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  • AERODYNAMICS
  • Aerodynamics
  • Animals
  • 2020-2024  (16)
  • 1955-1959  (239)
  • 1940-1944  (77)
  • 1925-1929
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  • 1
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    University of Calgary Press
    Publication Date: 2022-07-19
    Description: How have our interactions with animals shaped Calgary? What can we do to ensure that humans and animals in the city continue to co-exist, and even flourish together? This wide-ranging book explores the ways that animals inhabit our city, our lives and our imaginations. Essays from animal historians, wildlife specialists, artists and writers address key issues such as human-wildlife interactions, livestock in the city, and animal performers at the Calgary Stampede. Contributions from some of Calgary's iconic arts institutions, including One Yellow Rabbit Performance Theatre, Decidedly Jazz Danceworks, and the Glenbow Museum, demonstrate how animals continue to be a source of inspiration and exploration for fashion, art, dance, and theatre. The full-colour volume is beautifully illustrated throughout with archival images, wildlife photography, documentary and production stills, and original artwork. Calgary: City of Animals is published in co-operation with the Calgary Institute for the Humanities.
    Keywords: Nature ; Animals ; bic Book Industry Communication::J Society & social sciences::JF Society & culture: general::JFF Social issues & processes::JFFZ Animals & society
    Language: English
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  • 2
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    transcript Verlag | transcript Verlag
    Publication Date: 2024-03-28
    Description: Wie werden Natur und Tiere durch die Multispezies-Ethnographie inklusiv in Forschungsprojekte integriert? Katharina Ameli fokussiert die inter- und multidisziplinäre Zusammenarbeit. Aus einer Untersuchung der Schnittstellen zwischen gesellschafts- und naturwissenschaftlich orientierten Fachdisziplinen ergibt sich eine komplexe Betrachtung von Natur, Mensch und Tier. Die Einblicke in Interdependenzen unterschiedlicher Fachdisziplinen verdeutlichen den Bedarf an einer Multispezies-Ethnographie zur Analyse von MenschenTiereNaturenKulturen.
    Keywords: Natur ; Mensch ; Tiere ; Naturverständnis ; Interdisziplinarität ; Qualitative Forschung ; Kultur ; Ethnographie ; Umwelt ; Tier ; Human-animal Studies ; Umweltsoziologie ; Kulturanthropologie ; Kultursoziologie ; Kulturwissenschaft ; Nature ; Human ; Animals ; Understanding of Nature ; Interdisciplinarity ; Qualitative Research ; Culture ; Ethnography ; Environment ; Animal ; Environmental Sociology ; Cultural Anthropology ; Sociology of Culture ; Cultural Studies ; thema EDItEUR::J Society and Social Sciences::JB Society and culture: general::JBF Social and ethical issues::JBFU Animals and society ; thema EDItEUR::R Earth Sciences, Geography, Environment, Planning::RN The environment::RNT Social impact of environmental issues ; thema EDItEUR::J Society and Social Sciences::JH Sociology and anthropology::JHM Anthropology::JHMC Social and cultural anthropology
    Language: German
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  • 3
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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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  • 4
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    University of Calgary Press
    Publication Date: 2022-07-19
    Description: Animal Metropolis brings a Canadian perspective to the growing field of animal history, ranging across species and cities, from the beavers who engineered Stanley Park to the carthorses who shaped the city of Montreal. Some essays consider animals as spectacle: orca captivity in Vancouver, polar bear tourism in Churchill, Manitoba, fish on display in the Dominion Fisheries Museum, and the racialized memory of Jumbo the elephant in St. Thomas, Ontario. Others examine the bodily intimacies of shared urban spaces: the regulation of rabid dogs in Banff, the maternal politics of pure milk in Hamilton and the circulation of tetanus bacilli from horse to human in Toronto. Another considers the marginalization of women in Canada’s animal welfare movement. The authors collectively push forward from a historiography that features nonhuman animals as objects within human-centered inquiries to a historiography that considers the eclectic contacts, exchanges, and cohabitation of human and nonhuman animals. With contributions by: Kristoffer Archibald, Jason Colby, George Colpitts, Joanna Dean, Carla Hustak, Darcy Ingram, Sean Kheraj, William Knight, Sherry Olson, Rachel Poliquin, and Christabelle Sethna
    Keywords: Animals ; Anthropology ; Environmental Science ; History ; bic Book Industry Communication::J Society & social sciences::JH Sociology & anthropology::JHM Anthropology ; bic Book Industry Communication::H Humanities::HB History ; bic Book Industry Communication::K Economics, finance, business & management::KC Economics::KCN Environmental economics ; bic Book Industry Communication::J Society & social sciences::JF Society & culture: general::JFF Social issues & processes::JFFZ Animals & society
    Language: English
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  • 5
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    University Press of Colorado | University Press of Colorado
    Publication Date: 2024-04-02
    Description: Animals and Inequality in the Ancient World explores the current trends in the social archaeology of human-animal relationships, focusing on the ways in which animals are used to structure, create, support, and even deconstruct social inequalities. The authors provide a global range of case studies from both New and Old World archaeology—royal Aztec dog burial, the monumental horse tombs of Central Asia, and the ceremonial macaw cages of ancient Mexico among them. They explore the complex relationships between people and animals in social, economic, political, and ritual contexts, incorporating animal remains from archaeological sites with artifacts, texts, and iconography to develop their interpretations. Animals and Inequality in the Ancient World presents new data and interpretations that reveal the role of animals, their products, and their symbolism in structuring social inequalities in the ancient world. The volume will be of interest to archaeologists, especially zooarchaeologists, and classical scholars of pre-modern civilizations and societies.  Contributors: Alejandra Aguirre Molina, Benjamin S. Arbuckle, Levent Atici, Douglas V. Campana, Roderick Campbell, Ximena Chá­vez Balderas, Pam J. Crabtree, Susan D. deFrance, Kitty F. Emery, Abigail Holeman, H. Edwin Jackson, Leonardo López Lujá­n, Michael MacKinnon, Arkadiusz Marciniak, Sue Ann McCarty, Neil L. Norman, Gilberto Perez, Bernardo Rodriguez, William A. Saturno, Ashley E. Sharpe, Nawa Sugiyama, Charlotte K. Sunseri, Naomi Sykes, Fabiola Torres, Raul Valadez, Norma Valentin Maldonado, Adam S. Watson, Joshua Wright, Belem Zuniga-Arelleno
    Keywords: History ; Ancient ; Social Science ; Archaeology ; Nature ; Animals ; thema EDItEUR::N History and Archaeology::NH History::NHC Ancient history ; thema EDItEUR::N History and Archaeology::NK Archaeology ; thema EDItEUR::W Lifestyle, Hobbies and Leisure::WN Nature and the natural world: general interest::WNC Wildlife: general interest
    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: 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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  • 8
    Publication Date: 2024-04-05
    Description: Neurodegenerative diseases are the most frequent cause of dementia, representing a burden for public health systems (especially in middle and middle-high income countries). Although most research on this issue is concentrated in first-world centers, growing efforts in South America are affording important breakthroughs. This emerging agenda poses new challenges for the region but also new opportunities for the field. This book aims to integrate the community of experts across the globe and the region, and to establish new challenges and developments for future investigation. We present research focused on neurodegenerative research in South America. We introduce studies assessing the interplay among genetic, neural, and behavioral dimensions of these diseases, as well as articles on vulnerability factors, comparisons of findings from various countries, and works promoting multicenter and collaborative networking. More generally, our book covers a broad scope of human-research approaches (behavioral assessment, neuroimaging, electromagnetic techniques, brain connectivity, peripheral measures), animal methodologies (genetics, epigenetics, proteomics, metabolomics, other molecular biology tools), species (all human and non-human animals, sporadic, and genetic versions), and article types (original research, review, and opinion papers). Through this wide-ranging proposal, we hope to introduce a fresh approach to the challenges and opportunities of research on neurodegeneration in South America.
