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  • Industrial Chemistry  (1,307)
  • Aerodynamics
  • Aircraft Stability and Control
  • 2020-2024  (12)
  • 1950-1954  (1,415)
  • 1935-1939  (15)
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  • 1
    facet.materialart.
    Unknown
    MDPI - Multidisciplinary Digital Publishing Institute
    Publication Date: 2023-11-30
    Description: Active flow control (AFC) utilizes local active perturbations to induce changes in global flow behavior that result in aero/hydrodynamic performance improvement. It has been a vibrant research area with potential applications in a wide range of engineering fields. This Special Issue is a collection of 11 excellent research papers published in Actuators, showcasing and discussing new advances in both fundamental and applied AFC technologies.
    Keywords: Active flow control ; Actuators ; Aerodynamics ; Synthetic jets&nbsp ; bic Book Industry Communication::T Technology, engineering, agriculture::TB Technology: general issues
    Language: English
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  • 2
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    IntechOpen | IntechOpen
    Publication Date: 2024-04-11
    Description: Some sixty years after the experimental flights of the North American X-15 hypersonic rocket-powered aircraft, sustained hypervelocity travel is still the next frontier in high-speed transportation. Today, there is much excitement and interest regarding hypersonic vehicles. In fact, many aerospace agencies, large industries, and several start-ups are involved in design activities and experimental campaigns both in wind tunnels and in-flight with full-scale experimental flying test beds and prototypes to make hypersonic travel almost as easy and convenient as airliner travel. Achieving this goal will radically revolutionize the future of civil transportation. This book contains valuable contributions that focus on various design issues related to hypersonic aircraft.
    Keywords: Aerodynamics ; thema EDItEUR::T Technology, Engineering, Agriculture, Industrial processes::TG Mechanical engineering and materials::TGM Materials science::TGMF Engineering: Mechanics of fluids::TGMF1 Aerodynamics
    Language: English
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  • 3
    Publication Date: 2023-12-20
    Description: Giulia Parola’s Environmental Democracy at the Global Level: Rights and Duties for a New Citizenship can be seen as a manifesto that is both traditional and revolutionary at the same time. It calls for the construction of a new civilisation centred on the environment, while drawing on the traditional notions of democratic government. It adopts an approach that is focused on the power of individuals rather than governments, as ways to protect and improve the environment. It proposes that environmental rights and ecological duties are self-evident and inalienable, and should be treated as the cornerstones of a new democracy. Parola’s book is a thought provoking and intriguing work that will be of interest to scholars of environmental studies as well as to legal practitioners and non-specialists. Giulia Parola has studied Environmental Law at the University of Torino, at the University of René Descartes in Paris, (where she obtained PhD in Public Law) and at the University of Iceland ( LLM in Natural Resources Law and International Environmental Law). In 2011, she was appointed by the University of Laval (Canada, Quebec) as a researcher and a lecturer in Environmental Law.
    Keywords: GE1-350 ; K ; International Law ; Materials Science ; Industrial Chemistry ; Law ; Comparative Law ; Foreign Law ; Environment ; Natural Sciences ; German Civil Code ; Pollution Control ; bic Book Industry Communication::K Economics, finance, business & management::KC Economics::KCN Environmental economics
    Language: English
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  • 4
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    IntechOpen | IntechOpen
    Publication Date: 2024-04-11
    Description: Aerodynamics, the study of air motion around solid objects, allows us to understand and measure the dominating forces acting on aircrafts, buildings, bridges, automobiles, and other structures. The forces that result in an aircraft overcoming gravity and drag are called thrust and lift. Various parameters such as geometrical configurations of objects, as well as physical properties of air, which may be functions of position and time, affect those forces. This book covers some of the latest studies regarding the application of the principles of aerodynamics to the design of many different engineered objects. This book will be of interest to mechanical and aerospace engineering students, academics, and researchers who are looking for new insights into this fascinating branch of fluid mechanics.
    Keywords: Aerodynamics ; thema EDItEUR::T Technology, Engineering, Agriculture, Industrial processes::TG Mechanical engineering and materials::TGM Materials science
    Language: English
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  • 5
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    Taylor & Francis | CRC Press
    Publication Date: 2024-03-31
    Description: Because of many misconceptions, the biological drug manufacturing industry does not fully utilize disposable components, despite their wide availability. These misconceptions include concerns for the quality of materials, running costs, scalability, the level of automation possible, and the training of staff needed to include these components in existing bioprocessing systems. Not fully realizing the long-term benefits, many manufacturers are unwilling to discard investments made in fixed equipment and traditional stainless steel systems. Regulatory and environmental concerns, however, will eventually compel manufacturers to adopt disposable systems. Making a strong case for disposables, Disposable Bioprocessing Systems demonstrates the true potential of these systems. Written by a researcher and professor with hands-on experience in designing, establishing, and validating biological manufacturing facilities worldwide, and creating model facilities using maximum disposable technology, this book is the first comprehensive introduction to understanding disposable systems. It gives an overview of the current state of the disposable bioprocessing industry, resolves all controversial issues, and guides readers in choosing disposable components that meet their needs. An important chapter on safety addresses facts and myths about the use of plastics and elastomers—including the issue of leaching—and how to ensure regulatory compliance. Helping readers understand their choices, the book describes the equipment and systems available to prepare the starting materials for the manufacturing of biological drugs—from disposable containers to filters. The author also discusses costs, regulations, and concerns about waste disposal, and shares his predictions for the future of the disposable bioprocessing industry. A practical manual for those interested in the transition to disposable systems, this book will also interest students of bioprocessing. It offers a timely view of disposable bioprocessing technology as a "game changer" that will facilitate developing new drugs and conducting research in the emerging field of stem cells and gene therapy.
    Keywords: Biotechnology ; Pharmaceutical Science ; Industrial Chemistry ; PHARMACEUTICAL ; BIOSCIENCE ; CHEMLIB ; SCI-TECH ; BIOMEDICALSCIENCE ; CHEMICALENGINEERING ; STM ; bags ; bioreactors ; cleaning ; disposal ; downstream ; single ; stainless ; steel ; use ; validation ; thema EDItEUR::M Medicine and Nursing::MF Pre-clinical medicine: basic sciences ; thema EDItEUR::M Medicine and Nursing::MK Medical specialties, branches of medicine::MKG Pharmacology ; thema EDItEUR::T Technology, Engineering, Agriculture, Industrial processes::TD Industrial chemistry and manufacturing technologies::TDC Industrial chemistry and chemical engineering ; thema EDItEUR::M Medicine and Nursing::MQ Nursing and ancillary services::MQW Biomedical engineering
    Language: English
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  • 6
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    IntechOpen | IntechOpen
    Publication Date: 2024-04-11
    Description: Aerodynamics, from a modern point of view, is a branch of physics that study physical laws and their applications, regarding the displacement of a body into a fluid, such concept could be applied to any body moving in a fluid at rest or any fluid moving around a body at rest. This Book covers a small part of the numerous cases of stationary and non stationary aerodynamics; wave generation and propagation; wind energy; flow control techniques and, also, sports aerodynamics. It's not an undergraduate text but is thought to be useful for those teachers and/or researchers which work in the several branches of applied aerodynamics and/or applied fluid dynamics, from experiments procedures to computational methods.
    Keywords: Aerodynamics ; thema EDItEUR::T Technology, Engineering, Agriculture, Industrial processes::TG Mechanical engineering and materials::TGM Materials science
    Language: English
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  • 7
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    IntechOpen | IntechOpen
    Publication Date: 2024-04-11
    Description: This book is intended to be a valuable addition to students, engineers, scientists, industrialists, consultants and others providing greater insight into wind tunnel designs and their enormous research potential. It is a compilation of works from world experts on subsonic and supersonic wind tunnel designs, applicable to a diverse range of disciplines. The book is organised in two sections. The first section comprises of three chapters on various aspects of stationary and portable subsonic wind tunnel designs, followed by one chapter on supersonic wind tunnel and the final chapter discusses a method to address unsteadiness effects of fan blade rotation. The second section contains four chapters regarding wind tunnel applications across a multitude of engineering fields including civil, mechanical, chemical and environmental engineering.
