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  • AERODYNAMICS
  • Chemical Engineering
  • LUNAR AND PLANETARY EXPLORATION
  • 2005-2009  (2)
  • 1950-1954  (16)
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  • 1
    Publication Date: 2007-11-17
    Description: Artificial biochemical circuits are likely to play as large a role in biological engineering as electrical circuits have played in the engineering of electromechanical devices. Toward that end, nucleic acids provide a designable substrate for the regulation of biochemical reactions. However, it has been difficult to incorporate signal amplification components. We introduce a design strategy that allows a specified input oligonucleotide to catalyze the release of a specified output oligonucleotide, which in turn can serve as a catalyst for other reactions. This reaction, which is driven forward by the configurational entropy of the released molecule, provides an amplifying circuit element that is simple, fast, modular, composable, and robust. We have constructed and characterized several circuits that amplify nucleic acid signals, including a feedforward cascade with quadratic kinetics and a positive feedback circuit with exponential growth kinetics.〈br /〉〈span class="detail_caption"〉Notes: 〈/span〉Zhang, David Yu -- Turberfield, Andrew J -- Yurke, Bernard -- Winfree, Erik -- New York, N.Y. -- Science. 2007 Nov 16;318(5853):1121-5.〈br /〉〈span class="detail_caption"〉Author address: 〈/span〉Computation and Neural Systems, California Institute of Technology, MC 136-93, 1200 East California Boulevard, Pasadena, CA91125, USA. dzhang@dna.caltech.edu〈br /〉〈span class="detail_caption"〉Record origin:〈/span〉 〈a href="http://www.ncbi.nlm.nih.gov/pubmed/18006742" target="_blank"〉PubMed〈/a〉
    Keywords: Animals ; Catalysis ; Chemical Engineering ; *Computers, Molecular ; DNA/*chemistry ; Entropy ; Equipment Design ; Feedback, Physiological ; Mice ; Nanotechnology ; Nucleic Acid Hybridization ; Rabbits
    Print ISSN: 0036-8075
    Electronic ISSN: 1095-9203
    Topics: Biology , Chemistry and Pharmacology , Computer Science , Medicine , Natural Sciences in General , Physics
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  • 2
    Keywords: Biomass conversion ; Biotechnology ; Chemical Engineering ; Chemistry industry ; Industrial Chemistry ; Kent ; Riegel ; biochemical engineering
    Description / Table of Contents: Substantially revising and updating the classic reference in the field, this handbook offers a valuable overview and myriad details on current chemical processes, products, and practices. No other source offers as much data on the chemistry, engineering, economics, and infrastructure of the industry. The Handbook serves a spectrum of individuals, from those who are directly involved in the chemical industry to others in related industries and activities. It provides not only the underlying science and technology for important industry sectors, but also broad coverage of critical supporting topics. Industrial processes and products can be much enhanced through observing the tenets and applying the methodologies found in chapters on Green Engineering and Chemistry (specifically, biomass conversion), Practical Catalysis, and Environmental Measurements; as well as expanded treatment of Safety, chemistry plant security, and Emergency Preparedness. Understanding these factors allows them to be part of the total process and helps achieve optimum results in, for example, process development, review, and modification. Important topics in the energy field, namely nuclear, coal, natural gas, and petroleum, are covered in individual chapters. Other new chapters include energy conversion, energy storage, emerging nanoscience and technology. Updated sections include more material on biomass conversion, as well as three chapters covering biotechnology topics, namely, Industrial Biotechnology, Industrial Enzymes, and Industrial Production of Therapeutic Proteins.
