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![Development of an Apparatus for Wind Tunnel Dynamic Experiments at High-[alpha] PDF](https://books.google.com/books/content/images/frontcover/PdNQAAAAYAAJ?fife=w150-h200)
Author: Nelson Pedreiro
Publisher:
ISBN:
Category : Wind tunnels
Languages : en
Pages : 130
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Book Description
![Development of an Apparatus for Wind Tunnel Dynamic Experiments at High-[alpha] PDF](https://books.google.com/books/content/images/frontcover/PdNQAAAAYAAJ?fife=w80-h100)
Author: Nelson Pedreiro
Publisher:
ISBN:
Category : Wind tunnels
Languages : en
Pages : 130
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Book Description
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781723027574
Category :
Languages : en
Pages : 128
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Book Description
A unique experimental apparatus that allows a wind tunnel model two degrees of freedom has been designed and built. The apparatus was developed to investigate the use of new methods to augment aircraft control in the high angle of attack regime. The model support system provides a platform in which the roll-yaw coupling at high angles of attack can be studied in a controlled environment. Active cancellation of external effects is used to provide a system in which the dynamics are dominated by the aerodynamic loads acting on the wind tunnel model. Pedreiro, Nelson Ames Research Center WIND TUNNEL TESTS; AIRCRAFT CONTROL; AERODYNAMIC LOADS; ACTIVE CONTROL; WIND TUNNEL STABILITY TESTS; AERODYNAMIC STABILITY; WIND TUNNEL APPARATUS; WIND TUNNEL MODELS; DEGREES OF FREEDOM; ANGLE OF ATTACK; FLOW DISTRIBUTION...
Author: Colin Britcher
Publisher: Academic Press
ISBN: 0128181001
Category : Technology & Engineering
Languages : en
Pages : 672
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Book Description
Wind Tunnel Test Techniques: Design and Use at Low and High Speeds with Statistical Engineering Applications provides an up-to-date treatment of the topic. Beginning with a brief history of wind tunnels and its types and uses, the book goes on to cover subsonic, supersonic and hypersonic wind tunnel design and construction, calibration, boundary corrections, flow quality assessment, pressure surveys, and dynamic testing. It also focuses on wind tunnel facilities, making it useful for both the designer and operator. Engineers and graduate students in aerospace, automotive and similar programs will find this book useful in their work with experimental aerodynamics, gas dynamics, facility design and performance. - Deals with a broad range of flow speeds in wind tunnels, from low speed to high speed - Provides a discussion of similarity laws as well as material on statistical analysis - Includes coverage on facility-to-facility and facility-to-CFD correlation - Presents advanced topics such as cryogenic wind tunnels, ground simulation in automotive testing, and propulsion testing
Author: Jorge Colman Lerner
Publisher: BoD – Books on Demand
ISBN: 9533076232
Category : Science
Languages : en
Pages : 728
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Book Description
The book "Wind Tunnels and Experimental Fluid Dynamics Research" is comprised of 33 chapters divided in five sections. The first 12 chapters discuss wind tunnel facilities and experiments in incompressible flow, while the next seven chapters deal with building dynamics, flow control and fluid mechanics. Third section of the book is dedicated to chapters discussing aerodynamic field measurements and real full scale analysis (chapters 20-22). Chapters in the last two sections deal with turbulent structure analysis (chapters 23-25) and wind tunnels in compressible flow (chapters 26-33). Contributions from a large number of international experts make this publication a highly valuable resource in wind tunnels and fluid dynamics field of research.
Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781723862748
Category : Science
Languages : en
Pages : 54
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Book Description
This manual describes the NASA Glenn Research Center's 1 - by 1 -Foot Supersonic Wind Tunnel and provides information for customers who wish to conduct experiments in this facility. Tunnel performance envelopes of total pressure, total temperature, and dynamic pressure as a function of test section Mach number are presented. For each Mach number, maps are presented of Reynolds number per foot as a function of the total air temperature at the test section inlet for constant total air pressure at the inlet. General support systems-such as the service air, combustion air, altitude exhaust system, auxiliary bleed system, model hydraulic system, schlieren system, model pressure-sensitive paint, and laser sheet system are discussed. In addition, instrumentation and data processing, acquisition systems are described, pretest meeting formats and schedules are outlined, and customer responsibilities and personnel safety are addressed.Seablom, Kirk D. and Soeder, Ronald H. and Stark, David E. and Leone, John F. X. and Henry, Michael W.Glenn Research CenterMACH NUMBER; REYNOLDS NUMBER; SUPERSONIC WIND TUNNELS; SUPERSONIC FLOW; TEST CHAMBERS; DATA ACQUISITION; MANUALS; WIND TUNNEL NOZZLES; DYNAMIC PRESSURE; WIND TUNNEL TESTS
Author: O. B. Tufts
Publisher:
ISBN:
Category : Stability of airplanes, Longitudinal
Languages : en
Pages : 246
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Book Description
Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781730733956
Category : Science
Languages : en
Pages : 56
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Book Description
This manual describes the 10- by 10-Foot Supersonic Wind Tunnel at the NASA Lewis Research Center and provides information for users who wish to conduct experiments in this facility. Tunnel performance operating envelopes of altitude, dynamic pressure, Reynolds number, total pressure, and total temperature as a function of test section Mach number are presented. Operating envelopes are shown for both the aerodynamic (closed) cycle and the propulsion (open) cycle. The tunnel test section Mach number range is 2.0 to 3.5. General support systems, such as air systems, hydraulic system, hydrogen system, fuel system, and Schlieren system, are described. Instrumentation and data processing and acquisition systems are also described. Pretest meeting formats and schedules are outlined. Tunnel user responsibility and personnel safety are also discussed. Soeder, Ronald H. Glenn Research Center...
Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781723853821
Category : Science
Languages : en
Pages : 68
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Book Description
To better understand the ground effect encountered by slender wing supersonic transport aircraft, a test was conducted at NASA Langley Research Center's 14 x 22 foot Subsonic Wind Tunnel in October, 1997. Emphasis was placed on improving the accuracy of the ground effect data by using a "dynamic" technique in which the model's vertical motion was varied automatically during wind-on testing. This report describes and evaluates different aspects of the dynamic method utilized for obtaining ground effect data in this test. The method for acquiring and processing time data from a dynamic ground effect wind tunnel test is outlined with details of the overall data acquisition system and software used for the data analysis. The removal of inertial loads due to sting motion and the support dynamics in the balance force and moment data measurements of the aerodynamic forces on the model is described. An evaluation of the results identifies problem areas providing recommendations for future experiments. Test results are validated by comparing test data for an elliptical wing planform with an Elliptical wing planform section with a NACA 0012 airfoil to results found in current literature. Major aerodynamic forces acting on the model in terms of lift curves for determining ground effect are presented. Comparisons of flight and wind tunnel data for the TU-144 are presented.Graves, Sharon S.Langley Research CenterGROUND EFFECT (AERODYNAMICS); AERODYNAMIC FORCES; SUBSONIC WIND TUNNELS; WIND TUNNEL TESTS; DATA ACQUISITION; AIRCRAFT DESIGN; AERODYNAMIC CONFIGURATIONS; AIRCRAFT CONFIGURATIONS; SLENDER WINGS; WING PLANFORMS; SUPERSONIC TRANSPORTS; TU-144 AIRCRAFT; VERTICAL MOTION
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722834210
Category :
Languages : en
Pages : 78
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Book Description
The design of closed circuit wind tunnels has historically been performed using rule of thumb which have evolved over the years into a body of useful guidelines. The development of indraft wind tunnels, however, has not been as well documented. The design of indraft wind tunnels is therefore generally performed using a more intuitive approach, often resulting in a facility with disappointing flow quality. The primary problem is a lack of understanding of the flow in the inlet as it passes through the required antiturbulence treatment. For wind tunnels which employ large contraction ratio inlets, this lack of understanding is not serious since the relatively low velocity of the flow through the inlet treatment reduces the sensitivity to improper inlet design. When designing a small contraction ratio inlet, much more careful design is needed in order to reduce the flow distortions generated by the inlet treatment. As part of the National Full Scale Aerodynamics Complex Modification Project, 2-D computational methods were developed which account for the effect of both inlet screens and guide vanes on the test section velocity distribution. Comparisons with experimental data are presented which indicate that the methods accurately compute the flow distortions generated by a screen in a nonuniform velocity field. The use of inlet guide vanes to eliminate the screen induced distortion is also demonstrated both computationally and experimentally. Extensions of the results to 3-D is demonstrated and a successful wind tunnel design is presented. Ross, James C. Ames Research Center...
Author: Joseph R. Chambers
Publisher:
ISBN: 9781580072199
Category : History
Languages : en
Pages : 162
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Book Description
Radical Wings and Wind Tunnels presents a behind-the-scenes look at how the NACA, and today's NASA, have used wind tunnels and flight-testing in past and current projects to advance aeronautical science. NASA's Langley Research Center, located in Hampton, Virginia, was established on July 17, 1917, and has played a key role in the research and development of civil and military aviation since its infancy. For over 90 years, Langley's staff has wind-tunnel tested or test flown a wide range of leading-edge aircraft designs including vertical takeoff and landing aircraft, advanced fighters, civil transports, and high-speed supersonic and hypersonic vehicles. Results from the legacy of Langley's pioneering basic and applied aeronautical research have been incorporated into virtually all U.S. civil transports and military aircraft. This book describes the very unique testing capabilities of several historic Langley wind tunnels, such as the gigantic 30 x 60 ft Full Scale Tunnel, the Vertical Spin Tunnel, and the Free-Flight Tunnel. The major focus of the book is a discussion of the roles these wind tunnels and the NACA and NASA organizations played in R&D activities for more than 60 radical aerospace vehicles that did not, or have not yet entered production. The contents present an illuminating perspective on how the government's research agencies interacted beneficially with the military and civil communities for many of this nation's innovative aeronautical undertakings. Coverage begins in the 1920s with research on the earliest innovations for monoplanes and extends to current research on tomorrow's aircraft including hypersonic vehicles and aircraft designed to explore the Martian environment. Topics also include previously unpublished details of NACA activities in development of U.S. military aircraft in WWII, Langley's work on parawing vehicles, key activities for V/STOL aircraft, challenges for lifting bodies and reentry vehicles, ongoing research to remove the barriers for economically viable supersonic commercial transport, the latest technology for highly maneuverable fighters, and a look at the future. The photos in this edition are in black and white.