    Keywords: Aerodynamics ; thema EDItEUR::T Technology, Engineering, Agriculture, Industrial processes::TG Mechanical engineering and materials::TGM Materials science
    Language: English
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  • 8
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    IntechOpen | IntechOpen
    Publication Date: 2024-04-11
    Description: This book reports the latest development and trends in the low Re number aerodynamics, transition from laminar to turbulence, unsteady low Reynolds number flows, experimental studies, numerical transition modelling, control of low Re number flows, and MAV wing aerodynamics. The contributors to each chapter are fluid mechanics and aerodynamics scientists and engineers with strong expertise in their respective fields. As a whole, the studies presented here reveal important new directions toward the realization of applications of MAV and wind turbine blades.
    Keywords: Aerodynamics ; thema EDItEUR::T Technology, Engineering, Agriculture, Industrial processes::TG Mechanical engineering and materials::TGM Materials science
    Language: English
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  • 9
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    IntechOpen
    Publication Date: 2024-04-04
    Description: Spacecraft attitude maneuvers comply with Euler's moment equations, a set of three nonlinear, coupled differential equations. Nonlinearities complicate the mathematical treatment of the seemingly simple action of rotating, and these complications lead to a robust lineage of research. This book is meant for basic scientifically inclined readers, and commences with a chapter on the basics of spaceflight and leverages this remediation to reveal very advanced topics to new spaceflight enthusiasts. The topics learned from reading this text will prepare students and faculties to investigate interesting spaceflight problems in an era where cube satellites have made such investigations attainable by even small universities. It is the fondest hope of the editor and authors that readers enjoy this book.
    Keywords: Science ; Mechanics ; Aerodynamics ; bic Book Industry Communication::P Mathematics & science::PH Physics::PHD Classical mechanics::PHDF Fluid mechanics ; thema EDItEUR::P Mathematics and Science::PH Physics::PHD Classical mechanics::PHDF Physics: Fluid mechanics
    Language: English
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  • 10
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    Taylor & Francis | CRC Press
    Publication Date: 2024-04-11
    Description: Suitable for practicing engineers and engineers in training, this book covers the most important operations involving particulate solids. Through clear explanations of theoretical principles and practical laboratory exercises, the text provides an understanding of the behavior of powders and pulverized systems. It also helps readers develop skills for operating, optimizing, and innovating particle processing technologies and machinery in order to carry out industrial operations. The author explores common bulk solids processing operations, including milling, agglomeration, fluidization, mixing, and solid-fluid separation.
    Keywords: Industrial Chemistry ; Food Chemistry ; FOOD ; CHEMLIB ; SCI-TECH ; CHEMICALENGINEERING ; CHEMISTRY ; STM ; bed ; distribution ; fluidized ; industry ; mass ; material ; particle-size ; processing ; technology ; transfer ; thema EDItEUR::T Technology, Engineering, Agriculture, Industrial processes::TD Industrial chemistry and manufacturing technologies::TDC Industrial chemistry and chemical engineering ; thema EDItEUR::T Technology, Engineering, Agriculture, Industrial processes::TD Industrial chemistry and manufacturing technologies::TDC Industrial chemistry and chemical engineering::TDCT Food and beverage technology ; thema EDItEUR::T Technology, Engineering, Agriculture, Industrial processes::TG Mechanical engineering and materials::TGM Materials science
    Language: English
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  • 11
    facet.materialart.
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    IntechOpen | IntechOpen
    Publication Date: 2024-04-11
    Description: Although great advances in computational methods have been made in recent years, wind tunnel tests remain essential for obtaining the full range of data required to guide detailed design decisions for various practical engineering problems. This book collects original and innovative research studies on recent applications in wind tunnel tests, exhibiting various investigation directions and providing a bird’s eye view on this broad subject area. It is composed of seven chapters that have been grouped in two major parts. The first part of the book (chapters 1–4) deals with wind tunnel technologies and devices. The second part (chapters 5–7) deals with the latest applications of wind tunnel testing. The text is addressed not only to researchers but also to professional engineers, engineering lecturers, and students seeking to gain better understanding of the current status of wind tunnels. Through its seven chapters, the reader will have an access to a wide range of works related to wind tunnel testing.
    Keywords: Aerodynamics ; thema EDItEUR::T Technology, Engineering, Agriculture, Industrial processes::TG Mechanical engineering and materials::TGM Materials science
    Language: English
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  • 12
    facet.materialart.
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    IntechOpen | IntechOpen
    Publication Date: 2024-04-11
    Description: Spacecraft attitude maneuvers comply with Euler's moment equations, a set of three nonlinear, coupled differential equations. Nonlinearities complicate the mathematical treatment of the seemingly simple action of rotating, and these complications lead to a robust lineage of research. This book is meant for basic scientifically inclined readers, and commences with a chapter on the basics of spaceflight and leverages this remediation to reveal very advanced topics to new spaceflight enthusiasts. The topics learned from reading this text will prepare students and faculties to investigate interesting spaceflight problems in an era where cube satellites have made such investigations attainable by even small universities. It is the fondest hope of the editor and authors that readers enjoy this book.
    Keywords: Aerodynamics ; thema EDItEUR::T Technology, Engineering, Agriculture, Industrial processes::TG Mechanical engineering and materials::TGM Materials science
    Language: English
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  • 13
    Publication Date: 2019-06-28
    Description: No abstract available
    Keywords: Aerodynamics
    Type: NACA-RM-SL54F28
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  • 14
    Publication Date: 2019-07-11
    Description: The effects of several wing leading-edge camber and deflected-tip modifications on the force and moment characteristics of a 1/20-scale model of the Convair F-102 airplane have been determined at Mach numbers from 0.60 t o 1.14 for angles of attack up to 14 deg. in the Langley 8-foot transonic tunnel. The effects of elevator deflections from 0 deg. to -10 deg. were also obtained for a configuration incorporating favorable leading- edge and tip modifications. Leading-edge modifications which had a small amount of constant-chord camber obtained by vertically adjusting the thickness distribution over the forward (3.9 percent of the mean aerodynamic chord) portion of the wing were ineffective in reducing the drag at lifting conditions at transonic speeds. Leading edges with relatively large cambers designed to support nearly elliptical span load distributions at lift coefficients of 0.15 and 0.22 near a Mach number of 1.0 produced substantial reductions in drag at most lift coefficients.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL54K29
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  • 15
    Publication Date: 2019-07-11
    Description: An investigation has been made in the Langley low-turbulence pressure tunnel of the aerodynamic characteristics of the NACA 0012, 64(sub 2)-015, and 64(sub 3)-018 airfoil sections. Data were obtained at Mach numbers from 0.3 to that for tunnel choke, at angles of attack from -2deg to 30deg, and with the surface. of each airfoil smooth-and with roughness applied at the leading edge.The Reynolds numbers of the tests ranged from 0.8 x 10(exp 6) to 4.4 x 10(exp 6). The results are presented as variations of lift, drag, and quarter-chord pitching-moment coefficients with Mach number.
    Keywords: Aerodynamics
    Type: NACA-RM-L54H06a
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  • 16
    Publication Date: 2019-07-12
    Description: The effects of deflecting full-span, constant-chord, leading-edge flaps, having either round or sharp leading edges, upon the lift, drag,. and pitching moment characteristics of a model of an interceptor-type aircraft have been determined experimentally at subsonic and supersonic speeds. Results indicate that the variations of lift with angle of attack and of pitching moment with lift were unaffected by either the shape of the flap leading edge or flap deflection. Deflection of the flaps having either a round or sharp leading edge increased the drag at zero lift at both subsonic and supersonic speeds. In spite of the increase in the drag at zero lift, however, deflection of the flaps increased the maximum lift-drag ratio at subsonic speeds and had no deleterious effect at supersonic speeds.