    Pages: Online-Ressource (XIV, 1562 pages)
    ISBN: 9780387278438
    Language: English
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  • 3
    Publication Date: 2019-06-28
    Keywords: AERODYNAMICS
    Type: NACA-TN-3283
    Format: application/pdf
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  • 4
    Publication Date: 2019-06-28
    Description: The effects of primary and runback ice formations on the section drag of a 36 deg swept NACA 63A-009 airfoil section with a partial-span leading-edge slat were studied over a range of angles of attack from 2 to 8 deg and airspeeds up to 260 miles per hour for icing conditions with liquid-water contents ranging from 0.39 to 1.23 grams per cubic meter and datum air temperatures from 10 to 25 F. The results with slat retracted showed that glaze-ice formations caused large and rapid increases in section drag coefficient and that the rate of change in section drag coefficient for the swept 63A-009 airfoil was about 2-1 times that for an unswept 651-212 airfoil. Removal of the primary ice formations by cyclic de-icing caused the drag to return almost to the bare-airfoil drag value. A comprehensive study of the slat icing and de-icing characteristics was prevented by limitations of the heating system and wake interference caused by the slat tracks and hot-gas supply duct to the slat. In general, the studies showed that icing on a thin swept airfoil will result in more detrimental aerodynamic characteristics than on a thick unswept airfoil.
    Keywords: AERODYNAMICS
    Type: NACA-RM-E53J30
    Format: application/pdf
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  • 5
    Publication Date: 2019-06-27
    Keywords: AERODYNAMICS
    Type: NASA-TM-79864 , NACA-TN-3062
    Format: application/pdf
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  • 6
    Publication Date: 2019-06-27
    Keywords: AERODYNAMICS
    Type: NASA-TM-79844 , NACA-TR-1198 , NACA-TN-3018
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  • 7
    Publication Date: 2019-05-29
    Description: Conference on aerodynamics of high speed aircraft
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-57121
    Format: application/pdf
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  • 8
    Publication Date: 2019-05-23
    Description: Drag measurements at low lift of four-nacelle aircraft configuration with longitudinal distribution of cross-sectional area conducive to low transonic drag rise
    Keywords: AERODYNAMICS
    Type: NACA-RM-L53E29
    Format: application/pdf
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  • 9
    Publication Date: 2019-06-28
    Keywords: AERODYNAMICS
    Type: NACA-RM-A53G08
    Format: application/pdf
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  • 10
    Publication Date: 2019-06-28
    Description: Calculations have been made for the icing limit of a diamond airfoil at zero angle of attack in terms of the stream Mach number, stream temperature, and pressure altitude. The icing limit is defined as a wetted-surface temperature of 320 F and is related to the stream conditions by the method of Hardy. The results show that the point most likely to ice on the airfoil lies immediately behind the shoulder and is subject to possible icing at Mach numbers as high as 1.4.
    Keywords: AERODYNAMICS
    Type: NACA-TN-2861
    Format: application/pdf
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  • 11
    Publication Date: 2019-06-28
    Keywords: AERODYNAMICS
    Type: NACA-RM-E53C26
    Format: application/pdf
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  • 12
    Publication Date: 2019-06-28
    Description: The effects of primary and. runback icing and frost formations on the drag of an 8-foot-chord NACA 651-212 airfoil section were investigated over a range of angles of attack from 20 to 80 and airspeeds up to 260 miles per hour for icing conditions with liquid-water contents ranging from 0.25 to 1.4 grams per cubic meter and datum air temperatures of -30 to 30 F. The results showed that glaze-ice formations, either primary or runback, on the upper surface near the leading edge of the airfoil caused large and rapid increases in drag, especially at datum air temperatures approaching 32 F and in the presence of high rates of water catch. Ice formations at lower temperatures (rime ice) did not appreciably increase the drag coefficient over the initial (standard roughness) drag coefficient. Cyclic de-icing of the primary Ice formations on the airfoil leading-edge section permitted the drag coefficient to return almost to the bare airfoil drag value. Runback icing on the lower surface did not present a serious drag problem except when heavy spanwise ridges of runback ice occurred aft of the heatable area. Frost formations caused rapid and large increases in drag with incipient stalling of the airfoil.
