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  • AERODYNAMICS  (671)
  • Engineering General  (536)
  • 105-647A; 12-112; Deep Sea Drilling Project; DRILL; Drilling/drill rig; DSDP; Glomar Challenger; Joides Resolution; Leg105; Leg12; North Atlantic; Ocean Drilling Program; ODP; South Atlantic Ocean
  • 1985-1989  (1,209)
  • 1989  (1,209)
Collection
Keywords
Publisher
Years
  • 1985-1989  (1,209)
Year
  • 1
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    Eocene-Oligocene nannofossils from the Labrador Sea (1989)
    PANGAEA
    In:  Supplement to: Firth, John V (1989): Eocene and Oligocene calcareous nannofossils from the Labrador Sea, ODP Leg 105. In: Srivastava, SP; Arthur, M; Clement, B; et al. (eds.), Proceedings of the Ocean Drilling Program, Scientific Results, College Station, TX (Ocean Drilling Program), 105, 263-286, https://doi.org/10.2973/odp.proc.sr.105.131.1989
    Details
    Publication Date: 2024-01-09
    Description: During Ocean Drilling Program (ODP) Leg 105, a thick sequence of lower Eocene to lower Oligocene sediments was recovered from Hole 647A in the southern Labrador Sea. These sediments contain diverse, well-preserved, high-latitude calcareous nannofossil flora. The nannofossil biostratigraphy of the hole indicates the presence of a minor hiatus between Zones NP 16 and NP 17 in the upper middle Eocene and a barren interval separating Zones NP 13 and NP 15. Species abundance is highest within the lower to middle Eocene and starts to decline near the base of the upper Eocene. No major change in the nannoflora was observed across the Eocene/Oligocene boundary, although a slight decrease in species abundance was recorded. The Paleogene calcareous nannofossils of nearby DSDP Site 112 were reexamined and compared with those of Site 647. Several cores were reassigned to different nannofossil zones. The calcareous nannoflora are dominated by high-latitude indicative species and also exhibit a high diversity, which suggests the influence of more temperate water masses in this region during Eocene and Oligocene time. One new subspecies from the middle Eocene, Sphenolithus furcatolithoides labradorensis, is described.
    Keywords: 105-647A; 12-112; Deep Sea Drilling Project; DRILL; Drilling/drill rig; DSDP; Glomar Challenger; Joides Resolution; Leg105; Leg12; North Atlantic; Ocean Drilling Program; ODP; South Atlantic Ocean
    Type: Dataset
    Format: application/zip, 5 datasets
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    DATA PANGAEA
  • 2
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    Oligocene diatom biostratigraphy for the Labrador Sea (1989)
    PANGAEA
    In:  Supplement to: Baldauf, Jack G; Monjanel, Anne-Lise (1989): An Oligocene diatom biostratigraphy for the Labrador Sea: DSDP Site 112 and ODP Hole 647A. In: Srivastava, SP; Arthur, M; Clement, B; et al. (eds.), Proceedings of the Ocean Drilling Program, Scientific Results, College Station, TX (Ocean Drilling Program), 105, 323-347, https://doi.org/10.2973/odp.proc.sr.105.129.1989
    Details
    Publication Date: 2024-01-09
    Description: The Oligocene diatom assemblage observed in samples from Hole 647A consists of a mixture of species characteristic of the low latitudes, the high southern latitudes, and the Norwegian-Greenland Sea. This diverse and well-preserved diatom assemblage allows a diatom stratigraphy to be established for the Labrador Sea and to be correlated with previously established diatom zonations. Changes in the composition of the diatom assemblage from warm-temperate to temperate species suggest a change in oceanographic conditions in the Labrador Sea during the early Oligocene.
