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  • 1
    Electronic Resource
    Electronic Resource
    SBC Communications' process for strategic and portfolio planning (2003)
    London : Emerald
    Journal ofcorporate real estate 5 (2003), S. 126-142 
    Details
    ISSN: 1463-001X
    Source: Emerald Fulltext Archive Database 1994-2005
    Topics: Economics
    Notes: This paper presents the process and outcomes of developing a national capability for strategic and portfolio planning within SBC Communications, Inc., a Fortune 100 company, and reviews the progress made and lessons learned since this initiative was implemented in October 2001. At this time SBC Corporate Real Estate standardised the planning approach used by its regionalised staff in order to achieve consistent business practices. This multidisciplinary effort involved process design, development of tools and templates, training and deployment, facilitation and mentoring, production of prototype plans, and ongoing coaching during implementation in 2002. The new approach, featuring scenario planning and economic modelling, has elevated planning services to an advisory level by emphasising shareholder value while satisfying business unit needs. Within the first year of implementation, the process has been fully endorsed by corporate leadership and adopted by business unit management. Refinements to the planning approach and enhancements to the methodology are being incorporated on an ongoing basis as part of a continuous improvement programme.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1108/14630010310812064
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    Paper (German National Licenses)
    Fulltext
  • 2
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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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    NASA TECHNICAL REPORTS
  • 3
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    Application of advanced technologies to future military transports (1990)
    In:  CASI
    Details
    Publication Date: 2013-08-29
    Description: Long range military transport technologies are addressed with emphasis of defining the potential benefits of the hybrid laminar flow control (HLFC) concept currently being flight tested. Results of a 1990's global range transport study are presented showing the expected payoff from application of advanced technologies. Technology forecast for military transports is also presented.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: AGARD, Progress in Military Airlift; 8 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Performance of laminar-flow leading-edge test articles in cloud encounters (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: An extensive data bank of concurrent measurements of laminar flow (LF), particle concentration, and aircraft charging state was gathered for the first time. From this data bank, 13 flights in the simulated airline service (SAS) portion were analyzed to date. A total of 6.86 hours of data at one-second resolution were analyzed. An extensive statistical analysis, for both leading-edge test articles, shows that there is a significant effect of cloud and haze particles on the extent of laminar flow obtained. Approximately 93 percent of data points simulating LFC flight were obtained in clear air conditions; approximately 7 percent were obtained in cloud and haze. These percentages are consistent with earlier USAF and NASA estimates and results. The Hall laminar flow loss criteria was verified qualitatively. Larger particles and higher particle concentrations have a more marked effect on LF than do small particles. A particle spectrometer of a charging patch are both acceptable as diagnostic indicators of the presence of particles detrimental to laminar flow.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Research in Natural Laminar Flow and Laminar-Flow Control, Part 1; p 163-193
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Operational considerations for laminar flow aircraft (1986)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Considerable progress has been made in the development of laminar flow technology for commercial transports during the NASA Aircraft Energy Efficiency (ACEE) laminar flow program. Practical, operational laminar flow control (LFC) systems have been designed, fabricated, and are undergoing flight testing. New materials, fabrication methods, analysis techniques, and design concepts were developed and show much promise. The laminar flow control systems now being flight tested on the NASA Jetstar aircraft are complemented by natural laminar flow flight tests to be accomplished with the F-14 variable-sweep transition flight experiment. An overview of some operational aspects of this exciting program is given.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Laminar Flow Aircraft Certification; p 247-268
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Laminar flow control is maturing (1988)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Recent research demonstrates that laminar flow (LF) can be reliable in flight and that the support system need not be complex. Shaping produces favorable pressure gradients for maintaining natural laminar flow (NLF), and laminar flow control (LFC) techniques such as full chord suction promise a fuel-saving payoff of up to 30 percent on long-range missions. For large aircraft, current research is concentrated on hybrid LFC concepts which combine suction and pressure-gradient control. At NASA Ames, an F-14 with variable wing sweep has been flight tested with smooth surface gloves on the wings; preliminary results indicate high transition Reynolds numbers to sweep angles as large as 25 deg. In addition, a 757 was flight tested with an NLF glove on the right wing just outboard of the engine pylon; and the LF was found to be suprisingly robust.
    Keywords: AERODYNAMICS
    Type: Aerospace America (ISSN 0740-722X); 26; 20
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Some Aspects of the Modified Newtonian and Prandtl-Meyer-Expansion Method for Axisymmetric Blunt Bodies at Zero Angle of Attack (1959)
    In:  Other Sources
    Details
    Publication Date: 2018-06-05
    Description: In a recent article on hypersonic flow, Lees and Kubota suggested a modification of the local-expansion method to predict the surface pressures in the region of a nose-cylinder junction where Newtonian theory fails. The modification consists of matching the Newtonian pressure distribution and the Prandtl-Meyer relation at the point on the nose surface where both the pressure and the pressure gradient, predicted by these two solution, are equal. With this approximation, the pressure distribution can be predicted quite accurately up to the nose-cylinder junction for blunt-nosed bodies of continuous curvature, provided centrifugal-force effects are negligible. The purpose of this note is to facilitate the application of Lees' suggestion and to draw attention to some of its consequences.
    Keywords: Aerodynamics; Fluid Mechanics and Thermodynamics
    Type: Journal of Aerospace Sciences; Volume 26; No. 12
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Design of a hybrid laminar flow control nacelle (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Consideration is given to the potential application of hybrid-laminar-flow control to the external surface of a modern, high-bypass-ratio (HBR) turbofan engine nacelle. With the advent of advanced ultra-HBR fans (with bypass ratios of 10-15), the wetted areas of these nacelles approach 10 percent of the total wetted area of future commercial transports. A hybrid-laminar-flow-control pressure distribution is specified and the corresponding nacelle geometry is computed utilizing a predictor/corrector design method. Linear stability calculations are conducted to provide predictions of the extent of the laminar boundary layer. Performance studies on an advanced twin-engine transport configuration are presented to determine potential benefits in terms of reduced fuel consumption.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 92-0400
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Evaluation of cloud detection instruments and performance of laminar-flow leading-edge test articles during NASA Leading-Edge Flight-Test Program (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Summary evaluations of the performance of laminar-flow control (LFC) leading edge test articles on a NASA JetStar aircraft are presented. Statistics, presented for the test articles' performance in haze and cloud situations, as well as in clear air, show a significant effect of cloud particle concentrations on the extent of laminar flow. The cloud particle environment was monitored by two instruments, a cloud particle spectrometer (Knollenberg probe) and a charging patch. Both instruments are evaluated as diagnostic aids for avoiding laminar-flow detrimental particle concentrations in future LFC aircraft operations. The data base covers 19 flights in the simulated airline service phase of the NASA Leading-Edge Flight-Test (LEFT) Program.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TP-2888 , L-16509 , NAS 1.60:2888
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Laminar Heat-Transfer and Pressure-Distribution Studies on a Series of Reentry Nose Shapes at a Mach Number of 19.4 in Helium (1961)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: An experimental investigation has been conducted in the 2-inch helium tunnel at the Langley Research Center at a Mach number of 19.4 to determine the pressure distributions and heat-transfer characteristics of a family of reentry nose shapes. The pressure and heat-transfer-rate distributions on the nose shapes are compared with theoretical predictions to ascertain the limitations and validity of the theories at hypersonic speeds. The experimental results were found to be adequately predicted by existing theories. Two of the nose shapes were tested with variable-length flow-separation spikes. The results obtained by previous investigators of spike-nose bodies were found to prevail at the higher Mach number of the present investigation.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: NASA-TN-D-891 , L-1345
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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