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  • 1
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    Laminar flow flight experiments - A review (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: A development history is presented for flight tests of flow-laminarizing technologies, from the wooden-structure wing glove used with the B-18 of about 1940 to the X-21 of 1963-1965 and the wing incidence-varying tests conducted with gloved-wing F-111 and F-14 variable-sweep aircraft in more recent years. Natural laminar flight control testing has also been conducted with a B 757 airliner. Over the years, increasing attention has been given to the treatment of the leading edge of laminar flow wings in order to prevent flow instabilities that precipitate flow transition to turbulence farther aft.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: In: Natural laminar flow and laminar flow control (A93-41776 17-02); p. 23-71.
    Format: text
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  • 2
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    Applied aspects of laminar-flow technology (1990)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: An account is given of the development status and performance levels achieved with natural laminar flow (NLF), extended wing chord laminar flow control (LFC), and hybrid laminar flow control (HLFC) concepts combining NLF and partial-chord LFC in the leading-edge region. Attention is given to NLF wing structure construction methods capable of achieving the requisite surface-irregularity tolerances, LFC through wing surface suction slots or perforated skins, and the deleterious effects of insects, ice crystals, and noise disturbance inputs on the ability of NLF, LFC, and HLFC wings to maintain effective laminar flow operation.
    Keywords: AERODYNAMICS
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  • 3
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    Laminar-flow flight experiments (1989)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The flight testing conducted over the past 10 years in the NASA laminar-flow control (LFC) will be reviewed. The LFC program was directed towards the most challenging technology application, the high supersonic speed transport. To place these recent experiences in perspective, earlier important flight tests will first be reviewed to recall the lessons learned at that time.
    Keywords: AERODYNAMICS
    Type: Transonic Symposium: Theory, Application and Experiment, Volume 2; p 59-104
    Format: application/pdf
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  • 4
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    Laminar flow integration: Flight tests status and plans (1986)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Under the Aircraft Energy Efficiency - Laminar Flow Control Program, there are currently three flight test programs under way to address critical issues concerning laminar flow technology application to commercial transports. The Leading-Edge Flight Test (LEFT) with a JetStar aircraft is a cooperative effort with the Ames/Dryden Flight Research Facility to provide operational experience with candidate leading-edge systems representative of those that might be used on a future transport. In the Variable Sweep Transition Flight Experiment (VSTFE), also a cooperative effort between Langley and Ames/Dryden, basic transition data on an F-14 wing with variable sweep will be obtained to provide a data base for laminar flow wing design. Finally, under contract to the Boeing Company, the acoustic environment on the wing of a 757 aircraft will be measured and the influence of engine noise on laminar flow determined with a natural laminar flow glove on the wing. The status and plans for these programs are reported.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Langley Symposium on Aerodynamics, Volume 1; p 485-518
    Format: application/pdf
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  • 5
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    Energy Efficient Transport - Technology in hand (1984)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: Technologies developed through NASA's Energy Efficient Transport Program are described. The program was charged with research in advanced aerodynamics and active controls, with the goal of increasing the fuel efficiency of transport aircraft by 15 to 20 percent. Research in aerodynamics was directed toward the development of high-aspect-ratio supercritical wings, winglets, computational design methodology, high-lift devices, propulsion airframe integration, and surface coatings. The active control portion of the program investigated Wing Load Alleviation (WLA) through the use of active controls, drag reduction, and the effect of active pitch controls on fuel consumption. It was found that applying active control functions at the beginning of the aircraft design cycle brings the best benefit, and that if active control and advanced aerodynamic airframe configurations are applied to transport aircraft design concurrently with new lightweight materials, fuel consumption can be reduced by as much as 40 percent.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Aerospace America (ISSN 0740-722X); 22
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  • 6