    Keywords: RC321-571 ; Q1-390 ; South America ; Multicenter research ; Neurodegenerative Diseases ; Neurosciences ; Public Health ; Animals ; Clinical Protocols ; Research ; Human Experimentation ; Dementia ; thema EDItEUR::P Mathematics and Science::PS Biology, life sciences::PSA Life sciences: general issues::PSAN Neurosciences
    Language: English
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  • 9
    Publication Date: 2024-04-04
    Description: This eBook is a collection of articles from a Frontiers Research Topic. Frontiers Research Topics are very popular trademarks of the Frontiers Journals Series: they are collections of at least ten articles, all centered on a particular subject. With their unique mix of varied contributions from Original Research to Review Articles, Frontiers Research Topics unify the most influential researchers, the latest key findings and historical advances in a hot research area! Find out more on how to host your own Frontiers Research Topic or contribute to one as an author by contacting the Frontiers Editorial Office: frontiersin.org/about/contact
    Keywords: drugs ; Behavior ; Memory tasks ; pre-clinical ; clinical ; Humans ; Animals ; thema EDItEUR::P Mathematics and Science::PD Science: general issues ; thema EDItEUR::M Medicine and Nursing::MK Medical specialties, branches of medicine::MKG Pharmacology
    Language: English
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  • 10
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    Berghahn Books | Berghahn Books
    Publication Date: 2023-02-02
    Description: Employing methodological perspectives from the fields of political geography, environmental studies, anthropology, and their cognate disciplines, this volume explores alternative logics of sentient landscapes as racist, xenophobic, and right-wing. While the field of sentient landscapes has gained critical attention, the literature rarely seems to question the intentionality of sentient landscapes, which are often romanticized as pure, good, and just, and perceived as protectors of those who are powerless, indigenous, and colonized. The book takes a new stance on sentient landscapes with the intention of dispelling the denial of “coevalness” represented by their scholarly romanticization.
    Keywords: Social Science ; Sociology ; Rural ; Nature ; Animals ; Social Science ; Anthropology ; Cultural & Social ; bic Book Industry Communication::J Society & social sciences::JF Society & culture: general::JFS Social groups::JFSF Rural communities ; bic Book Industry Communication::W Lifestyle, sport & leisure::WN Natural history::WNC Wildlife: general interest ; bic Book Industry Communication::J Society & social sciences::JH Sociology & anthropology::JHM Anthropology::JHMC Social & cultural anthropology, ethnography
    Language: English
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  • 11
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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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  • 12
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    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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  • 13
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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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  • 14
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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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  • 15
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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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  • 16
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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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  • 17
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    In:  CASI
    Publication Date: 2006-10-26
    Keywords: AERODYNAMICS
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  • 18
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    In:  CASI
    Publication Date: 2006-10-26
    Keywords: AERODYNAMICS
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  • 19
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    In:  CASI
    Publication Date: 2006-10-26
    Keywords: AERODYNAMICS
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  • 20
    Publication Date: 2006-03-16
    Keywords: AERODYNAMICS
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  • 21
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    In:  Other Sources
    Publication Date: 2011-08-10
    Keywords: AERODYNAMICS
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  • 22
    Publication Date: 2012-05-11
    Keywords: AERODYNAMICS
    Type: RM-2419-NASA , RM-2419-NASA
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  • 23
    Publication Date: 2011-08-18
    Keywords: AERODYNAMICS
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  • 24
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    In:  CASI
    Publication Date: 2016-06-07
    Description: A simple, systematic, optimized vortex-lattice approach is developed for application to lifting-surface problems. It affords a significant reduction in computational costs when compared to current methods. Extensive numerical experiments have been carried out on a wide variety of configurations, including wings with camber and single or multiple flaps, as well as high-lift jetflap systems. Rapid convergence as the number of spanwise or chordwise lattices are increased is assured, along with accurate answers. The results from this model should be useful not only in preliminary aircraft design but also, for example, as input for wake vortex roll-up studies and transonic flow calculations.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Vortex-Lattice Utilization; p 325-342
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  • 25
    Publication Date: 2018-06-05
    Description: As part of the program of flight tests of airplane propellers to determine compressibility effects at high speeds, preliminary flights have been made with a conventional three-blade propeller (Hamilton Standard 3155-6) on a Bell YP-39 airplane. This preliminary report presents the high-speed data obtained thus far with a brief analysis of the results.
