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  • 1
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    Flight research on natural laminar flow (1986)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Five decades of flight experiences with natural laminar flow (NLF) have provided a basis of understanding how this technology can be used for reduction of viscous drag on modern practical aircraft. The effects of cruise unit Reynolds number on NLF achievability and maintainability; compressibility effects on Tollmein-Schlichting growth; flight experiment on the Cessna Citation III business jet; flight instrumentation on Lear 28/29; OV-I NLF engine nacelle experiments; and viscous drag reduction are examined.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Langley Symposium on Aerodynamics, Volume 1; p 461-474
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    NASA aerial applications wake interaction research (1982)
    In:  Other Sources
    Details
    Publication Date: 2018-12-01
    Description: A computer code has been developed for predicting trajectories of particles released in the wakes of airplanes or helicopters. The code accounts for effects of turbulence, crosswind, propeller slipstream, terrain variations, and plant canopy density on particle trajectories. Comparisons are given between experiments and theory. Applications of the code for spray pattern improvement are illustrated.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Advanced boundary layer transition measurement methods for flight applications (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: In modern laminar flow flight 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 transition modes of interest in current flight investigations include the viscous Tollmien-Schlichting instability, the inflectional instability at laminar separation, and the crossflow inflectional instability, as well as others. This paper presents the results to date of research on advanced devices and methods used for the study of laminar boundary-layer transition phenomena in the flight environment. Recent advancements in the development of arrayed hot-film devices and of a new flow visualization method are discussed. Arrayed hot-film devices have been designed to detect the presence of laminar separation, and of crossflow vorticity. The advanced flow visualization method utilizes color changes in liquid-crystal coatings to detect boundary-layer transition at high altitude flight conditions. Flight and wind tunnel data are presented to illustrate the design and operation of these advanced methods. These new research tools provide information on disturbance growth and transition mode which is essential to furthering our understanding of practical design limits for applications of laminar flow technology.
    Keywords: AIRCRAFT INSTRUMENTATION
    Type: AIAA PAPER 86-9786
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    NASA wake interactions research and applications (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This report describes the development, validation, and application of a computer program for predicting trajectories and ground deposit patterns for particle released in the wakes of airplanes or helicopters. The computer program accounts for the effects of atmospheric turbulence, crosswind, propeller slipstream, terrain variations, evaporation, and plant canopy density on the particle trajectories. In order to validate the prediction method, some comparisons are shown between experimental data and theoretical predictions. Possible applications of the code for spray pattern improvement and for mission operations analysis are illustrated. In addition, the effect of winglets on pattern uniformity, drift, and airplane aerodynamics are presented.
    Keywords: AERODYNAMICS
    Type: SAE PAPER 830764
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    The laminar separation sensor - An advanced transition measurement method for use in wind tunnels and flight (1987)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Wind tunnel and flight tests have recently been conducted by the NASA Langley Research Center to explore the ability of laminar separation hot-film sensors to identify the presence of laminar separation as the principal mode of instability amplification leading to transition. This paper describes the different sensor configurations evaluated during the course of testing and presents results from the flight and wind tunnel evaluations. Plans for the next generation of sensors are briefly discussed.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: SAE PAPER 871018
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    An experimental and theoretical investigation of deposition patterns from an agricultural airplane (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A flight test program has been conducted with a representative agricultural airplane to provide data for validating a computer program model which predicts aerially applied particle deposition. Test procedures and the data from this test are presented and discussed. The computer program features are summarized, and comparisons of predicted and measured particle deposition are presented. Applications of the computer program for spray pattern improvement are illustrated.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2348 , L-15718 , NAS 1.60:2348
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Flight evaluation of an insect contamination protection system for laminar flow wings (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The maintenance of minimum wing leading edge contamination is critical to the preservation of drag-reducing laminar flow; previous methods for the prevention of leading edge contamination by insects have, however, been rendered impractical by their excessive weight, cost, or inconvenience. Attention is presently given to the results of a NASA flight experiment which evaluated the performance of a porous leading edge fluid-discharge ice protection system in the novel role of insect contamination removal; high insect contamination conditions were also noted in the experiment. Very small amounts of the fluid are found to be sufficient for insect contamination protection.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SAE PAPER 850860
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Identifying Boundary-Layer Transitions on Aircraft Skin (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Sublimating chemicals offer accurate, low-cost way of indicating laminarto-turbulent flow transisions on surfaces of aircraft. Aerodynamic surfaces coated with thin film of such volatile chemical solids as naphthalene, diphenyl, acenaphthene, or fluorene. Film sublimes rapidly because of high local shear stress and heat transfer in boundary layer. Coating appears white in regions where chemical remained on surface indicating laminar flow; regions where chemical disappeared indicate turbulent flow.
    Keywords: MECHANICS
    Type: LAR-13089 , NASA Tech Briefs (ISSN 0145-319X); 8; 2; P. 232
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Aerodynamic design data for a cruise-matched high performance single-engine airplane (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Design data are presented for a class of high-performance single-engine business airplanes. The design objectives include a cruise speed of 300 knots, a cruise altitude of 10,700 m (35,000 ft), a cruise payload of six passengers (including crew and baggage), and a no-reserves cruise range of 1300 n.mi. Two unconventional aerodynamic technologies were evaluated: the individual and combined effects of cruise-matched wing loading and of a natural laminar flow airfoil were analyzed. The trade-off data presented illustrate the ranges of wing geometries, propulsion requirements, airplane weights, and aerodynamic characteristics which are necessary to meet the design objectives. Very large design and performance improvements resulted from use of the aerodynamic technologies evaluated. It is shown that the potential exists for achieving more than 200-percent greater fuel efficiency than is achieved by current airplanes capable of similar cruise speeds, payloads, and ranges.
    Keywords: AERODYNAMICS
    Type: SAE PAPER 810625 , Business Aircraft Meeting and Exposition; Apr 07, 1981 - Apr 10, 1981; Wichita, KS
    Format: text
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    NASA TECHNICAL REPORTS
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