    Keywords: Aerodynamics
    Type: NACA-RM-SA54B16
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  • 17
    Publication Date: 2019-07-12
    Description: An investigation to determine the altitude performance of the J57-P-1 turbojet engine and components was conducted at the NACA Lewis altitude wind tunnel. Data were obtained over a corrected inboard rotor speed range from 56 to 106 percent of rated speed, with intercompressor bleeds both open and closed, at altitudes from 15,000 to 50,000 feet and at a flight Mach number of 0.81. The corresponding range of Reynolds number indices was from 0.858 to 0.213. All data presented were obtained with a fixed-area exhaust nozzle sized according to the manufacturer's specification. Over-all engine performance parameters are presented as functions of inboard rotor speed corrected on the basis of engine inlet temperature. Component parameters are presented as functions of their respective corrected rotor speeds. A tabulation of all performance data is included in addition to the graphical presentation. Corrected net thrust is unusually sensitive to changes in corrected inboard rotor speed in the high speed region. A change of 1 percent in speed, at sated speed, produced a change of 6 percent in corrected net thrust . At rated engine speed, increasing the altitude from 15,000 to 50,000 feet at a constant flight Mach number of 0.81 increased the specific fuel consumption 13 percent but did not affect corrected net thrust.
    Keywords: Aerodynamics
    Type: NACA-RM-SE54D30
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  • 18
    Publication Date: 2019-07-11
    Description: An investigation was made of a 1/10-scale dynamically similar model of the North American F-86 airplane to study its behavior when ditched. The model was landed in calm water at the Langley tank no. 2 monorail. Various landing attitudes, speeds, and conditions of damage were simulated. The behavior of the model was determined from visual observations, acceleration records, and motion-picture records of the ditchings. Data are presented in tabular form, sequence photographs, and time-history acceleration curves. From the results of the investigation it was concluded that the airplane should be ditched at the nose-high, 14 deg attitude to avoid the violent dive which occurs at the 4 deg attitude. The flaps and leading-edge slats should be fully extended to obtain the lowest possible landing speed. The wing tanks should be jettisoned to avoid the undesirable behavior which occurs with the tanks attached. In a calm-water ditching under these conditions the airplane will run smoothly for about 600 feet. Maximum longitudinal and vertical decelerations of about 3g will be encountered.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL9K01
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  • 19
    Publication Date: 2019-07-11
    Description: An investigation is being conducted to determine the dynamic stability and control characteristics of a 0.13-scale flying model of Convair XFY-1 vertically rising airplane. This paper presents the results of flight and force tests to determine the stability and control characteristics of the model in vertical descent and landings in still air. The tests indicated that landings, including vertical descent from altitudes representing up to 400 feet for the full-scale airplane and at rates of descent up to 15 or 20 feet per second (full scale), can be performed satisfactorily. Sustained vertical descent in still air probably will be more difficult to perform because of large random trim changes that become greater as the descent velocity is increased. A slight steady head wind or cross wind might be sufficient to eliminate the random trim changes.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL54C19a
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  • 20
    Publication Date: 2019-07-11
    Description: A supplementary investigation was conducted in the Langley 20-foot free-spinning tunnel on a 1/24-scale model of the Grumman F9F-6 airplane. The primary purpose of the investigation was to reevaluate the spin-recovery characteristics of the airplane in view of the fact that the ailerons had been eliminated from the flaperon-aileron lateral control system of the airplane. A spin-tunnel investigation on a model of the earlier version of the F9F-6 airplane had indicated that use of ailerons with the spin (stick right in a right spin) was essential to insure recovery. The results indicate that with.ailerons eliminated, it may be difficult to obtain an erect developed spin but if a fully developed spin is obtained on the airplane, recovery therefrom may be difficult or impossible. Flaperon deflection should have little effect on spins or recoveries.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL54L01a
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  • 21
    Publication Date: 2019-07-11
    Description: An experimental investigation has been conducted to determine the stability and control characteristics of a 0.13-scale free-flight model of the Convair XFY-1 airplane during take-offs and landings in steady winds. The tests indicated that take-offs in headwinds up to at least 20 knots (full scale) will be fairly easy to perform although the airplane may be blown downstream as much as 3 spans before a trim condition can be established. The distance that the airplane will be blown down-stream can be reduced by restraining the upwind landing gear until the instant of take-off. The tests also indicated that spot landings in headwinds up to at least 30 knots (full scale) and in crosswinds up to at least 20 knots (full scale) can be accomplished with reasonable accuracy although, during the landing approach, there will probably be an undesirable nosing-up tendency caused by ground effect and by the change in angle of attack resulting from vertical descent. Some form of arresting gear will probably be required to prevent the airplane from rolling downwind or tipping over after contact. This rolling and tipping can be prevented by a snubbing line attached to the tip of the upwind' wing or tail or by an arresting gear consisting of a wire mesh on the ground and hooks on the landing gear to engage the mesh.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL54E28
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  • 22
    Publication Date: 2019-07-11
    Description: The effect on drag of positioning symmetrically mounted Douglas Aircraft Company, Inc. stores in pairs on a parabolic fuselage of fineness ratio 10.0 has been determined by flight tests of rocket-propelled, zero-lift models through a range of Mach number from 0.9 to 1.8. The stores were mounted in half-submerged positions and on pylons and were tested in three longitudinal locations on the fuselage with the forward position being located at the maximum diameter of the fuselage. The effects on drag of removing the half-submerged stores or extending them outward on pylons also was investigated by tests of models with half-submerged-store cavities on the fuselage. Two pylons differing in airfoil section and thickness were tested at the forward position of the stores on the fuselage with cavities. The half-submerged stores gave the smallest drag increments, which were approximately equal regardless of their respective longitudinal locations. Removing the half-submerged stores to expose the cavities increased the drag increments from two to three times. For the pylon-mounted stores, the store in the midposition had less drag than in the forward or rear positions at supersonic speeds. Adding the half-submerged-store cavities to the pylon-mounted-store configurations reduced the drag at the rear position between Mach numbers 0.95 and 1.50 and increased the drag at the midposition throughout the speed range. Changing from the 6-percent-thick flat pylon to the 10-percent-thick airfoil pylon increased the total drag slightly above Mach number 1.10. Good agreement was obtain& between the experimental and theoretical interference drag coefficients for the pylon-mounted stores (without fuselage cavities} in the three longitudinal locations tested at Mach numbers 1.2 and 1.5.