    Keywords: Aerodynamics
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  • 26
    Publication Date: 2019-05-31
    Description: A 1/13-scale model of the forebody of the Republic F-105 with twin-duct wing-root inlets was tested in the Langley 4- by 4-foot supersonic pressure tunnel through a range of angle of attack from -4 deg to 15 deg at a Mach number of 2.01 and a Reynolds number of approximately 3.4 x 10(exp 6) per foot. The tests were made with four configurations which incorporated varying amounts of sweep and stagger of the inlet leading edges, modifications to the areas of the boundary-layer diverter floor plate, and modifications to the area of the boundary-layer diverter bleed slots. The highest overall pressure recovery at an angle of attack of 0 deg (average total-pressure recovery, 0.84 mass-flow ratio, 0.98) was achieved with configuration having an inlet leading-edge sweep angle of 58 deg with no leading-edge stagger. Stagger was found to improve the angle-of- attack performance, but at a sacrifice in inlet efficiency for an angle of attack of 0 deg. The boundary-layer diverter floor height, of the order of one boundary-layer thickness, was satisfactory for bypassing the fuselage boundary layer. The boundary-layer diverter-plate bleed slots were effective in increasing the total-pressure recovery of the inlet. The total-pressure-recovery contour plots, taken at the compressor-face station, indicate the existence of high-velocity "cores" throughout the inlet operating range.
    Keywords: Aerodynamics
    Type: NACA-RM-SL56L12
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  • 27
    Publication Date: 2019-05-30
    Description: Flow spoiler and aerodynamic balance effects on oscillating hinge moments for swept fin-rudder combination in transonic wind tunnel
    Keywords: AERODYNAMICS
    Type: NACA-RM-L58C28
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  • 28
    Publication Date: 2019-05-11
    Description: A design guide is suggested as a basis for indicating combinations of airplane design variables for which the possibilities of pitch-up are minimized for tail-behind-wing and tailless airplane configurations. The guide specifies wing plan forms that would be expected to show increased tail-off stability with increasing lift and plan forms that show decreased tail-off stability with increasing lift. Boundaries indicating tail-behind-wing positions that should be considered along with given tail-off characteristics also are suggested. An investigation of one possible limitation of the guide with respect to the effects of wing-aspect-ratio variations on the contribution to stability of a high tail has been made in the Langley high-speed 7- by 10-foot tunnel through a Mach number range from 0.60 to 0.92. The measured pitching-moment characteristics were found to be consistent with those of the design guide through the lift range for aspect ratios from 3.0 to 2.0. However, a configuration with an aspect ratio of 1.55 failed t o provide the predicted pitch-up warning characterized by sharply increasing stability at the high lifts following the initial stall before pitching up. Thus, it appears that the design guide presented herein might not be applicable when the wing aspect ratios lower than about 2.0.
    Keywords: Aerodynamics
    Type: NASA-TM-X-26
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  • 29
    Publication Date: 2019-05-24
    Description: Movable tail surface for aircraft control without flutter using X-15 scale model at hypersonic speed
    Keywords: AERODYNAMICS
    Type: NACA-RM-L58B27
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  • 30
    Publication Date: 2019-05-24
    Description: An investigation has been made at Mach numbers of 1.61 and 2.01 and Reynolds numbers of 1.7 x l0(exp 6) and 3.6 x l0(exp 6) to determine the pressure distributions over a swept wing with a series of 14 control configurations. The wing had 40 deg of sweep of the quarter-chord line, an aspect ratio of 3.1, and a taper ratio of 0.4. Measurements were made at angles of attack from 0 deg to +/- 15 deg for control deflections from -60 deg to 60 deg. This report contains tabulated pressure data for the complete range of test conditions.
    Keywords: AERODYNAMICS
    Type: NACA-RM-L57H30
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  • 31
    Publication Date: 2019-05-23
    Description: Factors affecting static, longitudinal, and directional stability characteristics of supersonic aircraft configurations
    Keywords: AERODYNAMICS
    Type: NACA-RM-L57E24A
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  • 32
    Publication Date: 2019-05-23
    Description: Supersonic wind tunnel test of underslung scoop inlet on body of revolution
    Keywords: AERODYNAMICS
    Type: NACA-RM-E56L11
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  • 33
    Publication Date: 2019-05-23
    Description: Wind tunnel data of X-15 and B-52 aircraft models carry loads and mutual interference
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-184
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  • 34
    Publication Date: 2019-05-23
    Description: Supersonic wind tunnel test of twin-duct variable geometry side inlets
    Keywords: AERODYNAMICS
    Type: NACA-RM-E56K15
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  • 35
    Publication Date: 2019-05-23
    Description: Performance test data for pressure distributions over 60 deg delta wing at Mach 1.61 and 2.01
    Keywords: AERODYNAMICS
    Type: NACA-RM-L55L05
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  • 36
    Publication Date: 2019-05-23
    Description: Wind tunnel tests - effect of wind induced loads on dynamically scaled model of large missile in launching position
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-109
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  • 37
    Publication Date: 2019-05-23
    Description: An investigation of the aerodynamic characteristics of several hypersonic missile configurations with various canard controls for an angle-of-attack range from 0 deg to about 28 deg at sideslip angles of about 0 deg and 4 deg at a Mach number of 2.01 has been made in the Langley 4- by 4-foot supersonic pressure tunnel. The configurations tested we re a body alone which had a ratio of length to diameter of 10, the b ody with a 10 deg flare, the body with cruciform fins of 5 deg or 15 deg apex angle, and a flare-stabilized rocket model with a modified Von Karman nose. Various canard surfaces for pitch control only were te sted on the body with the 10 deg flare and on the body with both sets of fins. The results indicated that the addition of a flared afterbody or cruciform fins produced configurations which were longitudinally and directionally stable. The body with 5 deg fins should be capable of producing higher normal accelerations than the flared body. A l l of the canard surfaces were effective longitudinal controls which produced net positive increments of normal force and pitching moments which progressively decreased with increasing angle of attack.
