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  • 1985-1989  (7)
  • 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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    Wall shear stress measurements using a new transducer (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A new instrument has been developed for direct measurement of wall shear stress. This instrument is simple and symmetric in design with small moving mass and no internal friction. Features employed in the design of this instrument eliminate most of the difficulties associated with the traditional floating element balances. Vibration problems associated with the floating element skin friction balances have been found to be minimized by the design features and optional damping provided. The unique design of this instrument eliminates or reduces the errors associated with conventional floating-element devices: such as errors due to gaps, pressure gradient, acceleration, heat transfer and temperature change. The instrument is equipped with various sensing systems and the output signal is a linear function of the wall shear stress. Measurement made in three different tunnels show good agreement with theory and data obtained by the floating element devices.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: AIAA PAPER 86-1092
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Summary of test techniques used in the NASA Langley 0.3-meter Transonic Cryogenic Tunnel (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper describes test techniques used to obtain data in the 0.3-m Transonic Cryogenic Tunnel. Main sections include steady aerodynamic testing, unsteady aerodynamics, non-intrusive measurements, tunnel performance, and fluid mechanics. Test techniques with adequate previous documentation are briefly presented and referenced, and those for which no documentation yet exists are more thoroughly discussed. Attention is given to the model building and instrumentation technology necessary for testing at high Reynolds numbers in the presence of free transition. It is concluded that the testing techniques thus far demonstrated in the 0.3-m TCT are on par with modern transonic tunnels, and that the specialized techniques needed to exploit the advantages of cryogenic operation can be realized.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AIAA PAPER 86-0745
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Cryogenic wind tunnels for high Reynolds number testing (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A compilation of lectures presented at various Universities over a span of several years is discussed. A central theme of these lectures has been to present the research facility in terms of the service it provides to, and its potential effect on, the entire community, rather than just the research community. This theme is preserved in this paper which deals with the cryogenic transonic wind tunnels at Langley Research Center. Transonic aerodynamics is a focus both because of its crucial role in determining the success of aeronautical systems and because cryogenic wind tunnels are especially applicable to the transonics problem. The paper also provides historical perspective and technical background for cryogenic tunnels, culminating in a brief review of cryogenic wind tunnel projects around the world. An appendix is included to provide up to date information on testing techniques that have been developed for the cryogenic tunnels at Langley Research Center. In order to be as inclusive and as current as possible, the appendix is less formal than the main body of the paper. It is anticipated that this paper will be of particular value to the technical layman who is inquisitive as to the value of, and need for, cryogneic tunnels.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: NASA-TM-87743 , NAS 1.15:87743
    Format: application/pdf
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  • 5
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    The construction of airfoil pressure models by the plate method: Achievements, current research, technology development and potential applications (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A method of constructing airfoils by inscribing pressure channels on the face of opposing plates, bonding them together to form one plate with integral channels, and contour machining this plate to form an airfoil model is described. The research and development program to develop the bonding technology is described as well as the construction and testing of an airfoil model. Sample aerodynamic data sets are presented and discussed. Also, work currently under way to produce thin airfoils with camber is presented. Samples of the aft section of a 6 percent airfoil with complete pressure instrumentation including the trailing edge are pictured and described. This technique is particularly useful in fabricating models for transonic cryogenic testing, but it should find application in a wide ange of model construction projects, as well as the fabrication of fuel injectors, space hardware, and other applications requiring advanced bonding technology and intricate fluid passages.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: NASA-TM-87613 , NAS 1.15:87613
    Format: application/pdf
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  • 6
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    Description of the insulation system for the Langley 0.3-Meter Transonic Cryogenic Tunnel (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The thermal insulation system of the Langley 0.3 Meter Transonic Cryogenic Tunnel is described. The insulation system is designed to operate from room temperature down to about 77.4 K, the temperature of liquid nitrogen at 1 atmosphere. A detailed description is given of the primary insulation sytem consists of glass fiber mats, a three part vapor barrier, and a dry positive pressure purge system. Also described are several secondary insulation systems required for the test section, actuators, and tunnel supports. An appendix briefly describes the original insulation system which is considered inferior to the one presently in place. The time required for opening and closing portions of the insulation system for modification or repair to the tunnel has been reduced, typically, from a few days for the original thermal insulating system to a few hours for the present system.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: NASA-TM-86274 , L-15723 , NAS 1.15:86274
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Measurements in the flow field of a cylinder with a laser transit anemometer and a drag rake in the Langley 0.3 m transonic cryogenic tunnel (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An experiment was conducted at the 0.3 m Transonic Cryogenic Tunnel using a Laser Transit Anemometer (LTA) to probe the flow field around a 3.05 centimeter-diameter circular cylinder. Measurements were made along the stagnation line and determination of particle size was evaluated by their ability to follow the flow field. The LTA system was also used to scan into the boundary layer near the 45 degree point on the model. Results of these scans are presented in graphic and tabular form. Flow field particle seeding was accomplished by inbleeding dry service air. The residual moisture (5-10 ppm) condensed and formed ice particles which served as Mie scattering centers for the LTA detection system. Comparison of data taken along the stagnation streamline with theory indicated that these particles tracked the velocity gradient of the flow. Tunnel operating conditions for the tests were a Mach number of 0.3, a pressure of 1.93 x 100000 n/m squared, and a temperature of 225 degrees K. Free stream Mach number and pressure were varied for the particle size determination.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: NASA-TM-86399 , NAS 1.15:86399
    Format: application/pdf
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