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  • 1
    ISSN: 1432-0878
    Keywords: Myocardium, mitochondria, calcium ; Cryo-ultramicrotomy-X-ray microanalysis ; Ultrahistochemistry ; Cardiac surgery
    Source: Springer Online Journal Archives 1860-2000
    Topics: Biology , Medicine
    Notes: Summary Mitochondria of normal myocardial cells of the sand rat and the mouse as well as of the left ventricle of man, have been examined for their content of calcium. Ultrahistochemistry and X-ray microanalysis revealed two basically different inclusions: Osmiophilic mitochondrial granules and Spherical mitochondrial particles. Osmiophilic mitochondrial granules were found in conventionally fixed and plastic embedded tissues as well as in cryosections of chemically fixed and sucrose infused tissues. Such granules lacked inert electron density and probably consisted mainly of unsaturated lipids. X-ray spectra obtained from these tissues revealed no peaks for calcium. Spherical mitochondrial particles were present in dry-cut cryo-sections of N2-frozen tissues not treated by fixatives and/or cryoprotectants. These particles were deeply electron dense in unstained, freeze-dried cryo-sections. They usually measured from 600Å–900Å in diameter in the normal myocardium of the sand rat and the mouse and from 250 Å–400Å in diameter in the left ventricular myocardium of man. Significant calcium peaks could be identified in the X-ray spectra of these particles, whereas none occurred in the analyses of other tissue regions. Potassium was detected with about equal frequency in the particles and in other parts of the tissue. On the basis of the inert electron density of the particles and their absence in chemically fixed tissues as well as of the results of the X-ray analysis, it is concluded that they contain precipitates of extremely labile ions of mitochondrial calcium.
    Type of Medium: Electronic Resource
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  • 2
    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 31; 10; p. 1744-1752.
    Format: text
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  • 3
    Publication Date: 2009-11-17
    Description: Prediction of steady and unsteady airloads on space shuttles
    Keywords: AERODYNAMICS
    Type: NASA. LEWIS RES. CENTER SPACE TRANSPORTATION SYSTEM TECHNOL. SYMP., VOL. 2 JUL. 1970; P 223-237
    Format: text
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  • 4
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    In:  CASI
    Publication Date: 2011-10-14
    Description: This test was initiated to provide validation data on low aspect ratio wings at transonic speeds. The test was conducted so that the data obtained would be useful in the validation of codes, and all boundary condition data required would be measured as part of the test. During the conduct of the test, the measured quantities were checked for repeatability, and when the data would not repeat, the cause was tracked down and either eliminated or included in the measurement uncertainty. The accuracy of the data was in the end limited by wall imperfections of the wind tunnel in which the test was run.
    Keywords: AERODYNAMICS
    Type: AGARD, A Selection of Experimental Test Cases for the Validation of CFD Codes, Volume 2; 11 p
    Format: text
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  • 5
    Publication Date: 2011-08-19
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 23; 650-656
    Format: text
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  • 6
    Publication Date: 2013-06-04
    Description: Evaluation of atmospheric density data obtained by inflatable falling spheres
    Keywords: AERODYNAMICS
    Type: NASA, WASHINGTON STATUS OF PASSIVE INFLATABLE FALLING-SPHERE TECHNOL. FOR ATMOSPHERIC SENSING TO 100 KM 1969; P 271-279
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  • 7
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    In:  Other Sources
    Publication Date: 2011-08-18
    Description: Noise emission from very small chord and very large chord airfoils was measured with eleven 0.63 cm microphones placed along a horizontal semicircle (4.57 m radius) that was centered at the leading edge of the test airfoil. The noise signals were analyzed by an automated spectrum analyzer which yielded 1/3-octave band sound pressure level spectra for each microphone, and the data were corrected to remove the effects of atmospheric attenuation and jet noise. It is found that the effect of thickness is large and must be accounted for in any fundamental airfoil noise theory that attempts to describe the noise emitted from real airfoils. Incident mean velocity gradients and compressibility must also be taken into account. The effect of thickness increases with frequency, with thick airfoils being quieter than thin ones.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 20; Mar. 198
    Format: text
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  • 8
    Publication Date: 2013-08-31
    Description: An investigation which was designed to provide insight into the fundamental aspects of fan rotor-downstream strut interaction was undertaken. High response, miniature pressure transducers were embedded in the rotor blades of an experimental fan rig. Five downstream struts were placed at several downstream locations in the discharge flow annulus of the single-stage machine. Significant interaction of the rotor blade surface pressures with the flow disturbance produced by the downstream struts was measured. Several numerical procedures for calculating the quasi-steady rotor response due to downstream flow obstructions were developed. A preliminary comparison of experimental and calculated fluctuating blade pressures on the rotor blades shows general agreement between the experimental and calculated values.
    Keywords: AERODYNAMICS
    Type: NASA-CR-175756 , NAS 1.26:175756 , IR-1
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  • 9
    Publication Date: 2016-06-07
    Description: Two theoretical methods are presented for optimizing multi-element airfoils to obtain maximum lift. The analyses assume that the shapes of the various high lift elements are fixed. The objective of the design procedures is then to determine the optimum location and/or deflection of the leading and trailing edge devices. The first analysis determines the optimum horizontal and vertical location and the deflection of a leading edge slat. The structure of the flow field is calculated by iteratively coupling potential flow and boundary layer analysis. This design procedure does not require that flow separation effects be modeled. The second analysis determines the slat and flap deflection required to maximize the lift of a three element airfoil. This approach requires that the effects of flow separation from one or more of the airfoil elements be taken into account. The theoretical results are in good agreement with results of a wind tunnel test used to corroborate the predicted optimum slat and flap positions.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Advanced Technol. Airfoil Res., Vol. 1, Pt.1; p 237-253
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  • 10
    Publication Date: 2019-05-23
    Description: Aerodynamic damping derivatives measured as function of instantaneous angular displacement and relationship to damping derivatives measured as function of oscillation amplitude
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-2855
    Format: application/pdf
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