    Keywords: Aerodynamics
    Type: NACA-RM-L54E26
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  • 23
    Publication Date: 2019-08-14
    Description: The lift, pitching-moment, and drag characteristics of a missile configuration having a body of fineness ratio 9.33 and a cruciform triangular wing and tail of aspect ratio 4 were measured at a Mach number of 1.99 and a Reynolds number of 6.0 million, based on the body length. The tests were performed through an angle-of-attack range of -5 deg to 28 deg to investigate the effects on the aerodynamic characteristics of roll angle, wing-tail interdigitation, wing deflection, and interference among the components (body, wing, and tail). Theoretical lift and moment characteristics of the configuration and its components were calculated by the use of existing theoretical methods which have been modified for application to high angles of attack, and these characteristics are compared with experiment. The lift and drag characteristics of all combinations of the body, wing, and tail were independent of roll angle throughout the angle-of-attack range. The pitching-moment characteristics of the body-wing and body-wing-tail combinations, however, were influenced significantly by the roll angle at large angles of attack (greater than 10 deg). A roll from 0 deg (one pair of wing panels horizontal) to 45 deg caused a forward shift in the center of pressure which was of the same magnitude for both of these combinations, indicating that this shift originated from body-wing interference effects. A favorable lift-interference effect (lift of the combination greater than the sum of the lifts of the components) and a rearward shift in the center of pressure from a position corresponding to that for the components occurred at small angles of attack when the body was combined with either the exposed wing or tail surfaces. These lift and center-of-pressure interference effects were gradually reduced to zero as the angle of attack was increased to large values. The effect of wing-tail interference, which influenced primarily the pitching-moment characteristics, is dependent on the distance between the wing trailing vortex wake and the tail surfaces and thus was a function of angle of attack, angle of roll, and wing-tail interdigitation. Although the configuration at zero roll with the wing and tail in line exhibited the least center-of-pressure travel, the configuration with the wing and tail interdigitated had the least change in wing-tail interference over the angle-of-attack range. The lift effectiveness of the variable-incidence wing was reduced by more than 70 percent as a result of an increase in the combined angle of attack and wing incidence from 0 deg to 40 deg. The wing-tail interference (effective downwash at the tail) due to wing deflection was nearly zero as a result of a region of negative vorticity shed from the inboard portion of the wing. The lift characteristics of the configuration and its components were satisfactorily predicted by the calculated results, but the pitching moments at large angles of attack were not because of the influence of factors for which no adequate theory is available, such as the variation of the crossflow drag coefficient along the body and the effect of the wing downwash field on the afterbody loading.
    Keywords: Aerodynamics
    Type: NACA-RM-A54H27
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  • 24
    Publication Date: 2019-07-11
    Description: A flight test has been conducted to determine the longitudinal stability and control,characteristics of a 0.133-scale model of the Consolidated Vultee XFY-1 airplane without propellers for the Mach number range between 0.73 and 1.19.
    Keywords: Aerodynamics
    Type: NACA-RM-SL54B03A
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  • 25
    Publication Date: 2019-07-11
    Description: An investigation was conducted in the Langley high-speed 7- by 10-foot tunnel to determine effects of modifications to a bomb model (particularly with regard to drag) when mounted on a wing-fuselage model and tested at Mach numbers from 0.70 to 1.10. In addition, the static longitudinal stability characteristics of several configurations of a larger scale model of the bomb alone were obtained over a Mach number range from 0.50 to 0.95. The results obtained for the wing-fuselage-bomb model indicate that large reductions in installation drag were obtained for the wing-fuselage-bomb model when the flat nose of the basic bomb was replaced by rounded or pointed noses of various calibers. Shortening the mounting pylon gave further decreases in the installation drag. The tests of the bomb alone indicated that only the flat-nose configurations were stable over the greater part of the Mach number range. Nose-shape modifications which improved the drag also caused the bombs to become unstable at low angles of attack. The stability of the low-drag bomb configurations could be improved by lengthening the cylindrical portion of the body behind the center of gravity.
    Keywords: Aerodynamics
    Type: NACA-RM-SL54D30
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  • 26
    Publication Date: 2019-07-11
    Description: An investigation has been conducted in the Langley 8-foot transonic tunnel to determine the effects of several fuselage modifications on the transonic drag-rise characteristics of a 1/20-scale model of the Convair F-102 airplane. Tests covered an angle-of-attack range from 0deg to about 10deg and a Mach number range from 0.60 to 1.14. Results indicated that the transonic drag rise .for the basic F-102 airplane could be substantially reduced by extending the fuselage after-body approximately 8 percent of the fuselage length. Tests of other bodies indicated that a shorter (4-percent) afterbody extension may have a similar effect on the drag rise. Further improvement of the axial cross-sectional-area distribution of the 8-percent extended configuration through the addition of fuselage volume resulted in additional reductions in the drag rise at a Mach number of 1.0 and caused no or only slight drag penalties at the higher Mach numbers. The results of the present tests generally substantiate the area-rule concept with respect to the prediction of the transonic drag rise through the use of an equivalent-area body of revolution for a practical delta-wing airplane configuration.
    Keywords: Aerodynamics
    Type: NACA-RM-SL54K18a
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  • 27
    Publication Date: 2019-07-11
    Description: An experimental investigation has been conducted to determine the dynamic stability and control characteristics in hovering and transition flight of a 0.13-scale flying model of the Convair XFY-1 vertically rising airplane with the lower vertical tail removed. The purpose of the tests was to obtain a general indication of the behavior of a vertically rising airplane of the same general type as the XFY-1 but without a lower vertical tail in order to simplify power-off belly landings in an emergency. The model was flown satisfactorily in hovering flight and in the transition from hovering to normal unstalled forward flight (angle of attack approximately 30deg). From an angle of attack of about 30 down to the lowest angle of attack covered in the flight tests (approximately 15deg) the model became progressively more difficult to control. These control difficulties were attributed partly to a lightly damped Dutch roll oscillation and partly to the fact that the control deflections required for hovering and transition flight were too great for smooth flight at high speeds. In the low-angle-of-attack range not covered in the flight tests, force tests have indicated very low static directional stability which would probably result in poor flight characteristics. It appears, therefore, that the attainment of satisfactory directional stability, at angles of attack less than 10deg, rather than in the hovering and transition ranges of flight is the critical factor in the design of the vertical tail for such a configuration.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL54E07
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  • 28
    Publication Date: 2019-07-11
    Description: A low-speed wind-tunnel investigation has been made of some aspects of the aerodynamic problems associated with the use of air-to-air missiles when carried externally on aircraft. Measurements of the forces and moments on a missile model for a range of positions under the mid-semispan location of a 45deg sweptback wing indicated longitudinal and lateral forces with regard to both carriage and release of the missiles. Surveys of the characteristics of the flow field in the region likely to be traversed by the missiles showed abrupt gradients in both flow angularity and in local dynamic pressure. Through the use of aerodynamic data on the isolated missile and the measured flow-field characteristics, the longitudinal forces and moments acting on the missile while in the presence of the wing-fuselage combination could be estimated with fair accuracy. Although the lateral forces and moments predicted were qualitatively correct, there existed some large discrepancies in absolute magnitude.
    Keywords: Aerodynamics
    Type: NACA-RM-L54J20
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  • 29
    Publication Date: 2019-07-12
    Description: Experimental results showing the static longitudinal-stability and control characteristics of a model of a fighter airplane employing a low-aspect-ratio unswept wing and an all-movable horizontal tail are presented. The investigation was made over a Mach number range from 0.60 to 0.90 and from 1.35 to 1.90 at a constant Reynolds number of 2.40 million, based on the wing mean aerodynamic chord. Because of the location of the horizontal tail at the tip of the vertical tail, interference was noted between the vertical tail and the horizontal tail and between the wing and the horizontal tail. This interference produced a positive pitching-moment coefficient at zero lift throughout the Mach number range of the tests, reduced the change in stability with increasing lift coefficient of the wing at moderate lift coefficients in the subsonic speed range, and reduced the stability at low lift coefficients at high supersonic speeds. The lift and pitching-moment effectiveness of the all movable tail was unaffected by the interference effects and was constant throughout the lift-coefficient range of the tests at each Mach number except 1.90.