    Keywords: AERODYNAMICS
    Type: NACA-RM-L58A21
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  • 38
    Publication Date: 2019-05-23
    Description: Internal aerodynamics and performance of clustered jet-exit installations at transonic speeds
    Keywords: AERODYNAMICS
    Type: NACA-RM-L58E01
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  • 39
    Publication Date: 2019-05-23
    Description: An experimental investigation was conducted to determine the performance characteristics an underslung nose-scoop air-induction system for a supersonic airplane. Five different nose shapes, three lip shapes, and two internal diffusers were investigated. Tests were made at Mach numbers from 0 to 1.9, angles of attack from 0 deg to approximately l5 deg, and mass-flow ratios from 0 to maximum obtainable. It was found that the underslung nose-scoop inlet was able to operate at Mach numbers from 0.6 to 1.9 over a large positive angle-of-attack range without adverse effects on the pressure recovery. Although there was no one inlet configuration that was markedly superior over the entire range of operating variables, the arrangement having a nose designed to give increased supersonic compression at low angles of attack, and a sharp lip (configuration designated N3L3) showed the most favorable performance characteristics over the supersonic Mach number range. Inlets with sizable lip radii gave satisfactory performance up to a Mach number of 1.5; however, as a result of an increase in drag, the performance of such inlets was markedly inferior to the sharp-lip configuration above Mach numbers of 1.5. Throughout the range of test Mach numbers all inlet configurations evidenced stable air-flow characteristics over the mass-flow range for normal engine operation. Analysis of the inlet performance on the basis of a propulsive thrust parameter showed that a fixed inlet area could be used for Mach numbers up to 1.5 with only a small sacrifice in performance.
    Keywords: AERODYNAMICS
    Type: NACA-RM-A55G13
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  • 40
    Publication Date: 2019-05-23
    Description: High subsonic speed of static longitudinal aerodynamic characteristics of delta wing configuration for angle of attack from 0 deg to 90 deg
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-168
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  • 41
    Publication Date: 2019-05-23
    Description: Stability and control of variable sweep wing configuration with outboard wing panels swept back 75 degrees at Mach 2.01
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-32
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  • 42
    Publication Date: 2019-05-23
    Description: Zero angle of attack performance of isentropic spike inlet designed for maximum external compression at hypersonic speed
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-4
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  • 43
    Publication Date: 2019-06-28
    Description: An investigation of some aspects of the sonic boom has been made with the aid of wind-tunnel measurements of the pressure distributions about bodies of various shapes. The tests were made in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 2.01 and at a Reynolds number per foot of 2.5 x 10(exp 6). Measurements of the pressure field were made at orifices in the surface of a boundary-layer bypass plate. The models which represented both fuselage and wing types of thickness distributions were small enough to allow measurements as far away as 8 body lengths or 64 chords. The results are compared with estimates made using existing theory. To the first order, the boom-producing pressure rise across the bow shock is dependent on the longitudinal development of body area and not on local details. Nonaxisymmetrical shapes may be replaced by equivalent bodies of revolution to obtain satisfactory theoretical estimates of the far-field pressures.
    Keywords: Aerodynamics
    Type: NASA-TN-D-161
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  • 44
    Publication Date: 2019-06-28
    Description: Time histories of noise pressures near ground level were measured during flight tests of fighter-type airplanes over fairly flat, partly wooded terrain in the e Mach number range between 1.13 and 1.4 and at altitudes from 25,000 to 45,000 feet. Atmospheric soundings and radar tracking studies were made for correlation with the measured noise data. The measured and calculated values of the pressure rise across the shock wave were generally in good agreement. There is a tendency for the theory to overestimate the pressure at locations remote from the track and to underestimate the pressures for conditions of high tailwind at altitude. The measured values of ground-reflection factor averaged about 1.8 f or the surface tested as compared to a theoretical value of 2.0. P o booms were measured in all cases. The observers also generally reported two booms; although, in some cases, only one boom was reported. The shock-wave noise associated with some of the flight tests was judged to be objectionable by ground observers, and in one case the cracking of a plate-glass store window was correlated in time with the passage of the airplane at an altitude of 25,000 feet.
    Keywords: Aerodynamics
    Type: NASA-TN-D-48
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  • 45
    Publication Date: 2019-05-29
    Description: Supersonic pressure distributions for tip and trailing edge controls on 60 deg delta wing
    Keywords: AERODYNAMICS
    Type: NACA-RM-L58C07
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  • 46
    Publication Date: 2019-05-29
    Description: Wind tunnel investigations of effect on static stability of modifications to swept wing fighter aircraft model
    Keywords: AERODYNAMICS
    Type: NACA-RM-L57A31
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  • 47
    Publication Date: 2019-05-29
    Description: Translating spike inlet air flow regulation characteristics from transonic to supersonic speeds at zero angle of attack
    Keywords: AERODYNAMICS
    Type: NACA-RM-E56D23B
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  • 48
    Publication Date: 2019-05-29
    Description: Longitudinal and lateral stability and control characteristics of swept wing fighter aircraft
    Keywords: AERODYNAMICS
    Type: NACA-RM-L56K19
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  • 49
    Publication Date: 2019-05-29
    Description: Pressure distribution at supersonic speeds on conically cambered wing with and without pylon mounted engine nacelles
    Keywords: AERODYNAMICS
    Type: NACA-RM-A56B03
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  • 50
    Publication Date: 2019-05-29
    Description: Transonic wind tunnel study of aerodynamic characteristics of blunt reentry vehicles at varying angles of attack
    Keywords: AERODYNAMICS
    Type: NASA-MEMO-1-21-59L
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  • 51
    Publication Date: 2019-05-29
    Description: Effects of conical camber for triangular wing- body-tail combinations on aerodynamic characteristics
    Keywords: AERODYNAMICS
    Type: NACA-RM-A57A10
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  • 52
    Publication Date: 2019-05-29
    Description: Horizontal tail flutter in fighter aircraft at transonic speeds
    Keywords: AERODYNAMICS
    Type: NACA-RM-L57K13
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  • 53
    Publication Date: 2019-05-29
    Description: Aerodynamic interference effects on effectiveness of aircraft vertical tail at supersonic speeds
    Keywords: AERODYNAMICS
    Type: NACA-RM-A55H30
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  • 54
    Publication Date: 2019-05-29
    Description: Comparisons are made of experimental and theoretical zero-lift wave drag for several nose shapes, wing-body combinations, and models of current airplanes at Mach numbers up to 1.0. The experimental data were obtained from tests in the Ames 6- by6-foot supersonic wind tunnel and at the NACA Wallops Island facility. The theoretical drag was found by use of linear theory utilizing model area distributions. The agreement between theoretical and experimental zero-lift wave-drag coefficients was generally very good, especially for a fuselage or for fuselage-wing combinations that were vertically symmetrical. For other models that had rapid changes in body shape and/or were not vertically symmetrical, the agreement of theory with experiment ranged from fair to poor, depending on the severity of the change in shape.