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    The EET Horizontal Tails Investigation and the EET Lateral Controls Investigation (1981)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: In the energy efficient transport (EET) Horizontal Tails Investigation, aerodynamic data were measured for five different horizontal tails on a full span model with a wide body fuselage. Three of the horizontal tails were low tail configurations and two were T tail configurations. All tails were tested in conjunction with two wings, a current wide body wing and a high aspect ratio supercritical wing. Local downwash angles and dynamic pressures in the vicinity of the tails were measured using a yaw head rake. The results provide a comparison of the aerodynamic characteristics of the two wing configurations at trimmed conditions for Mach numbers between 0.60 and 0.90. In the EET Lateral Controls Investigation, the control effectiveness of a conventional set of lateral controls was measured over a Mach number range from 0.60 to 0.90 on a high aspect ratio supercritical wing semispan model. The conventional controls included a high speed aileron, a low speed aileron, and six spoiler segments. The wing was designed so that the last 25% of the chord is removable to facilitate testing of various control systems. The current status and an indication of the data obtained in these investigations are presented.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: Advan. Aerodyn. and Active Controls; p 123-133
    Format: application/pdf
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  • 7
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    Analysis for the application of hybrid laminar flow control to a long-range subsonic transport aircraft (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The FLOPS aircraft conceptual design/analysis code has been used to evaluate the effects of incorporating hybrid laminar flow control (HLFC) in a 300-passenger, 6500 n. mi. range, twin-engine subsonic transport aircraft. The baseline configuration was sized to account for 50 percent chord laminar flow on the wing upper surface as well as both surfaces of the empennage airfoils. Attention is given to the additional benefits of achieving various degrees of laminar flow on the engine nacelles, and the horsepower extraction and initial weight and cost increments entailed by the HLFC system. The sensitivity of the results obtained to fuel-price and off-design range are also noted.
    Keywords: AERODYNAMICS
    Type: SAE PAPER 912113
    Format: text
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  • 8
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    Laminar flow - The past, present, and prospects (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Flight research conducted on natural laminar flow (NLF) is discussed. Emphasis is on recent flight testing conducted by the National Aeronautics and Space Administration. To place these flight experiences in perspective, important flight tests from the early days of natural laminar flow research are first reviewed to recall the lessons learned at that time. Then, based on more recent flight experiences and analyses with state-of-the-art boundary layer stability theory, speculation is made on the possibility of extensive NLF on swept wing transport aircraft.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 89-0989
    Format: text
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  • 9
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    Energy efficient transport technology: Program summary and bibliography (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Energy Efficient Transport (EET) Program began in 1976 as an element of the NASA Aircraft Energy Efficiency (ACEE) Program. The EET Program and the results of various applications of advanced aerodynamics and active controls technology (ACT) as applicable to future subsonic transport aircraft are discussed. Advanced aerodynamics research areas included high aspect ratio supercritical wings, winglets, advanced high lift devices, natural laminar flow airfoils, hybrid laminar flow control, nacelle aerodynamic and inertial loads, propulsion/airframe integration (e.g., long duct nacelles) and wing and empennage surface coatings. In depth analytical/trade studies, numerous wind tunnel tests, and several flight tests were conducted. Improved computational methodology was also developed. The active control functions considered were maneuver load control, gust load alleviation, flutter mode control, angle of attack limiting, and pitch augmented stability. Current and advanced active control laws were synthesized and alternative control system architectures were developed and analyzed. Integrated application and fly by wire implementation of the active control functions were design requirements in one major subprogram. Additional EET research included interdisciplinary technology applications, integrated energy management, handling qualities investigations, reliability calculations, and economic evaluations related to fuel savings and cost of ownership of the selected improvements.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-RP-1135 , L-15921 , NAS 1.61:1135
    Format: application/pdf
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  • 10
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    Tabulated pressure measurements on an executive-type jet transport model with a supercritical wing (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A 1/9 scale model of an existing executive type jet transport refitted with a supercritical wing was tested on in the 8 foot transonic pressure tunnel. The supercritical wing had the same sweep as the original airplane wing but had maximum thickness chord ratios 33 percent larger at the mean geometric chord and almost 50 percent larger at the wing-fuselage juncture. Wing pressure distributions and fuselage pressure distributions in the vicinity of the left nacelle were measured at Mach numbers from 0.25 to 0.90 at angles of attack that generally varied from -2 deg to 10 deg. Results are presented in tabular form without analysis.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-72701 , NAS 1.15:X-72701
    Format: application/pdf
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