    Keywords: Aerodynamics
    Type: NACA-RM-SA54D05
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  • 30
    Publication Date: 2019-07-12
    Description: This paper presents the results of an investigation of the dynamic stability and controllability of a model which approximately represents the Lockheed XFV-1 airplane to a 1/8 scale. The investigation consisted of hovering flights in still air at a considerable height above the ground, hovering flights very close to the ground, vertical take-offs and landings, flights through the transition range from hovering to normal forward flight, and sideways translational flights. The model could be flown smoothly and easily in hovering flight despite the fact that the uncontrolled pitching and yawing motions were unstable oscillations. There was a noticeable reduction in the controllability of the model when hovered very close to the ground but take-offs could be made easily and landings on a g,ven spot could be made accurately in spite of this adverse ground effect. Flights through the transition range from hovering to normal forward flight could be performed fairly easily. The model seemed to have stability of angle of attack and angle of roll over most of the transition range. The yawing motion was divergent in the very high angle-of-attack range but could be controlled easily. At the lower angles of attack, the model seemed to become stable in yaw. In sideways flight there was an increasingly strong tendency to diverge in roll as the speed was increased and finally, at a speed of about 25 knots (full scale), the model rolled off despite efforts of the pilot to control it.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL54J18
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  • 31
    Publication Date: 2019-07-12
    Description: An investigation has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 1.41 to determine the static stability and control and drag characteristics of a l/l5-scale model of the Grunman F9F-9 airplane. The effects of alternate fuselage shapes, wing camber, wing fences, and fuselage dive brakes on the aerodynamic characteristics were also investigated. These tests were made at a Reynolds number of 1.96 x l0 (exp 6) based on the wing mean aerodynamic chord of 0.545 foot. The basic configuration had a static margin of stability of 38.4 percent of the mean aerodynamic chord and a minimum drag coefficient of 0.049. For the maximum horizontal tail deflection investigated (-l0 deg), the maximum trim lift coefficient was 0.338. The basic configuration had positive static lateral stability at zero angle of attack and positive directional control throughout the angle-of-attack range investigated up to ll deg.
    Keywords: Aerodynamics
    Type: NACA-RM-SL54G08
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  • 32
    Publication Date: 2019-07-12
    Description: The longitudinal stability and control characteristics of a 1/30-scale model of the Republic XF-103 airplane were investigated in the Langley 8-foot transonic tunnel. The effect of speed brakes located at the end of the fuselage was also investigated. The main part of the investigation was made with internal flow in the model, but some data were obtained with no internal flow. The longitudinal stability and control at transonic-speeds appeared satisfactory. The transonic drag rise was small. The speed brakes had no adverse effects on longitudinal stability.
    Keywords: Aerodynamics
    Type: NACA-RM-SL54H24
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  • 33
    Publication Date: 2019-07-12
    Description: At the request of the Bureau of Aeronautics, Department of the Navy, National Advisory Committee for Aeronautics has conducted a preliminary investigation at high subsonic speeds of the static longitudinal and lateral stability characteristics of a 0.05-scale model of the Convair F2Y-1 water-based fighter airplane. The tests covered a Mach number range from 0.5 to 0.94 and corresponding Reynolds numbers, based on the wing mean aerodynamic chord, from 3.3 x 10(exp 6) to 4.3 x 10(exp 6). The maximum angle-of-attack range (obtained at the lower Mach numbers) was from -2 degrees to 25 degrees. Sideslip angles from -4 degrees to 12 degrees also were investigated. The investigation included effects of various arrangements of wing fences and of rocket packages.
    Keywords: Aircraft Stability and Control
    Type: NACA-RM-SL54A12
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  • 34
    Publication Date: 2019-07-12
    Description: A 1/5-scale, rocket-propelled model of the Convair F-102 configuration was tested in free flight to determine zero-lift drag at Mach numbers up to 1.34 and at Reynolds numbers comparable to those of the full-scale airplane. This large-scale model corresponded to the prototype airplane and had air flow through the duct. Additional zero-lift drag tests involved a series of small equivalent bodies of revolution which were launched by means of a helium gun. The several small-scale models tested corresponded to: the basic configuration, the 1/5-scale rocket-propelled model configuration, a 2-foot (full-scale) fuselage-extension configuration, and a 7-foot (full-scale) fuselage-extension configuration. Models designed to correspond to the area distribution at a Mach number of 1.0 were flown for each of these 'shapes and, in addition, models designed to correspond to the area distribution at a Mach number of 1.2 were flown for the 1/5-scale rocket-propelled model and the 7-foot-fuselage-extension configuration. The value of external pressure drag coefficient (including base drag) obtained from the large-scale rocket model was 0.0190 at a Mach number of 1..05 and the corresponding values from the equivalent-body tests varied from 0.0183 for the rocket-propelled model shape to 0.0137 for the 7-foot-fuselage-extension configuration. From the results of tests of equivalent bodies designed to correspond to the area distribution at a Mach number of 1.0, it is evident that the small changes in shape incorporated in the basic and 2-foot-fuselage-extension configurations from that of the rocket-propelled model configuration will provide no significant change in pressure drag. On the other hand, the data from the 7-foot-fuselage-extension model indicate a substantial reduction in pressure drag at transonic speeds.
    Keywords: Aerodynamics
    Type: NACA-RM-SL54DO9b
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  • 35
    Publication Date: 2019-07-12
    Description: The transonic longitudinal aerodynamic characteristics of a 0.0858-scale model of the Lockheed XF-104 airplane have been obtained from tests at the Langley 16-foot transonic tunnel. The results of the investigation provide some general information applicable to the transonic properties of thin, low-aspect-ratio, unswept wing configurations utilizing a high horizontal tail . The model employs a horizontal tail mounted at the top of the vertical tail and a wing with an aspect ratio of 2.5, a taper ratio of 0.385, and 3.4-percent-thick airfoil sections. The lift, drag, and static longitudinal pitching moment were measured at Mach numbers from 0.80 t o 1.09 and angles of attack from -2.5 deg to 22.5 deg. Some of the dynamic longitudinal stability properties of the airplane have been predicted from the test results. In addition, some visual flow studies on the wing surfaces obtained at Mach numbers of 0.80 and 1.00 are included. Results of the investigation show that the transonic rise in drag coefficient at zero lift is about 0.030. At high angles of attack, the model becomes longitudinally unstable at Mach numbers from 0.80 t o 0.90, whereas a reduction in static stability is experienced when very high angles of attack are reached at Mach numbers above 0.90. Longitudinal dynamic stability calculations show that the longitudinal control is good at angles of attack below the unstable break in the static pitching-moment curves, but a typical corrective control applied after the occurrence of neutral stability has little effect in averting pitch-up.
    Keywords: Aerodynamics
    Type: NACA-RM-SL54K19a
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  • 36
    Publication Date: 2019-07-12
    Description: The effects of elevator deflections from 0deg to -20deg on the force and moment characteristics of a 1/20-scale model of the Convair F-102 airplane with chordwise fences have been determined a t Mach numbers from 0.6 to 1.1 for angles of attack up to 20deg in the Langley 8-foot transonic tunnel. The configuration exhibited static longitudinal stability throughout the range tested, although a mild pitch-up tendency was indicated a t Mach numbers from 0.85 to 0.95. Elevator pitch effectiveness decreased rapidly between the Mach numbers of 0.9 and 1.0, however, no complete loss or reversal was indicated for all conditions tested. Because of the type of longitudinal control used, trimming the configuration from the zero elevator condition resulted in substantial decreases in lift-curve slope and maximum lift-drag ratio and increases in drag due to lift. The drag at zero lift, drag due to lift, and trim drag were high for this configuration.
    Keywords: Aerodynamics
    Type: NACA-RM-SL54G15
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  • 37
    Publication Date: 2019-07-12
    Description: A 1/10-scale rocket model of the Lockheed XF-104 with faired inlets has been flown over a Mach number range from 0.80 to 1.45 to determine low-lift drag and a limited amount of stability data. The center-of-gravity locations were 4.0 and 1.5 percent of the mean aerodynamic chord before and after sustainer firing, respectively. Oscillations induced by pulse rockets were used to determine stability data. The external transonic drag coefficient increased from a value of 0.0160 at Mach number 0.80 to a maximum of 0.0432 near Mach number 1-13, with a drag rise Mach number of about 0.93. At Mach numbers where it could be determined, the model exhibited stable dynamic and static stability characteristics at low lift.