    Keywords: AERODYNAMICS
    Type: NACA-TN-2962
    Format: application/pdf
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  • 13
    Publication Date: 2019-06-28
    Description: An investigation has been made in the NACA Lewis icing research tunnel to determine the aerodynamic and icing characteristics of a full-scale induction-system air-scoop assembly incorporating a flush alternate inlet. The flush inlet was located immediately downstream of the offset ram inlet and included a 180 deg reversal and a 90 deg elbow in the ducting between inlet and carburetor top deck. The model also had a preheat-air inlet. The investigation was made over a range of mass-air- flow ratios of 0 to 0.8, angles of attack of 0 and 4 deg airspeeds of 150 to 270 miles per hour, air temperatures of 0 and 25 F various liquid-water contents, and droplet sizes. The ram inlet gave good pressure recovery in both clear air and icing but rapid blockage of the top-deck screen occurred during icing. The flush alternate inlet had poor pressure recovery in both clear air and icing. The greatest decreases in the alternate-inlet pressure recovery were obtained at icing conditions of low air temperature and high liquid-water content. No serious screen icing was observed with the alternate inlet. Pressure and temperature distributions on the carburetor top deck were determined using the preheat-air supply with the preheat- and alternate-inlet doors in various positions. No screen icing occurred when the preheat-air system was operated in combination with alternate-inlet air flow.
    Keywords: AERODYNAMICS
    Type: NACA-RM-E53E07
    Format: application/pdf
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  • 14
    Publication Date: 2019-06-28
    Keywords: AERODYNAMICS
    Type: NACA-RM-A52B06
    Format: application/pdf
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  • 15
    Publication Date: 2019-05-30
    Description: Estimating method for lift interference of wing- body combinations at supersonic speeds
    Keywords: AERODYNAMICS
    Type: NACA-RM-A51J04
    Format: application/pdf
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  • 16
    Publication Date: 2019-06-28
    Description: The general characteristics of the flow field in a submerged air inlet are investigated by theoretical, wind-tunnel, and visual-flow studies. Equations are developed for calculating the laminar and turbulent boundary-layer growth along the ramp floor for parallel, divergent, and convergent ramp walls, and a general equation is derived relating the boundary-layer pressure losses to the boundary-layer thickness. It is demonstrated that the growth of the boundary layer on the floor of the divergent-ramp inlet is retarded and that a vortex pair is generated in such an inlet. Functional relationships are established between the pressure losses in the vortices and the geometry of the inlet. A general discussion of the boundary layer and vortex formations is included, in which variations of the various losses and of the incremental external drag with mass-flow ratio are considered. Effects of compressibility are also discussed.
    Keywords: AERODYNAMICS
    Type: NACA-TN-2323
    Format: application/pdf
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  • 17
    Publication Date: 2019-08-14
    Description: Theoretical blockage corrections are presented for a body of revolution and for a three-dimensional, unswept wing in a circular or rectangular wind tunnel. The theory takes account of the effects of the wake and of the compressibility of the fluid, and is based on the assumption that the dimensions of the model are small in comparison with those of the tunnel throat. Formulas are given for correcting a number of the quantities, such as dynamic pressure and Mach number, measured in wind tunnel tests. The report presents a summary and unification of the existing literature on the subject
    Keywords: AERODYNAMICS
    Type: NACA-TR-995
    Format: application/pdf
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  • 18
    Publication Date: 2019-06-27
    Description: The problem of the minimum induced drag of wings having a given lift and a given span is extended to include cases in which the bending moment to be supported by the wing is also given. The theory is limited to lifting surfaces traveling at subsonic speeds. It is found that the required shape of the downwash distribution can be obtained in an elementary way which is applicable to a variety of such problems. Expressions for the minimum drag and the corresponding spanwise load distributions are also given for the case in which the lift and the bending moment about the wing root are fixed while the span is allowed to vary. The results show a 15-percent reduction of the induced drag with a 15-percent increase in span as compared with results for an elliptically loaded wing having the same total lift and bending moment.
    Keywords: AERODYNAMICS
    Type: NACA-TN-2249 , Collected Works of Robert T. Jones; p 539-556
    Format: application/pdf
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