    Keywords: AERODYNAMICS
    Type: NACA-RM-A56I07
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  • 55
    Publication Date: 2019-05-29
    Description: A brief investigation of the longitudinal stability and control effectiveness at supersonic speeds of a model of a low-wing missile with interdigitated tail surfaces was made in the Langley Unitary Plan wind tunnel. The data were obtained at Mach numbers M of 2.29, 2.97, and 3.51 for Reynolds number (based on the mean geometric chord of the wing) of 1.15 x 10(exp 6), 1.14 x 10(exp 6), and 1.11 x 10(exp 6), respectively. Data were obtained for three settings of the longitudinal control surfaces: with deflection of all surfaces, with deflection of the lower surfaces only, and with all surfaces undeflected. Directional stability data were obtained at M=3.51 for angles of attack of approximately 0 deg and 10 deg. These data, with summary data and typical schlieren photographs, are presented with only a brief analysis. The data indicate that the controls are effective throughout the Mach number range and lift-coefficient range (CL = -0.15 to 0.7, approximately) of the tests. There is a severe break in the pitching-moment curve at M=2.29 which might result in a pitch-up condition in flight, and also a large forward movement of the aerodynamic center with increasing Mach number that produces neutral longitudinal stability at M=3.51 for the moment center used in this investigation. The model was directionally unstable at M=3.51; however, the level of directional stability was about the same for 0 deg and 10 deg angles of attack.
    Keywords: AERODYNAMICS
    Type: NACA-RM-L58C19
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  • 56
    Publication Date: 2019-05-29
    Description: Static force and interference drag on externally carried bomb in flow field of supersonic, swept wing fighter-bomber aircraft
    Keywords: AERODYNAMICS
    Type: NACA-RM-L56K30
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  • 57
    Publication Date: 2019-05-29
    Description: Wind tunnel testing of two and four engine models of delta wing aircraft for transonic drag rise increment and maximum lift-drag ratio comparison
    Keywords: AERODYNAMICS
    Type: NACA-RM-L55I27B
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  • 58
    Publication Date: 2019-05-29
    Description: Effects of boattail area contouring and simulated turbojet exhaust on loading and fuselage-tail component drag of twin-engine fighter-type airplane model
    Keywords: AERODYNAMICS
    Type: NACA-RM-L58C04
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  • 59
    Publication Date: 2019-05-29
    Description: Wind tunnel tests to determine lateral-directional stability of aircraft from transonic to supersonic speeds
    Keywords: AERODYNAMICS
    Type: NACA-RM-A55J03
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  • 60
    Publication Date: 2019-05-30
    Description: Wing-body combinations with wings of very low aspect ratio at supersonic speeds
    Keywords: AERODYNAMICS
    Type: NACA-RM-A56G16
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  • 61
    Publication Date: 2019-05-30
    Description: Performance characteristics of underslung vertical wedge inlet with porous suction at Mach numbers of 0.63 and 1.5 to 2.0
    Keywords: AERODYNAMICS
    Type: NACA-RM-E56B15
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  • 62
    Publication Date: 2019-05-30
    Description: Hypersonic flutter tests on rectangular flat-plate models and double-wedge airfoils in helium flow
    Keywords: AERODYNAMICS
    Type: NASA-MEMO-4-8-59L
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  • 63
    Publication Date: 2019-05-23
    Description: Wind tunnel studies at supersonic and transonic speeds to determine aerodynamic characteristics of variable sweep wing aircraft - configuration
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-206
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  • 64
    Publication Date: 2019-05-23
    Description: The static aeroelastic divergence characteristics of a delta-planform model of the canard control surface of a proposed air-to-ground missile have been studied both analytically and experimentally in the Mach number range from 0.6 to 3.0. The experiments indicated that divergence occurred at a nearly constant value of dynamic pressure at Mach numbers up to 1.2. At higher Mach numbers somewhat higher values of dynamic pressure were required to produce divergence. The analysis and the experiment indicate that the camber stiffness of the control surface and the stiffness of the control actuator are both important in divergence of surfaces of this type.
    Keywords: AERODYNAMICS
    Type: NACA-RM-L58E07
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  • 65
    Publication Date: 2019-05-23
    Description: Transonic performance of three turbojet nozzle- afterbody configurations
    Keywords: AERODYNAMICS
    Type: NASA-MEMO-10-24-58L
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  • 66
    Publication Date: 2019-05-23
    Description: Free flight drag measurements on delta wing with wing-fuselage-store
    Keywords: AERODYNAMICS
    Type: NASA-MEMO-10-9-58L
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  • 67
    Publication Date: 2019-05-23
    Description: Stage-stacking technique for predicting over-all performance in multistage axial flow turbojet compressor using interstage-air bleed
    Keywords: AERODYNAMICS
    Type: NASA-MEMO-10-4-58E
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  • 68
    Publication Date: 2019-05-23
    Description: Mach number and air temperature effect on hypersonic flow over blunt bodies
    Keywords: AERODYNAMICS
    Type: NASA-MEMO-10-9-58A
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  • 69
    Publication Date: 2019-05-23
    Description: Aerodynamic loads on external store adjacent to 60 deg delta wing at Mach numbers 0.75 to 1.96
    Keywords: AERODYNAMICS
    Type: NACA-RM-L56B02A
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  • 70
    Publication Date: 2019-05-23
    Description: A supersonic wind-tunnel investigation on store interference has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 1.61. Forces and moments were measured on a large ogive-cylinder store in the presence of a 45 deg swept-wing-fuselage bomber configuration for a number of store locations below the fuselage center line. Results of the investigation show that large variations of store lift, drag, and pitch occur with changes in store or airplane angle of attack, store vertical location, and store horizontal location. The variation of the store forces and moments with respect to the chordwise location of the wing plan form indicates that the wing is a large factor in producing the interference loads on the store. Comparison of data for underfuselage and underwing store locations at an angle of attack of 0 deg showed maximum store drag interferences of similar magnitudes, but showed considerably smaller maximum interference on store lift an pitching moments for underfuselage store locations.