    Keywords: Aerodynamics
    Type: NACA-RM-SL54E14
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  • 38
    Publication Date: 2019-07-12
    Description: A flight test has been conducted to determine the longitudinal stability and control characteristics of a 0.133-scale model of the Consolidated Vultee XFY-1 airplane with windmilling propellers for the Mach number range between 0.70 and 1.13. The variation of lift-curve slope C(sub L(sub alpha) with Mach number was gradual with a maximum value of 0.074 occurring at a Mach number of 0.97. Propellers had little effect upon the values of lift-curve slope or the linearity of lift coefficient with angle of attack. At lift coefficients between approximately 0.25 and 0.45 with an elevon angle of approximately -l0 deg, there was a region of neutral longitudinal stability at Mach numbers below 0.93 introduced by the addition of windmilling propellers. Below a lift coefficient of 0.10 and above a lift coefficient of 0.45, the model was longitudinally stable throughout the Mach number range of the test. There was a forward shift in the aerodynamic center of about 3-percent mean aerodynamic chord introduced by the addition of propellers. The aerodynamic center as determined at low lift moved gradually from a value of 28.5-percent mean aerodynamic chord at a Mach number of 0.75 to a value of 47-percent mean aerodynamic chord at a Mach number of 1.10. There was an abrupt decrease in pitch damping between Mach numbers of 0.88 and 0.99 followed by a rapid increase in damping to a Mach number of 1.06. The propellers had little effect upon the pitch damping characteristics . The transonic trim change was a large pitching-down tendency with and without windmilling propellers. The elevons were effective pitch controls throughout the speed range; however, their effectiveness was reduced about 50 percent at supersonic speeds. The propellers had no appreciable effect upon the control effectiveness.
    Keywords: Aerodynamics
    Type: NACA-RM-SL54F11
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  • 39
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Es wird der Versuch unternommen, die Wärmeübergangszahl einer in einem senkrechten Verdampferrohr umlaufenden und siedenden Flüssigkeit in Abhängigkeit von den maßgebenden Einflüssen anzugeben. Zu diesem Zwecke wurden die Rohrwandtemperatur und die Flüssigkeitstemperatur im Rohr gemessen. Für die verwendeten Rohrabmessungen läßt sich die Wärmeübergangszahl durch eine einfache Potenzfunktion wiedergeben. Über sie wird im folgenden berichtet.Die Versuche wurden durchgeführt mit der dankenswerten Unterstützung des Vereins Deutscher Ingenieure durch Zuschüsse aus ERP-Mitteln, ferner der DECHEMA, Frankfurt a. M.; BASF, Ludwigshafen a. Rh.; B. Müller, Weidenau; C. Canzler, Düren, und Deutsche Forschungsgemeinschaft, Bad Godesberg.Meinen beiden Mitarbeitern Dipl.-Ing. R. Baumann und Dipl.-Ing. W. Busch danke ich für ihre Unterstützung bei der Durchführung und Auswertung der Versuche. Ferner waren mit den Versuchen beschäftigt die Herren cand. chem. ing. Hunke Schwarze, Boger, Canzler, Hummel, Ernst u. George.
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  • 40
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Die Verfahrenstechnik benutzt vielfach Methoden der Vakuumtechnik als Hilfsmittel. Ein Hauptproblem bei Verfahren im Druckgebiet unter 10 Torr ist der Transport großer Gas- und Dampfvolumina. Es wird eine Apparatur beschrieben, mit der man unter Ausnutzung dieser Tatsache sehr kleine Gasgehalte in Flüssigkeiten bestimmen kann.
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  • 41
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Es wird eine Auswahl neuer Anwendungen beschrieben, die sich auf die Theorie der Flammenfortpflanzung, auf rheologische Flüssigkeiten, die Strömung geschmolzenen Glases in der Schmelzwanne, die Bewegung des flüssigen Stahls im Konverter, den Einfluß pulsierender Strömung auf die Kohfenstaubverbrennung und die Heizgasströmung bei Eckenfeuerung beziehen. Am Beispiel des Gesetzes von Avogadro und des Wienschen Verschiebungsgesetzes wird schließlich gezeigt, daß die Bedeutung der Ähnlichkeitstheorie wesentlich tiefer als nur in der Anwendung liegt.
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  • 42
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 51-55 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Additional Material: 5 Ill.
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  • 43
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Es wurde die Wärmeleitzahl verschiedener Flüssigkeiten in einer näher beschriebenen Apparatur untersucht, in der gleichzeitig ein hohes elektrisches Feld angelegt werden konnte. Es zeigte sich, daß das Wärmeleitvermögen unter dem Einfluß des Gleichspannungsfeldes auf das 2- bis 5fache des normalen Wertes ansteigt. Wie Schlierenaufnahmen beweisen, wird dieser mit steigender Temperatur zunehmende Effekt durch Konvektionsbewegungen der Flüssigkeiten hervorgerufen.
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  • 44
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 56-56 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
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  • 45
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 72-74 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Technische Kornverteilungen werden meist mit Hilfe der Rosin-Rammler-Sperling-Gleichung in einem doppelt-logarithmisch geteilten Körnungsnetz dargestellt. Im folgenden wird gezeigt, daß diese Verteilungsfunktion unter bestimmten Bedingungen auch Normalverteilungen erfaßt. Diese Tatsache erweitert den Anwendungsbereich der RRS-Gleichung und läßt manche Darstellungen im Körnungsnetz sinnfälliger deuten.
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  • 46
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 81-83 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Für elektrophoretische Trennungen von Substanzgemischen (Eiweißhydrolysaten, Gerbstoffgemischen) wurde ein Stromversorgungsgerät entwickelt, welches elektronisch - stabilisierte Gleichspannungen von 0 bis 1500 V liefert.
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  • 47
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Der Transport von Gasen und Dämpfen in Papier wird unter Verwendung einer Strömungsmethode untersucht. Die für die Luftdurchlässigkeit maßgebenden Faktoren können auf bekannte Gesetze zurückgeführt werden, so daß man die Durchlässigkeit für jedes permanente Gas aus einer Messung der Luftdurchlässigkeit für einen beliebigen mittleren Druck berechnen kann.  -  Der Wasserdampftransport in Papier und Folien kann, sofern er nicht nach den bekannten Gesetzen durch das freie Porenvolumen vonstatten geht, unter Berücksichtigung von Adsorptionsisothermen quantitativ erfaßt werden. Aus den theoretischen und experimentellen Untersuchungen folgt, daß das Oberflächenkonzentrationsgefälle sowie die Oberflächenkonzentration selbst von maßgeblichem Einfluß sind. Es wird damit die Möglichkeit aufgezeigt, Aussagen über die Wasserdampfdurchlässigkeit unter allen praktisch vorkommenden klimatischen Bedingungen zu machen.
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  • 48
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 97-100 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Außer der für die Selbstzündung von Gasen und Dämpfen maßgebenden Temperatur, dem „Gaszündpunkt“, findet man bei vielen brennbaren chemischen Substanzen noch einen  -  meist sehr viel niedriger liegenden  -  „Tropfzündpunkt“, bei dem sich die flüssige Phase der betreffenden Substanz beim Auftreffen auf eine heiße Fläche entzündet. Die Merkmale der beiden Zündpunkte werden einander gegenübergestellt und Folgerungen für explosionsgefährdete Räume gezogen; weiterhin wird eine empirische Formel für die Berechnung des Tropfzündpunktes in einzelnen chemischen Gruppen angegeben.
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  • 49
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 113-113 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
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  • 50
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 101-106 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
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  • 51
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 114-116 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
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  • 52
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 118-120 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
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  • 53
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    Chemie Ingenieur Technik - CIT 26 (1954) 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
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  • 54
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 129-131 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Es wird ein Verfahren und die zugehörige Apparatur für die kontinuierliche Kurzweg-Fraktionierung beschrieben. Die Apparatur ist aus kontinuierlich abgestuften Elementen der einfachen Destillation zusammengesetzt und hat als wesentlichsten Bestandteil eine Heizwanne mit einem Temperaturgradienten. Die Leistungsfähigkeit des Verfahrens wird am Beispiel eines Zweistoffgemisches mit einer gewöhnlichen Fraktionierung aus einem Claisenkolben verglichen.
