was measured by laser velocimetry. The vortex wavelength clearly varied with Goertler number as predicted by linear theory. Both flow visualization and velocity measurements indicated vortex damping in the convex zone. Secondary instability was observed at the higher Goertler numbers.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 85-0491
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    The vulnerability of commercial aircraft avionics to carbon fibers (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Avionics components commonly used in commercial aircraft were tested for vulnerability to failure when operated in an environment with a high density of graphite fibers. The components were subjected to a series of exposures to graphite fibers of different lengths. Lengths used for the tests were (in order) 1 mm, 3 mm, and 10 mm. The test procedure included subjecting the equipment to characteristic noise and shock environments. Most of the equipment was invulnerable or did not fail until extremely high average exposures were reached. The single exception was an air traffic control transponder produced in the early 1960's. It had the largest case open area through which fibers could enter and it had no coated boards.
    Keywords: COMPOSITE MATERIALS
    Type: NASA-CR-159213
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Laser velocimeter survey about a NACA 0012 wing at low angles of attack (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An investigation was conducted in the Langley V/STOL tunnel with a laser velocimeter to obtain measurements of airflow velocities about a wing at low angles of attack. The applicability of the laser velocimeter technique for this purpose in the V/STOL tunnel was demonstrated in this investigation with measurement precision bias calculated at -1.33 percent to 0.91 percent and a random uncertainty calculated at + or - 0.47 percent. Free stream measurements were obtained with this device and compared with velocity calculations from pitot static probe data taken near the laser velocimeter measurement location. The two measurements were in agreement to within 1 percent. Velocity measurement results about the centerline at 0.6 degrees angle of attack were typically those expected. At 4.75 degrees, the velocity measurements indicated that a short laminar separation bubble existed near the leading edge with an oscillating shear layer.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: NASA-TM-74040
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    A laser velocimeter flow survey above a stalled wing (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A laser velocimeter operating in the backscatter mode was used to survey the flow about a stalled wing installed in the Langley V/STOL tunnel. Mean velocities and magnitudes of velocity fluctuations were calculated from measurements of two orthogonal components of velocity. Free shear mixing layers above and below a large separated flow region were defined. Velocity power spectra were calculated at two points in the flow field. The flow-field survey was carried out about a rectangular aspect-ratio-8 wing with an airfoil section. The wing angle of attack was 19.4 deg, the Mach number was 0.148, and the nominal Reynolds number was 1 x 1 million.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1266 , AVRADCOM-TR-78-50
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Development of a controllable particle generator for LV seeding in hypersonic wind tunnels (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The paper describes the considerations that went into the development of a controllable particle generator for laser velocimeter seeding in a hypersonic wind tunnel operating at 3.45 million N/sq m, 533 K, and stream speed of about 1000 m/sec. Operating conditions determined the choice of a silicone oil as the material, and the requirement that the particle follow the flow within a certain accuracy range put constraints on the allowable particle size range. The principle of the particle generating device chosen was that of the LaMer generator, in which a liquid is first vaporized, mixed with the carrier gas, and then condensed under carefully controlled conditions. Preliminary results of studies on the effect of various apparatus parameters on the particle median diameter are given.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: Minnesota Symposium on Laser Anemometry; Oct 22, 1975 - Oct 24, 1975; Bloomington, MN
    Format: text
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