    Keywords: 105-647A; 12-112; Deep Sea Drilling Project; DRILL; Drilling/drill rig; DSDP; Glomar Challenger; Joides Resolution; Leg105; Leg12; North Atlantic; Ocean Drilling Program; ODP; South Atlantic Ocean
    Type: Dataset
    Format: application/zip, 2 datasets
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    DATA PANGAEA
  • 3
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    High-alpha aerodynamic characteristics of crescent and elliptic wings (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-08-27
    Description: Static longitudinal and lateral-directional forces and moments were measured for elliptic- and crescent-wing models at high angles of attack in the NASA Langley 14-by-22-ft Subsonic Tunnel. The forces and moments were obtained for an angle-of-attack range including stall and post-stall conditions at a Reynolds number based on the average wing chord of about 1.8 million. Flow-visualization photographs using a mixture of oil and titanium-dioxide were also taken for several incidence angles. The force and moment data and the flow-visualization results indicated that the crescent wing model with its highly swept tips produced much better high-angle-of-attack aerodynamic characteristics than the elliptic model. Leading-edge separation-induced vortex flow over the highly swept tips of the crescent wing is thought to produce this improved behavior at high angles of attack. The unique planform design could result in safer and more efficient low-speed airplanes.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 89-2240 , AIAA Applied Aerodynamics Conference; Jul 31, 1989 - Aug 02, 1989; Seattle, WA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    NASA's CFD Validation Program (1989)
    In:  CASI
    Details
    Publication Date: 2019-08-27
    Description: With computational fluid dynamics (CFD) becoming a productive research and design tool, the requirement to validate CFD codes has grown significantly. NASA had emphasized CFD validation activities since 1986 when a separate work element was formed to fund experimental activities related to validation. NASA's CFD and CFD validation programs are closely coordinated to ensure that experimental data bases are available as soon as possible for validating codes. In response to industry and academic requirements, four levels of experimental research have been defined as part of CFD validation with NASA's Aeronautics Advisory Committee (AAC) support although only the fourth level actually has the detailed information necessary for validating codes. Critical flow physics especially turbulence modeling are key to improved CFD codes. NASA has focused additional resources on transition and turbulence physics to meet these requirements. With improved turbulence models, CFD codes will be more accurate, robust, and efficient. However, with the level of detailed information available from CFD codes, highly accurate and detailed experiments are required to capture the critical information for validating codes. Advanced instrumentation especially non-intrusive instrumentation is required to acquire this information in validation experiments. The CFD validation program is being coordinated and managed to address these critical activities. A list of experiments which are currently being supported at least partially are included.
    Keywords: AERODYNAMICS
    Type: NASA, Ames Research Center, NASA Computational Fluid Dynamics Conference. Volume 1: Sessions 1-6; p 123-134
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Transonic Symposium: Theory, Application, and Experiment, volume 1, part 2 (1989)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: In order to assess the state of the art in transonic flow disciplines and to glimpse at future directions, NASA-Langley held a Transonic Symposium. Emphasis was placed on steady, three dimensional external, transonic flow and its simulation, both numerically and experimentally. The symposium included technical sessions on wind tunnel and flight experiments; computational fluid dynamic applications; inviscid methods and grid generation; viscous methods and boundary layer stability; and wind tunnel techniques and wall interference. This, being volume 1, is unclassified.
    Keywords: AERODYNAMICS
    Type: NASA-CP-3020-VOL-1-PT-2 , L-16501-VOL-1-PT-2 , NAS 1.55:3020-VOL-1-PT-2 , Apr 19, 1988 - Apr 21, 1988; Hampton, VA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Transonic Symposium: Theory, Application, and Experiment, Volume 1, Part 1 (1989)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: Topics addressed include: wind tunnel and flight experiments; computational fluid dynamics (CFD) applications, industry overviews; and inviscid methods and grid generations.