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  • 55
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: An einigen Beispielen wird erläutert, wie man durch strömungstechnische Maßnahmen in Trocknern eine gleichmäßige Trocknung und geringe Verluste an Strömungsenergie erreichen kann. Ferner wird dargelegt, wie sich die Strömung vor und hinter Lüftern sowie in Querschnittsänderungen und Umlenkungen ordnen und lenken läßt, und wie man die Luft auf mehrere Kanäle genügend gleichmäßig verteilen kann.
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  • 56
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 157-163 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
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  • 57
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Es werden die Bedingungen für die Entstehung eines Quertriebs (Auftriebs), der von der Magnus-Kraft herrührt, beschrieben und zunächst an sedimentierenden Teilchenschüttungen verschiedener Größe und verschiedenen Materials geprüft. Dabei wird die Zahl der sedimentierenden Teilchen im wandnahen Bereich mit der im achsennahen Bereich verglichen. Es ergab sich eine Anreicherung der Teilchen im achsennahen Bereich bis zu 25%. Bei sedimentierenden Schüttungen mit Teilchen zweier Größenklassen reichern sich dagegen die größeren im Strömungsmaximum bis zu 40% an.Im II. Teil dieser Arbeit wird die Wirkung der Magnus - Kraft in strömenden Elektrolytlösungen und Gasgemischen erörtert.
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 163-168 
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    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 171-172 
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 175-176 
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 236-236 
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 237-238 
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 239-244 
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 259-264 
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    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Wenn man die Meßwerte für die reduzierte (d. h. auf den kritischen Zustand bezogene) Dichte aesättigter Flüssigkeiten in Abhängigkeit von der reduzierten Temperatur aufträgt, so erhält man, ähnlich wie beim Dampfdruck, keine einheitliche Kurve, wie es das Theorem der übereinstimmenden Zustände in der üblichen Fassung verlangt, sondern eine einparametrige Kurvenschar. Für diese wird eine der Erfahrung angepaßte Gleichung aufgestellt, die den auch für die Dampfdruckkurve maßgebenden „kritischen Parameter“ enthält. Durch Einführung der Nullpunktsdichte statt der kritischen Dichte ergibt sich eine vom kritischen Parameter weitgehend unabhängige Funktion, die tabellarisch wiedergegeben wird und deren Anwendungsmöglichkeiten diskutiert und an Hand von Zahlenbeispielen erläutert werden. Das auf den absoluten Nullpunkt extrapolierte Molvolumen zeigt bei Kohlenwasserstoffen präzise Zusammenhänge mit der Struktur der Molekeln. Zur Abschätzung des kritischen Volumens organischer Verbindungen wird eine Zusammenstellung der Meßwerte und ein System von Substitutionsinkrementen angegeben.
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 281-284 
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    Notes: Nach einer grundsätzlichen Betrachtung des Ausmauerungs-Problems werden allgemeine Formeln zur Ermittlung der Spannungen und Dehnungen angegeben, die in einer Kugelschale unter dem Einfluß des Druckes und eines Temperaturgefälles auftreten. Hieraus wird für den ausgemauerten, kugelförmigen Behälter eine Bedingung hergeleitet, deren Erfüllung gewährleistet, daß sich das Mauerwerk vom Eisenmantel nicht ablöst. Die Verwendung von quellendem Kitt bringt Vorteile. Abschließend werden die im Mauerwerk und im Eisenmantel auftretenden Spannungen ermittelt.
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    Notes: Im I. Teil wurde der Quertrieb in sedimentierenden Teilchenschüttungen untersucht. Nachfolgend wird gezeigt, daß auch in laminar strömenden wäßrigen Elektrolytlösungen ein Quertrieb entsteht, infolgedessen die größeren lonen bevorzugt in den Bereich höherer Strömungsgeschwindigkeit, also in den achsennahen Bereich diffundieren. Diese Versuche lassen Schlüsse auf die lonenhydratation zu. Außerdem wurde der Quertrieb in laminar strömender Luft mit sehr hoher Strömungsgeschwindigkeit, z. B. im Wirbelrohr, beobachtet. Auch dort ergibt sich für die größeren Molekeln eine Anreicherung im achsennahen Bereich, d. h. eine O2-Anreicherung im Kaltgasanteil. Abschließend werden die Ergebnisse in den einzelnen Aggregatzuständen miteinander verglichen.
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 287-289 
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 291-291 
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 349-349 
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 413-418 
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 425-428 
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 533-538 
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    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Für verschiedene Verfahren der chemischen Technik, insbesondere bei der Glasherstellung und in der Eisenindustrie, werden Werkstoffe gebraucht, die bei Temperaturen von etwa 1500 °C und darüber beständig sind. Hierfür kommen vor allem keramische Materialien in Betracht. Es werden daher im folgenden Baustoffe und Rohstoffe behandelt, welche zur Herstellung von Silica-, Sillimanit-, Korund-, Magnesit-, Chrommagnesit-, Dolomit-, Siliciumcarbid- und Zirkon-Steinen dienen. Anwendungsgrenzen, Wärmedehnung, Temperaturwechselbeständigkeit, Wärmeleitung und die chemische Beständigkeit dieser Materialien bei Temperaturen um 1500 °C werden besprochen.
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 548-554 
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    Notes: Es wird ein Überblick über die Eigenschaften und die Verwendungsmöglichkeiten von Kunststoff-Folien und kunststoffbeschichteten Papieren und Pappen als Verpackungswerkstoffe in der chemischen Industrie gegeben, wobei deren Vor- und Nachteile einander gegenübergestellt werden.
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 543-547 
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    Notes: Der Packstoffverbrauch entfällt zu einem großen Teil auf Aluminiumfolien, vor allem in der Nahrungsund Genußmittel-Industrie. In der chemischen und pharmazeutischen Industrie dagegen ist er verhältnismäßig gering. Im folgenden wird ein Überblick über die für Verpackungszwecke wichtigen Eigenschaften von Aluminiumfolien gegeben unter besonderer Berücksichtigung der Möglichkeiten zu ihrer Veredelung.
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 555-561 
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    Notes: Die Badische Anilin- & Soda-Fabrik A.G. hat gemeinsam mit der Firma Dr. F. Raschig GmbH., Ludwigshafen am Rhein, für die chemische Technik den neuen Werkstoff BascodurEingetragenes Warenzeichen der BASF. entwickelt, der geeignet ist, Lücken innerhalb der heute bekannten nichtmetallischen Apparatebaustoffe zu schließen. Nach kurzen Angaben über Eigenschaften und Verarbeitung des Materials werden an Hand zahlreicher Bilder insbesondere Anwendungsbeispiele aus dem chemischen Apparatebau besprochen.
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 568-575 
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 643-643 
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 647-648 
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 667-669 
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    Notes: Im In- und Ausland nimmt die Anwendung dimensionsloser Kennzahlen auf dem Gebiet der Wärmeübertragung immer mehr zu. Diese Entwicklung läßt sich nicht durch den Einwand aufhalten, daß dimensionslose Darstellungen unanschaulich seien, denn in Wirklichkeit lassen sich alle wichtigen Kennzahlen als Verhältnisse gleichartiger Größen in anschaulicher Form darstellen und bei der Berechnung von Wärmeübertragern verwenden.
