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  • 1
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    The purpose of glycolysis (1997)
    American Association for the Advancement of Science (AAAS)
    Details
    Publication Date: 1997-07-25
    Description: 〈br /〉〈span class="detail_caption"〉Notes: 〈/span〉Sparks, S -- New York, N.Y. -- Science. 1997 Jul 25;277(5325):459-60.〈br /〉〈span class="detail_caption"〉Record origin:〈/span〉 〈a href="http://www.ncbi.nlm.nih.gov/pubmed/9254411" target="_blank"〉PubMed〈/a〉
    Keywords: Alanine/metabolism ; Animals ; Brain/*metabolism ; Cerebrovascular Circulation ; Cytosol/metabolism ; *Glycolysis ; Humans ; Lactic Acid/metabolism ; Neurons/*metabolism ; Oxidation-Reduction ; Oxygen Consumption ; Pyruvic Acid/metabolism
    Print ISSN: 0036-8075
    Electronic ISSN: 1095-9203
    Topics: Biology , Chemistry and Pharmacology , Computer Science , Medicine , Natural Sciences in General , Physics
    Published by American Association for the Advancement of Science (AAAS)
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    PAPER CURRENT
  • 2
    Electronic Resource
    Electronic Resource
    Ecdysteroids during embryogenesis of the house cricket, Acheta domesticus: Occurrence of novel ecdysteroid conjugates in developing eggs
    Amsterdam : Elsevier
    Insect Biochemistry and Molecular Biology 23 (1993), S. 319-329 
    Details
    ISSN: 0965-1748
    Keywords: 20-Hydroxyecoysone ; Ecoysone ; High-performance liquid chromatography ; Radioimmunoassay ; Steroid hormones
    Source: Elsevier Journal Backfiles on ScienceDirect 1907 - 2002
    Topics: Biology
    Type of Medium: Electronic Resource
    URL: http://linkinghub.elsevier.com/retrieve/pii/0965-1748(93)90015-K
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    Paper (German National Licenses)
    Fulltext
  • 3
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    A full potential flow analysis with realistic wake influence for helicopter rotor airload prediction (1987)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A 3-D, quasi-steady, full potential flow solver was adapted to include realistic wake influence for the aerodynamic analysis of helicopter rotors. The method is based on a finite difference solution of the full potential equation, using an inner and outer domain procedure for the blade flowfield to accommodate wake effects. The nonlinear flow is computed in the inner domain region using a finite difference solution method. The wake is modeled by a vortex lattice using prescribed geometry techniques to allow for the inclusion of realistic rotor wakes. The key feature of the analysis is that vortices contained within the finite difference mesh (inner domain) were treated with a vortex embedding technique while the influence of the remaining portion of the wake (in the outer domain) is impressed as a boundary condition on the outer surface of the finite difference mesh. The solution procedure couples the wake influence with the inner domain solution in a consistent and efficient solution process. The method has been applied to both hover and forward flight conditions. Correlation with subsonic and transonic hover airload data is shown which demonstrates the merits of the approach.
    Keywords: AERONAUTICS (GENERAL)
    Type: NASA-CR-4007 , NAS 1.26:4007 , R86-915999-13
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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