    Keywords: AERODYNAMICS
    Type: NASA-CP-3020-VOL-1-PT-1 , L-16501-VOL-1-PT-1 , NAS 1.55:3020-VOL-1-PT-1 , Apr 19, 1988 - Apr 21, 1988; Hampton, VA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Numerical study of a delta planform with multiple jets in ground effect (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: The flow past a 60-deg delta wing equipped with two thrust-reverser jets near the inboard trailing edge has been analyzed by numerical solution of the 3D thin-layer Navier-Stokes equations. An implicit, partially flux-split, approximately-factored Navier-Stokes solver coupled with a multiple grid embedding scheme has been adapted to this problem. Studies of the impact of numerical parameters (e.g., grid refinement and dissipation levels), and flow-field parameters such as the height of the delta wing above the ground plane and the jet size on the solution, were performed. Results of these numerical studies indicate some challenges in the accurate resolution of complex 3D free shear layers and jets. Nevertheless, flow features such as jet deformation and ground vortex formation observed in experimental flow visualizations are captured. Further, comparisons with experimental data confirm the ability to simulate the loss of wing-borne lift, commonly referred to 'suckdown, as the delta planform flies at slow speeds in close proximity to the ground. Detailed analysis of the numerical results has also given additional insight into the structure of the ground vortex and the mechanisms of lift loss.
    Keywords: AERODYNAMICS
    Type: SAE PAPER 892283 , ; 15 p.|SAE, Aerospace Technology Conference and Exposition; Sept. 25-28, 1989; Anaheim, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Prediction of transitional (laminar-turbulent) hypersonic flows using the parabolized Navier-Stokes equations (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: Hypersonic transitional flow predictions have been made using the parabolized Navier-Stokes equations with an algebraic transition/turbulence model by appropriately modulating the turbulent viscosity with the available intermittency functions for incompressible and compressible flows. A comparison between the predictions with and without a low Reynolds number correction has also been made. The predictions are compared with the available experimental data and with the theory over a range of Mach number. A simple Re(theta)/M(delta) criterion is shown to satisfactorily predict the meridional variation of the onset location of transition on a cone at a small angle of attack, whereas none of the correlations discussed can do that. Various available correlations are discussed vis-a-vis the predictions as to the locations of the onset and the end of transition.
    Keywords: AERODYNAMICS
    Type: International Conference on Hypersonic Aerodynamics; Sept. 4-6, 1989; Manchester
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    On hypersonic shock layer and its extension beyond the Navier-Stokes level (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: An extension of the continuum model beyond the Navier-Stokes (NS) level and related issues on problem formulation are examined for a hypersonic shock layer on the basis of Grad's thirteen-moment equations for a Maxwell gas. The 13-moment system, simplified consistently with a fully viscous version of the thin shock-layer approximation, permits correlation with the corresponding NS-based solution. With the exception of pressure and density, several flow properties including normal stress, shear stress and normal heat flux along a streamline are unaffected by translational nonequilibrium and are therefore predicted correctly by the NS solution to the leading order, even in a domain far from translational equilibrium where molecular-transport processes rank equally with the convection.
    Keywords: AERODYNAMICS
    Type: International Conference on Hypersonic Aerodynamics; Sept. 4-6, 1989; Manchester
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    NASA TECHNICAL REPORTS
  • 10
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    2-D and 3-D mixing flow analyses of a scramjet-afterbody configuration (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-07-27
    Description: A cold simulant gas study of propulsion/airframe integration for a hypersonic vehicle powered by a scramjet engine is presented. The specific heat ratio of the hot exhaust gases are matched by utilizing a cold mixture of argon and Freon-12. Solutions are obtained for a hypersonic corner flow and a supersonic rectangular flow in order to provide the upstream boundary conditions. The computational test examples also provide a comparison of this flow with that of air as the expanding supersonic jet, where the specific heats are assumed to be constant. It is shown that the three-dimensional computational fluid capabilities developed for these types of flow may be utilized to augment the conventional wind tunnel studies of scramjet afterbody flows using cold simulant exhaust gases, which in turn can help in the design of a scramjet internal-external nozzle.
    Keywords: AERODYNAMICS
    Type: International Conference on Hypersonic Aerodynamics; Sept. 4-6, 1989; Manchester
    Format: text
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    NASA TECHNICAL REPORTS
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