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    Notes: Das Problem der automatischen Zählung und Größenanalyse mikroskopischer Teilchen wird besonders in den USA und England seit einigen Jahren intensiv bearbeitet, während in Deutschland auf diesem Gebiet praktisch noch kein Schrifttum vorliegt. Es sollen deshalb hier der Stand der Entwicklung und die bekanntgewordenen Geräte diskutiert werden. Allen beschriebenen Methoden ist das Ziel gemeinsam, jedes Teilchen einzeln zu messen und zu zählen. Dies führt zwangsläufig zu elektronischen Mitteln, da nur diese hinreichende Zählgeschwindigkeiten ermöglichen. -  Im ersten Teil der Arbeit werden Verfahren zur automatischen Größenanalyse von Aerosolen behandeit, während im zweiten Teil automatische Methoden zur Auszählung von mikroskopischen Präparaten und Mikrophotographien beschrieben werden.
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 673-676 
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    Notes: Nachdem im ersten Teil das Anheizen flüssigkeitsgefüllter Behälter behandelt wurde, werden nun der Temperaturverlauf und die Wärmeverluste beim Abkühlen derartiger Behälter berechnet. Dabei wird sowohl der Abkühlungsvorgang aus dem stationären Zustand heraus behandelt als auch der Fall, daß vor Erreichen des stationären Zustands die Wärmezufuhr im Innern des Behälters aufhört. Die Resultate für den Abkühlungsvorgang lassen sich ohne neue Schwierigkeiten aus den schon in Teil I gewonnenen Ergebnissen für das Anheizen herleiten. Es wird ferner das Anheizen und die Abkühlung gasgefüllter Behälter untersucht. Zwei Beispiele zeigen die Anwendung der gewonnenen Gleichungen und der daraus entwickelten Diagramme.
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 1-1 
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    Notes: Aus umfangreichen Untersuchungen an den verschiedensten Trocknertypen1 wird in dieser Arbeit über die Ergebnisse berichtet, die an Tunnel-, Mulden- sowie Stromtrocknern erhalten wurden. Die Versuche hatten den Zweck, rechnerische Unterlagen für den Entwurf der Trockner zu schaffen.
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 14-18 
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    Notes: Die Erzeugung der technisch wichtigen spezifischen Oberflächen am Beispiel von Quarzsand bei fort-schreitender Schwingmahlung wird in weitem Feinheitsbereich verfolgt; die jeweils aus Siebanalyse bzw. Körnungsnetz erhaltenen idealisierten Oberflächen und die Oberflächen nach dem Blaine-Test werden mit der zunächst physikalish am besten definierten Oberfläche nach der Argon-Adsorptionsmethode verglichen und wesentliche zerkleinerungsphysikalische Folgerungen gezogen sowie Bewertungsfragen beantwortet.
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    Notes: In der Verfahrenstechnik sind häufig Prozesse durchzuführen, bei denen Mehrstoffgemische mit einer flüssigen oder gasförmigen Phase behandelt werden müssen. Die bei diesen Verfahren auftretenden strömungstechnischen Probleme sind bisher von der klassischen Strömungslehre nur sehr wenig erörtert worden. Die folgenden Ausführungen zeigen, wie auf diesem Gebiete durch Anwendung strömungstechnischer Methoden praktisch wichtige Erkenntnisse gewonnen werden können.
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    Notes: Beschrieben werden ein Verfahren sowie eine Meßanordnung, mit denen die Wämeleitfähigkeit λ, die Wärmekapazität cλ und die Wärmeeindringzahl \documentclass{article}\pagestyle{empty}\begin{document}$\sqrt {\lambda c\gamma } $\end{document} in einem Kurzversuch gleichzettig bestimmt werden können.
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 44-51 
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    Notes: In einer Versuchsanlage wurden Wärmeübergang und Druckabfall verschiedener Speichermassen gemessen. Auf Grund dieser und früherer Versuche wurden Heizflächenbedarf und Heizflächenkosten unter gleichen energetischen Bedingungen für längs durchströmte Rohre verschiedenen Durchmessers, Kugelschüttungen, Raschig-Ringfüllungen sowie Riffeleinsätze ermittelt. Am Beispiel der Regeneratoren von Linde-Fränkl-Anlagen werden die Vorteile gegenüber Röhren-Wärmeaustauschern diskutiert. Die Versuche sind noch nicht abgeschlossen.
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 59-60 
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    Chemie Ingenieur Technik - CIT 26 (1954), S. 57-57 
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    Notes: Chemie und Hüttenkunde sind keine getrennten Forschungsgebiete. Lediglich ihre äußere und industrielle Geschichte führte zu zwei verschiedenen Bezeichnungen, die auch heute noch beibehalten werden. In Wirklichkeit aber überschneiden sich gerade in den letzten Jahrzehnten die beiden Wissenschaftszweige in zunehmendem Maße. Der Einfluß der reinen Chemie auf die Hüttenkunde wird an vielen Beispielen erläutert.
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    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Nachdem bereits über das Grundprinzip des Sorbogen-I-Verfahens berichtet wurde, soll hier seine Anwendung bei der Abscheidung von Wasser, Kohlendioxyd und Acetylen aus zu zerlegender Luft in einer Reinigungsanlage beschrieben werden. Die Anlage arbeitet mit Aktivkohle als Adsorbens bei Normaltemperatur und mäßig erhöhtem Druck und bildet den vorgeschalteten Teil einer Luftzerlegungsanlage. Das Verfahren bietet gegenüber älteren Anlagen wirtschaftliche Vorteile. Es wird ein Reinheitsgrad von einigen Hundertstel pM (1 pM = 1 ċ 10-4%) Kohlendioxyd und eine völlige Entfernung von Acetylen und Wasserdampf ohne zusätzlichen Energieaufwand erreicht.
    Additional Material: 2 Ill.
    Type of Medium: Electronic Resource
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  • 99
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Nach dem Theorem der übereinstimmenden Zustände sollten die reduzierten Dampfdruckkurven verschiedener nicht assoziierter Stoffe zusammenfallen. Tatsächlich bilden sie jedoch in guter Näherung eine einparametrige Kurvenschar. Durch Einführung eines stoffspezifischen „kritischen Parameters“ gelingt es, eine die Meßwerte befriedigend darstellende Gleichung dieser Kurvenschar zu entwickeln, mit deren Hilfe man die ganze Dampfdruckkurve einer Substanz berechnen kann, wenn der kritische Punkt und der normale Siedepunkt bekannt sind. Kennt man aus Messungen den Dampfdruck bei zwei beliebigen Temperaturen, so läßt sich auch der kritische Druck mit einiger Zuverlässigkeit abschätzen. Zur Erleichterung der Anwendung werden die in der Gleichung auftretenden Temperaturfunktionen tabellarisch wiedergegeben. An verschiedenen Beispielen wird die Brauchbarkeit der neuen Dampfdruckformel gezeigt.
    Additional Material: 4 Ill.
    Type of Medium: Electronic Resource
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  • 100
    Electronic Resource
    Electronic Resource
    Weinheim : Wiley-Blackwell
    Chemie Ingenieur Technik - CIT 26 (1954), S. 94-96 
    ISSN: 0009-286X
    Keywords: Chemistry ; Industrial Chemistry
    Source: Wiley InterScience Backfile Collection 1832-2000
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Notes: Die konstruktiven Voraussetzungen für Laboratoriumszentrifugen mit bisher in der Praxis nicht erreichbaren Fliehkräften werden dargelegt. Das entwickelte Gerät, das im Gegensatz zu anderen Bauarten nur eine einzige radial um die Drehachse rotierende Zelle für die Einsatzflüssigkeit besitzt, wird beschrieben. Es ermöglicht bei 84 000 U/min Normalbeschleunigungen von 584 000 g, bei 120 000 U/min und kleineren Präparatmengen von 915 000 g. Besondere Einsätze zur Erfassung des Sediments bringen bei präparativen und möglicherweise auch analytischen Arbeiten besondere Vorteile.
    Additional Material: 3 Ill.
    Type of Medium: Electronic Resource
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