    Keywords: AERODYNAMICS
    Type: NACA-RM-L56I25
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  • 71
    Publication Date: 2019-05-23
    Description: Low cowl drag, external compression inlet with subsonic dump diffuser for high Mach number application
    Keywords: AERODYNAMICS
    Type: NACA-RM-E58A09
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  • 72
    Publication Date: 2019-05-23
    Description: Experimental investigation of high subsonic turbine with forty blade rotor with zero suction-surface diffusion
    Keywords: AERODYNAMICS
    Type: NACA-RM-E57J22
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  • 73
    Publication Date: 2019-05-23
    Description: Double-ramp side inlet with combinations of fuselage, ramp, and throat boundary layer removal
    Keywords: AERODYNAMICS
    Type: NACA-RM-E56G09A
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  • 74
    Publication Date: 2019-05-23
    Description: Static longitudinal stability and control characteristics of wingless missile configuration at supersonic and hypersonic speeds
    Keywords: AERODYNAMICS
    Type: NACA-RM-A58C20
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  • 75
    Publication Date: 2019-05-23
    Description: Overall stage and stator blade element performance with straight stator and tilted stator in transonic axial flow compressor stage
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-99
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  • 76
    Publication Date: 2019-05-23
    Description: Pressure measurements in flight over conically cambered delta wing of F-102A aircraft at transonic speeds
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-48
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  • 77
    Publication Date: 2019-06-28
    Description: An exploratory wind-tunnel investigation has been made to determine the lift effects of blowing from nacelles over the upper surface of flaps on a model having a delta wing of aspect ratio 3. Several flap conditions were examined. High-pressure air was blown from an external-pipe arrangement supported above the wing to simulate jet-engine exhaust. The jet momentum- coefficient range was from 0 to 3.0 and the model angle of attack was 0 deg. The results of this limited investigation show that values of jet circulation lift coefficient larger than the Jet reaction were produced with blowing over flaps from nacelles mounted above the wing. 'I!heuse of double slotted flaps with the gap unsealed between the flaps and wing had a large detrimental effect on the lift capabilities. With these gaps sealed, larger lift coefficients were obtained when fantails were added to the nacelles. The longitudinal trim problems created by large diving moments were similar to those encountered with other jet-augmented-flap systems
    Keywords: Aerodynamics
    Type: NACA-TN-4298
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  • 78
    Publication Date: 2019-06-28
    Description: Problems involved in the stability and control of tailless airplanes are discussed. Such factors as the location of the aerodynamic center and its effect on the longitudinal stability, longitudinal trim with high-lift devices, the effects of various changes in the shape of the wing on lateral stability, and the effects of nacelles are covered. It appears that sufficient stability and controllability can be secured without sweepback. With sweepback, a flap over the center section of the wing may be used to serve the dual purpose of elevator control and high-lift device. Sweepback introduces undesirable stalling characteristics, however, and may require auxiliary devices to prevent stalling of the tips.
    Keywords: Aerodynamics
    Type: NACA-TN-837
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  • 79
    Publication Date: 2019-06-28
    Description: An analysis, based on the linearized thin-airfoil theory for supersonic speeds, of the wave drag at zero lift has been carried out for a simple two-body arrangement consisting of two wedgelike surfaces, each with a rhombic lateral cross section and emanating from a common apex. Such an arrangement could be used as two stores, either embedded within or mounted below a wing, or as auxiliary bodies wherein the upper halves could be used as stores and the lower halves for bomb or missile purposes. The complete range of supersonic Mach numbers has been considered and it was found that by orienting the axes of the bodies relative to each other a given volume may be redistributed in a manner which enables the wave drag to be reduced within the lower supersonic speed range (where the leading edge is substantially subsonic). At the higher Mach numbers, the wave drag is always increased. If, in addition to a constant volume, a given maximum thickness-chord ratio is imposed, then canting the two surfaces results in higher wave drag at all Mach numbers. For purposes of comparison, analogous drag calculations for the case of two parallel winglike bodies with the same cross-sectional shapes as the canted configuration have been included. Consideration is also given to the favorable (dragwise) interference pressures acting on the blunt bases of both arrangements.
    Keywords: Aerodynamics
    Type: NACA-TN-4120
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  • 80
    Publication Date: 2019-06-28
    Description: A simplified analysis of the velocity and deceleration history of missiles entering the earth's atmosphere at high supersonic speeds is presented. The results of this motion analysis are employed to indicate means available to the designer for minimizing aerodynamic heating. The heating problem considered involves not only the total heat transferred to a missile by convection, but also the maximum average and local time rates of convective heat transfer.
    Keywords: Aerodynamics
    Type: NACA-TN-4047
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  • 81
    Publication Date: 2019-06-28
    Description: A solution of the equations of the compressible laminar boundary layer including the effects of transpiration cooling is presented. The analysis applies to the flow over an isothermal porous plate with a velocity of fluid injection proportional to the reciprocal of the square root of the distance from the leading edge. The effect of several flow parameters on coolant-flow rates is discussed with the aid of representative examples. A stability analysis indicates that, although transpiration cooling requires a lower surface temperature for stable flow than does internal wall cooling, this lower temperature can be obtained with a smaller expenditure of coolant.
    Keywords: Aerodynamics
    Type: NACA-TN-3404
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  • 82
    Publication Date: 2019-06-28
    Description: An investigation was made of the flow downstream from a "two-dimensional" grid formed of parallel rods. In both two and three dimensional jet fields there is a critical range of grid density below which the downstream flow is stable and above which it is unstable. The flow can be completely stabilized by means of an adequate lateral contraction beginning immediately after the grid or by use of a fine-mesh damping screen parallel to the grid plane and within a definite range of positions downstream from the grid.
