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  • Cell & Developmental Biology  (25,032)
  • AERODYNAMICS  (12,790)
  • Sperm whales
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  • 1
    Publication Date: 2022-05-25
    Description: © The Author(s), 2017. This article is distributed under the terms of the Creative Commons Attribution License. The definitive version was published in Ecotoxicology 26 (2017): 820-830, doi:10.1007/s10646-017-1813-4.
    Description: Mathematical models are essential for combining data from multiple sources to quantify population endpoints. This is especially true for species, such as marine mammals, for which data on vital rates are difficult to obtain. Since the effects of an environmental disaster are not fixed, we develop time-varying (nonautonomous) matrix population models that account for the eventual recovery of the environment to the pre-disaster state. We use these models to investigate how lethal and sublethal impacts (in the form of reductions in the survival and fecundity, respectively) affect the population’s recovery process. We explore two scenarios of the environmental recovery process and include the effect of demographic stochasticity. Our results provide insights into the relationship between the magnitude of the disaster, the duration of the disaster, and the probability that the population recovers to pre-disaster levels or a biologically relevant threshold level. To illustrate this modeling methodology, we provide an application to a sperm whale population. This application was motivated by the 2010 Deepwater Horizon oil rig explosion in the Gulf of Mexico that has impacted a wide variety of species populations including oysters, fish, corals, and whales.
    Description: This research is part of the Littoral Acoustic Demonstration Center-Gulf Ecological Monitoring and Modeling (LADC-GEMM) consortium project supported by Gulf of Mexico Research Initiative Year 5–7 Consortia Grants (RFP-IV). Hal Caswell also acknowledges support from ERC Advanced Grant 322989.
    Keywords: Population recovery ; Environmental disasters ; Stochastic modeling ; Lethal impact ; Sublethal impact ; Sperm whales
    Repository Name: Woods Hole Open Access Server
    Type: Article
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  • 2
    Publication Date: 2019-08-28
    Description: Statistical mechanics for wall shear turbulence in Couette flow based on Brownian motion and comparison with stochastic theory based on Navier-Stokes equation
    Keywords: AERODYNAMICS
    Type: NASA-SP-4014
    Format: application/pdf
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  • 3
    Publication Date: 2019-08-28
    Description: Annotated bibliography and indexes on aeronautical engineering and aerodynamics - July 1971
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(07)
    Format: application/pdf
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  • 4
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    In:  CASI
    Publication Date: 2019-08-28
    Description: Analyses of aircraft aerodynamic characteristics
    Keywords: AERODYNAMICS
    Type: NASA-SP-228 , A Symposium Held at Ames Research Center; Oct 28, 1969 - Oct 30, 1969; MOFFETT FIELD, CA; United States
    Format: application/pdf
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  • 5
    Publication Date: 2019-08-28
    Description: Annotated reference bibliography on aeronautical engineering documents
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(01)
    Format: application/pdf
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  • 6
    Publication Date: 2019-08-28
    Description: Review of steps taken by nasa toward landing a man on the moon
    Keywords: AERODYNAMICS
    Type: Advancees in the Astronautical Sciences: Manned Lunar Flight; 10; 11-20
    Format: text
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  • 7
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    In:  CASI
    Publication Date: 2019-08-28
    Description: Annotated bibliography and indexes on aeronautical engineering and aerodynamics - Jan. 1971
    Keywords: AERODYNAMICS
    Type: NASA-SP-7037(02)
    Format: application/pdf
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  • 8
    Publication Date: 2019-08-28
    Description: The use of the External propulsion Accelerator (EPA) for launching models of hypersonic aerodynamic configurations into an instrumented ballistic range is discussed. The aerodynamic model is encased inside an axisymmetric projectile designed to be accelerated to high speed in the EPA. Accelerator lengths required to achieve hypersonic speeds are estimated to vary from 10 meters for Mach 7, 40 meters for Mach 10, 150 meters for Mach 15, and 700 meters for Mach 30, assuming a limit of 50,000 g's acceleration. For a model span of 10 cm to 25 cm, the launch tube diameters are 40 cm and 100 cm, respectively. Using this EPA launcher will enable exact simulation of hypersonic flight in ground facilities where both the gas composition and pressure can be controlled in the ballistic range.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 95-6138 , AIAA, Aerospace Planes and Hypersonics Technologies Conference; Apr 03, 1995 - Apr 07, 1995; Chattanooga, TN; United States|; 5 p.
    Format: text
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  • 9
    Publication Date: 2019-08-28
    Description: NASA is directing research to develop technology for a high-speed civil transport. Supersonic laminar flow control has been identified as a program element, since it offers significant drag-reduction benefits and is one of the more promising technologies for producing an economically viable aircraft design. NASA is using two prototype F-16XL aircraft to research supersonic laminar flow control. The F-16XL planform is similar to design planforms of high-speed civil transports. The planform makes the aircraft ideally suited for developing technology pertinent to high-speed transports. The supersonic laminar flow control research programs for both aircraft are described. Some general results of the ship-1 program demonstrate that significant laminar flow was obtained using laminar flow control on a highly swept wing at supersonic speeds.
    Keywords: AERODYNAMICS
    Type: SAE PAPER 921994 , ; 14 p.|SAE, Aerotech ''92 Conference; Oct 05, 1992 - Oct 08, 1992; Anaheim, CA; United States
    Format: text
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  • 10
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    In:  Other Sources
    Publication Date: 2019-08-28
    Description: Issues and advances in current hypersonic flow research perceived to be of interest in theoretical fluid/gas dynamics are reviewed. Particular attention is given to the hypersonic aircraft as waverider, computational methods and theoretical development in the study of viscous interaction, and boundary-layer instability and transition studies. In the present framework the study of viscous hypersonic flow faces transition problems of two kinds which represent the two major areas of current research: the turbulence transition in the high Re range and the transition to the free-molecule limit.
    Keywords: AERODYNAMICS
    Type: In: Annual review of fluid mechanics. Vol. 25 (A94-10885 01-34); p. 455-484.
    Format: text
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