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  • AIRCRAFT PROPULSION AND POWER  (5)
  • Air-breathing  (1)
  • 1
    ISSN: 1432-136X
    Keywords: Key words Oxygen ; Acid-base ; Adenylates ; Cherax ; Air-breathing
    Source: Springer Online Journal Archives 1860-2000
    Topics: Biology , Medicine
    Notes: Abstract The Australian Yabby Cherax destructor voluntarily emerges from water to breathe air with increased frequency as water PO2 decreases. When the water PO2 declined below 2.7 kPa the crayfish spent 〉50% of time breathing air. The respiratory gas transport, acid-base, ionic and energetic status were quantified in simulations of this emersion behaviour to determine the benefits that the crayfish may gain from switching to air-breathing. C. destructor initially showed an elevated O2 uptake rate on emerging from hypoxic water, but after 1 h the O2 uptake rate was not different from that of crayfish in normoxic water. During 3 h of air breathing, subsequent to 2.7 kPa aquatic hypoxia, the haemolymph PO2 increased while oxygen content was essentially unchanged, although cardiac output increased 5-fold. The haemolymph PCO2 increased from 0.44 to 1.21 kPa after 3 h while the CO2 content increased from 3.47 to 8.66 mmol · l−1 and the pH decreased from 7.73 to 7.57 after 1 h in air. In air C. destructor eventually achieved an O2 uptake rate similar to that achieved in water. A general hyperglycaemia occurred without anaerobiosis. In air-breathing C. destructor, small changes in lactate appear to offset the decrease in haemocyanin-O2 affinity caused by acid Bohr shift. During air-breathing, decreased haemocyanin-O2 affinity assisted in maintaining O2 diffusion into the tissues, but the ATP content of the tail muscle decreased so that after 3 h in air the energy charge was only 0.59. The data are consistent with a specific depression of the Emden-Meyerhof pathway, preventing either lactate formation or oxidative phosphorylation in the tail muscle, despite a concomitant glycogenolysis.
    Type of Medium: Electronic Resource
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  • 2
    Publication Date: 2017-10-02
    Description: Propulsion systems are evaluated in terms of relative aircraft range for a fixed payload and takeoff gross weight with a design cruise Mach number of 2.7. In order to put the performance of these engines in perspective, a comparison of these engines and the former U.S. SST engine is made with an idealized variable cycle engine whose performance at all operating points matches that of an optimized point design cycle within specified limits. Range comparisons are made with and without noise level constraints to determine the influence of noise upon cycle selection. The critical areas requiring new or improved technology for each cycle are delineated.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AGARD Variable Geometry and Multicycle Eng.; 19 p
    Format: text
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  • 3
    Publication Date: 2019-06-27
    Description: Performance estimations, weights, and scaling laws for the six blade and ten blade highly loaded propellers combined with an advanced turboshaft engine are presented. These data are useful for aircraft mission studies using the turboprop system. Comparisons are made between the performance of post 1980 technology turboprop propulsion systems and the performance of both a current technology turbofan and a post 1990 technology turbofan.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-81840
    Format: application/pdf
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  • 4
    Publication Date: 2019-06-27
    Description: The rapid computer program is designed to be run in a stand-alone mode or operated within a larger program. The computation is based on a simplified one-dimensional gas turbine cycle. Each component in the engine is modeled thermo-dynamically. The component efficiencies used in the thermodynamic modeling are scaled for the off-design conditions from input design point values using empirical trends which are included in the computer code. The engine cycle program is capable of producing reasonable engine performance prediction with a minimum of computer execute time. The current computer execute time on the IBM 360/67 for one Mach number, one altitude, and one power setting is about 0.1 seconds. about 0.1 seconds. The principal assumption used in the calculation is that the compressor is operated along a line of maximum adiabatic efficiency on the compressor map. The fluid properties are computed for the combustion mixture, but dissociation is not included. The procedure included in the program is only for the combustion of JP-4, methane, or hydrogen.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-78653
    Format: application/pdf
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  • 5
    Publication Date: 2019-06-27
    Description: Performance estimation, weights, and scaling laws for an eight-blade highly loaded propeller combined with an advanced turboshaft engine are presented. The data are useful for planned aircraft mission studies using the turboprop propulsion system. Comparisons are made between the performance of the 1990+ technology turboprop propulsion system and the performance of both a current technology turbofan and an 1990+ technology turbofan.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-80075
    Format: application/pdf
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  • 6
    Publication Date: 2019-06-27
    Description: Three proposed SCAR propulsion systems in terms of aircraft range for a fixed payload and take-off gross weight with a design cruise Mach number 2.7 are evaluated. The effects of various noise and operational restraints are determined and sensitivities to some of the more important performance variables are presented for the most probable design noise and operational restraint case. Critical areas requiring new or improved technology for each cycle are delineated.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-73977
    Format: application/pdf
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