    Keywords: Aerodynamics
    Type: NACA-WR-W-90 , NACA-ACR-4H24
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  • 83
    Publication Date: 2019-06-28
    Description: Problem of improving thrust at low speeds is primarily one of reducing angle of attack of operation of sections to improve L/D or reducing blade helix angle. An analysis, based on recent propeller data, is presented for determining improvements in thrust or efficiency which could be obtained by increased number of blades, increased blade width, increased diameter, dual rotation, and two-speed gearing. All methods were found very effective, particularly two-speed gearing.
    Keywords: Aerodynamics
    Type: NACA-WR-L-483
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  • 84
    Publication Date: 2019-06-28
    Description: Test of a ducted body with Internal flow were made in the 8-foot high-speed wind tunnel for the purpose of studying the effects on external drag and an critical speed of the addition of efficient inlet and outlet openings to a basic streamline shape. Drag tests of a 13.6- inch-diameter streamline body of fineness ratio 6.14 were made at Mach numbers ranging from 0.20 to 0.75. The model was centrally mounted on a 9-percent-thick airfoil and was designed to have an efficient airfoil-body juncture and a high critical speed. An air inlet at the nose and various outlets at the tail were added: drag and internal-flow data were obtained over the given speed range. The critical speed of the ducted bodies was found to be as high as that of the streamline body. The external - drag with air flow through the body did not exceed the drag of the basic streamline shape. No appreciable variation in the efficiency of the diffuser section of the internal duct occurred throughout the Mach number range of the tests.
    Keywords: Aerodynamics
    Type: NACA-WR-L-486
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  • 85
    Publication Date: 2019-06-28
    Description: Data taken from tests at constant speed to establish trim limits of stability, tests at accelerated speeds to determine stable limits of center of gravity shift, and tests at decelerated speeds to obtain landing characteristics of several model hull forms were used to establish hull design effect on longitudinal stability of porpoising. Results show a reduction of dead rise angle as being the only investigated factor reducing low trim limit. Various methods of reducing afterbody interference increased upper trim limit
    Keywords: Aerodynamics
    Type: NACA-WR-L-468
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  • 86
    Publication Date: 2019-06-28
    Description: In order to determine the critical stresses caused by an outward acting pressure on the upper surface of a wing due to the difference in internal and external pressures, torsional tests were made on two curved-sheet specimens subjected to an outward acting normal pressure. Results show that an outward acting normal pressure appreciable raises the critical shear stress for an unstiffened curved sheet; the absolute increase in critical shear stress is slightly greater for a 30 in. rib spacing than for a 10 in. rib spacing.
    Keywords: Aerodynamics
    Type: NACA-WR-L-416
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  • 87
    Publication Date: 2019-06-28
    Description: Two airfoil plans were used for propeller blades. One is modified Clark Y section designed for structural reliability and the second an NACA 16 airfoil section designed to produce minimum aerodynamic losses. At low air speeds, the propeller designed for aerodynamic effects showed a gain of from 1.5 to 4.0 percent in propulsive efficiency over the conventional type depending on the pitch. Because of the numerous variables involved, the effect of each one on the aerodynamic characteristics of the propellers could not be isolated.
    Keywords: Aerodynamics
    Type: NACA-WR-L-404
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  • 88
    Publication Date: 2019-06-28
    Description: Description is given of flight tests conducted on gun fairings, designed to correct the detrimental effects of the projecting and submerged wing guns on an F4F-3 fighter. It was found that the installation of unfaired guns on a clean wing resulted in a premature stall that increased the stalling speed in the carrier-approach and landing conditions of flight by suitably fairing the guns, it was possible to reduce the stalling speeds to values approaching very nearly the clean-wing values.
    Keywords: Aerodynamics
    Type: NACA-WR-L-247
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  • 89
    Publication Date: 2019-06-28
    Description: Porpoising characteristics were observed on V-body fitted with tail surfaces for different combinations of load, speed, moment of inertia, location of pivot, elevator setting, and tail area. A critical trim was found which was unaltered by elevator setting or tail area. Critical trim was lowered by moving pivot either forward or down or increasing radius or gyration. Increase in mass and moment of inertia increased amplitude of oscillations. Complete results are tabulated and shown graphically.
    Keywords: Aerodynamics
    Type: NACA-WR-L-479
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  • 90
    Publication Date: 2019-06-28
    Description: No abstract available
    Keywords: Aerodynamics
    Type: NACA-WR-L-702
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  • 91
    Publication Date: 2019-06-28
    Description: No abstract available
    Keywords: Aerodynamics
    Type: NACA-WR-L-493
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  • 92
    Publication Date: 2019-06-28
    Description: Pressure distribution measurements were made over an airfoil with slotted Frise aileron up to 0.76 Mach at various angles of attack and aileron defections. Section characteristics were determined from these pressure data. Results indicated loss of aileron rolling power for deflections ranging from -12 Degrees to -19 Degrees. High stick forces for non-differential deflections incurred at high speed, which were due to overbalancing tendency of up-moving aileron, may precipitate serious control difficulties. Detailed results are presented graphically.
    Keywords: Aerodynamics
    Type: NACA-WR-L-266 , NACA-ACR-L4G12
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  • 93
    Publication Date: 2019-06-28
    Description: Methods are given of determining the potential flow plast an arbitrary cascade of airfoils and the inverse problem of determining an airfoil having a prescribed velocity distribution in cascade. Results indicated that Cartesian mapping function method may be satisfactorily extended to include cascades. Numerical calculation for computing cascades by Cartesian mapping function method is considerably greater than for single airfoils but much less than hitherto required for cascades. Detailed results are presented graphically.
