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  • 1
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    Advanced measurement techniques, part 1 (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: In modern laminar flow flight and wind tunnel research, it is important to understand the specific cause(s) of laminar to turbulent boundary layer transition. Such information is crucial to the exploration of the limits of practical application of laminar flow for drag reduction on aircraft. The process of transition involves both the possible modes of disturbance growth, and the environmental conditioning of the instabilities by freestream or surface conditions. The possible modes of disturbance growth include viscous, inviscid, and modes which may bypass these natural ones. Theory provides information on the possible modes of disturbance amplification, but experimentation must be relied upon to determine which of those modes actually dominates the transition process in a given environment. The results to date of research on advanced devices and methods used for the study of transition phenomena in the subsonic and transonic flight and wind tunnel environments are presented.
    Keywords: AERODYNAMICS
    Type: Research in Natural Laminar Flow and Laminar-Flow Control, Part 2; p 317-340
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Insect contamination protection for laminar flow surfaces (1986)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The ability of modern aircraft surfaces to achieve laminar flow was well-accepted in recent years. Obtaining the maximum benefit of laminar flow for aircraft drag reduction requires maintaining minimum leading-edge contamination. Previously proposed insect contamination prevention methods have proved impractical due to cost, weight, or inconvenience. Past work has shown that insects will not adhere to water-wetted surfaces, but the large volumes of water required for protection rendered such a system impractical. The results of a flight experiment conducted by NASA to evaluate the performance of a porous leading-edge fluid discharge ice protection system operated as an insect contamination protections system are presented. In addition, these flights explored the environmental and atmospheric conditions most suitable for insect accumulation.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Langley Symposium on Aerodynamics, Volume 1; p 539-556
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    In-flight detection of Tollmien-Schlichting instabilities in laminar flow (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper presents the results of a recent flight experiment conducted to evaluate surface-mounted hot-film sensors designed to detect Tollmien-Schlichting instability in the boundary layer in flight. Flight data are presented to illustrate the design and operation of the sensors and to provide information on disturbance growth and transition mode. The results of calculations using a boundary-layer analysis code and boundary-layer linear stability analysis methods are included.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: SAE PAPER 871016
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    A New Method for Laminar Boundary Layer Transition Visualization in Flight: Color Changes in Liquid Crystal Coatings (1986)
    In:  CASI
    Details
    Publication Date: 2019-10-31
    Description: The visualization of laminar to turbulent boundary layer transition plays an important role in flight and wind tunnel aerodynamic testing of aircraft wing and body surfaces. Visualization can help provide a more complete understanding of both transition location as well as transition modes; without visualization, the transition process can be very difficult to understand. In the past, the most valuable transition visualization methods for fight applications included sublimating chemicals and oil flows. Each method has advantages and limitations. In particular, sublimating chemicals are impractical to use in subsonic applications much above 20,000 feet because of the greatly reduced rates of sublimation at lower temperatures (less than -4 degrees Fahrenheit). Both oil flow and sublimating chemicals have the disadvantage of providing only one good data point per flight. Thus, for many important flight conditions, transition visualization has not been readily available. This paper discusses a new method for visualizing transition in fight by the use of liquid crystals. The new method overcomes the limitations of past techniques, and provides transition visualization capability throughout almost the entire altitude and speed ranges of virtually all subsonic aircraft flight envelopes. The method also has wide applicability for supersonic transition visualization in flight and for general use in wind tunnel research over wide subsonic and supersonic speed ranges.
    Keywords: Aerodynamics
    Type: NASA-TM-87666 , NAS 1.15:87666
    Format: application/pdf
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  • 5
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    Laminar-Separation Sensor (1988)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: Sensor detects flow reversal in boundary layer. Laminar-separation sensor provides means for detecting laminar-separation bubble by use of very thin, surface-mounted sensor. Consists of flush array of three proximate thin films. Middle film electronically heated by means of constant-temperature anemometer (CTA). Outer films, one upstream and one downstream of middle film, incorporated into bridge circuit to respond as resistance thermometers. This sensor provides only known surface-mounted means for positively identifying pressure of laminar separation as cause of boundary-layer transition.
    Keywords: MECHANICS
    Type: LAR-13463 , NASA Tech Briefs (ISSN 0145-319X); 12; 8; P. 72
    Format: text
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  • 6
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    Coatings Show Laminar Boundary-Layer Transitions (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: New method, utilizing liquid-crystal coatings, provides means to visualize transition in flight. Difference in levels of relative shear stress or skin friction between laminar and turbulent boundary layers one order of magnitude. Difference in skin friction is physical parameter to which liquid crystals respond. Transition measured and documented on aircraft in flight at altitudes above 20,000 ft., up to at least 50,000 ft. at subsonic and supersonic speeds. Technique has rapid response and reversible; capability of indicating unlimited number of transition locations during single flight.
    Keywords: MECHANICS
    Type: LAR-13554 , NASA Tech Briefs (ISSN 0145-319X); 11; 8; P. 60
    Format: text
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