    Keywords: Aerodynamics
    Type: NACA-WR-L-81 , NACA-ARR-L4K22B
    Format: application/pdf
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  • 94
    Publication Date: 2019-06-28
    Description: Flight tests were conducted on the OS2U-2 seaplane with simple circular-arc-type ailerons directly connected to the actuating torque tube. Two aileron test installations were made, differing only in the inclination of the projecting surface with the wing's upper surface. The lateral-control characteristics of the airplane were determined from data obtained in stalls and rudder-fixed aileron rolls. The revised ailerons were deficient in maximum rolling effectiveness, but were capable of controlling the rolling tendencies of the airplane near the stall.
    Keywords: Aerodynamics
    Type: NACA-WR-A-32
    Format: application/pdf
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  • 95
    Publication Date: 2019-06-28
    Description: This report contains those results of the theory of wings and of wing sections which are of immediate practical value. They are proved and demonstrated by the use of the simple conceptions of "kinetic energy" and "momentum" only, familiar to every engineer; and not by introducing "isogonal transformations" and "vortices," which latter mathematical methods are not essential to the theory and better are used only in papers intended for mathematicians and special experts.
    Keywords: Aerodynamics
    Type: NACA-TR-191
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  • 96
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    Unknown
    In:  CASI
    Publication Date: 2019-06-28
    Description: Available experimental two-dimensional-cascade data for conventional compressor blade sections are correlated. The two-dimensional cascade and some of the principal aerodynamic factors involved in its operation are first briefly described. Then the data are analyzed by examining the variation of cascade performance at a reference incidence angle in the region of minimum loss. Variations of reference incidence angle, total-pressure loss, and deviation angle with cascade geometry, inlet Mach number, and Reynolds number are investigated. From the analysis and the correlations of the available data, rules and relations are evolved for the prediction of the magnitude of the reference total-pressure loss and the reference deviation and incidence angles for conventional blade profiles. These relations are developed in simplified forms readily applicable to compressor design procedures.
    Keywords: Aerodynamics
    Type: NACA-RM-E56B03a
    Format: application/pdf
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  • 97
    Publication Date: 2019-06-28
    Description: A model of a cruciform missile configuration having a low-aspect-ratio wing equipped with flap-type controls was flight tested in order to determine stability and control characteristics while rolling at about 5 radians per second. Comparison is made with results from a similar model which rolled at a much lower rate. Results showed that, if the ratio of roll rate to natural circular frequency in pitch is not greater than about 0.3, the motion following a step disturbance in pitch essentially remains in a plane in space. The slope of normal- force coefficient against angle of attack C(sub N(sub alpha)) was the same as for the slowly rolling model at 0 degrees control deflection but C(sub N(sub alpha)) was much higher for the faster rolling model at about 5 degrees control deflection. The slope of pitching-moment coefficient against angle of attack C(sub m(sub alpha)) as determined from the model period of oscillation was the same for both models at 0 degrees control deflection but was lower for the faster rolling model at about 5 degrees control deflection. Damping data for the faster rolling model showed considerably more scatter than for the slowly rolling model.
    Keywords: Aerodynamics
    Type: NACA-RM-L55L16
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  • 98
    Publication Date: 2019-06-28
    Description: The temperature distributions encountered in thin solid wings subjected to aerodynamic heating induce thermal stresses that may effectively reduce the stiffness of the wing. The effects of this reduction in stiffness were investigated experimentally by rapidly heating the edges of a cantilever plate. The midplane thermal stresses imposed by the nonuniform temperature distribution caused the plate to buckle torsionally, increased the deformations of the plate under a constant applied torque, and reduced the frequency of the first two natural modes of vibration. By using small-deflection theory and employing energy methods, the effect of nonuniform heating on the plate stiffness was calculated. The theory predicts the general effects of the thermal stresses, but becomes inadequate as the temperature difference increases and plate deflections become large.
    Keywords: Aerodynamics
    Type: NACA-RM-L55E20c
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  • 99
    Publication Date: 2019-06-28
    Description: Skin-temperature measurements have been made at several locations on a flat-faced cone-cylinder nose which was flight tested on a fivestage rocket-propeller model to a Mach number of 14.64 and a free-stream Reynolds number of 2.0 x 10(exp 6), based on flat-face diameter, at an altitude of 66,300 feet. The copper nose had a 29 deg total-angle conical section which was 1.6 flat-face diameters long. The aerodynamic-heating rates determined from the temperature measurements reached 1,440 Btu/( sec) (sq ft) on the flat face. The heating rates near the center of the flat face agreed well at Mach numbers up to 13.6 with those obtained by a theory for laminar stagnation-point heating in equilibrium dissociated air (Avco Res. Rep. 1). At Mach numbers above 13.6, the heating rates at locations near the center of the flat face became progressively lower than stagnation-point theory and. were 29 percent lower at Mach number 14.6 at the end. of the test. The reason for this behavior of the heating on the central part of the flat face was not determined. Excluding the relatively low heating rates that occurred on the central part of the nose at the highest Mach numbers, the distribution of experimental heating along the innermost 0.79 of the flat-face radius, expressed as a percentage of stagnation-point heating, was in fair agreement with the distribution predicted by laminar theory. At a location of 0.71 radii from the stagnation point, the experimental heating was very near 130 percent of the theoretical stagnation-point rate at Mach numbers from 11 to 14.5. The experimental beating rates on the conical section of the nose were in good agreement with laminar-cone theory using the assumption of theoretical sharp-cone static pressure on the conical section.
    Keywords: Aerodynamics
    Type: NACA-RM-L57L03
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  • 100
    Publication Date: 2019-06-28
    Description: The pitching and the yawing moments of a vee-type and a conventional type of tail surface were measured. The tests were made in the presence of a fuselage and a wing-fuselage combination in such a way as to determine the moments contributed by the tail surfaces. The results showed that the vee-type tail tested, with a dihedral angle of 35.3 deg, was about 71 percent as effective in pitch as the conventional tail and had a yawing-moment to pitching-moment ratio of 0.3. The conventional tail, the panels of which were all congruent to those of the vee-type tail, had a yawing-moment to pitching-moment ratio of 0.48. These ratios are in fair agreement with values calculated by methods shown in this and previous reports. The values of the measured moments were reduced from 15 to 25 percent of the calculated value by fuselage interference.
    Keywords: Aerodynamics
    Type: NACA-TN-815
    Format: application/pdf
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