Download or read book Design and Evaluation of a Low speed Wind tunnel with Expanding Corners written by Arne V. Johansson and published by . This book was released on 2002 with total page 43 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Design and Evaluation of a Low Speed Density and Velocity Stratified Wind Tunnel written by Jack William Pluister and published by . This book was released on 1973 with total page 112 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Low Speed Wind Tunnel Testing written by Jewel B. Barlow and published by John Wiley & Sons. This book was released on 1999-02-22 with total page 738 pages. Available in PDF, EPUB and Kindle. Book excerpt: A brand-new edition of the classic guide on low-speed wind tunnel testing While great advances in theoretical and computational methods have been made in recent years, low-speed wind tunnel testing remains essential for obtaining the full range of data needed to guide detailed design decisions for many practical engineering problems. This long-awaited Third Edition of William H. Rae, Jr.'s landmark reference brings together essential information on all aspects of low-speed wind tunnel design, analysis, testing, and instrumentation in one easy-to-use resource. Written by authors who are among the most respected wind tunnel engineers in the world, this edition has been updated to address current topics and applications, and includes coverage of digital electronics, new instrumentation, video and photographic methods, pressure-sensitive paint, and liquid crystal-based measurement methods. The book is organized for quick access to topics of interest, and examines basic test techniques and objectives of modeling and testing aircraft designs in low-speed wind tunnels, as well as applications to fluid motion analysis, automobiles, marine vessels, buildings, bridges, and other structures subject to wind loading. Supplemented with real-world examples throughout, Low-Speed Wind Tunnel Testing, Third Edition is an indispensable resource for aerospace engineering students and professionals, engineers and researchers in the automotive industries, wind tunnel designers, architects, and others who need to get the most from low-speed wind tunnel technology and experiments in their work.

Download or read book Wind Tunnel Test Techniques written by Colin Britcher and published by Academic Press. This book was released on 2023-10-20 with total page 672 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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

Download or read book Experimental Evaluation of Two Turning Vane Designs for High speed Corner of 0 1 scale Model of NASA Lewis Research Center s Proposed Altitude Wind Tunnel written by Royce D. Moore and published by . This book was released on 1986 with total page 136 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Experimental Evaluation of Two Turning Vane Designs for High speed Corner of 0 1 scale Model of NASA Lewis Research Center s Proposed Altitude Wind Tunnel written by Royce D. Moore and published by . This book was released on 1986 with total page 136 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Design Construction and Evaluation of a Subsonic Wind Tunnel written by Milan Vlajinac and published by . This book was released on 1970 with total page 128 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Wind Tunnel Designs and Their Diverse Engineering Applications written by Noor Ahmed and published by BoD – Books on Demand. This book was released on 2013-03-06 with total page 232 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.

Download or read book Experimental Evaluation of Turning Vane Designs for High Speed and Coupled Fan Drive Corners of 0 1 Scale Model of NASA Lewis Research Center s Proposed Altitude Wind Tunnel written by Thomas F. Gelder and published by . This book was released on 1987 with total page 51 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Report on Evaluation and Development of a Low seed Wind Tunnel written by Chan Ho Park and published by . This book was released on 1970 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: The purpose of the present work is to determine the flow characteristics of the existing low-speed wind tunnel located in the Fluid Dynamics and Heat Transfer Laboratory and to correct any prominent unsatisfactory characteristics that might exist. A schematic diagram of the wind tunnel system is shown as figure 1 and its specifications are described in section II. The present investigation was initiated as a result of the wind tunnel being moved from a location wherein the blower was connected directly to the wind tunnel to its new location where space requirements dictated that a plenum chamber be placed between the blower and the tunnel. The plenum chamber causes the flow through it to be turned 90 degrees, thereby effecting a required decrease in the in-line length of the blower-tunnel combination. Additionally, the plenum chamber provides for access ports which can be utilized by other flow experiments using the same blower. As with any flow turning device, the introduction of the plenum chamber is expected to increase the losses through the system. In its former location, the tunnel had been evaluated with respect to attainable velocities, velocity profiles in the test section, and turbulence intensities. This evaluation, as accomplished by Sohn, showed that the tunnel performance was generally satisfactory and that the maximum obtainable test section velocity was 256 fps. However, after the tunnel was installed in its new location, the maximum velocity was observed in initial tests to be reduced to 180 fps; additionally, the tunnel appeared to be "rough" during operation at higher velocities. In view of the foregoing performance deterioration, some modifications in the tunnel configuration in its new location were clearly needed. First, the flow losses could be reduced by placing some turning vanes in the plenum chamber, which initially turned the flow 90 degrees without the aid of any interior surfaces. Secondly, it was reasoned that the "rough" sound of the wind tunnel might be the result of a resonance coupling between the main flow going through the plenum chamber and the rather large cavities existing both above and below the elevations where the wind tunnel and the blower join the plenum. It might be added that the plenum chamber was not designed in its 4' x 4' x 8' shape for its present use, but rather was available. This possible resonance problem was attacked by locating two 4' x 4' panels horizontally inside the plenum chamber so as to block off the unused portions of the plenum chamber. Details of these two major modifications are shown in figure 1. One additional improvement sought in the tunnel performance was a reduction in test section turbulence intensity. Such improvement was sought by adding a second 20 x 20 mesh screen in front of the single screen spanning the wind tunnel entrance. This addition, in conjunction with the foregoing modifications, resulted in the three following wind tunnel configurations for the current series of tests: Configuration #1 - As initially installed in the new location with no turning vanes or 4' x 4' panels and a single entrance screen; Configuration #2 - With turning vanes and panels in place and a single entrance screen; Configuration #3 - As in #2 with the exception of having two entrance screens. The particular evaluation tests which have been performed on the tunnel in this present project include the following: a. Measurements of center-line velocity in the test section for various louver openings (velocity levels) and tunnel configurations; b. Measurements of velocity profile across the test section at mid-height for various louver openings; c. Determination of center-line turbulence intensity in the test section for various louver openings and tunnel configurations; d. Determination of turbulence intensity across the test section at mid-height for various louver openings. In addition to the above tests, several oscillograph traces showing center-line velocity patterns as measured by a hot-wire anemometer were photographically recorded. Such recordings were made for different velocity levels and tunnel configurations, and they provide convenient quantitative insight into the tunnel performance.

Download or read book Development of Guide vanes for Expanding Corners with Application in Wind tunnel Design written by and published by . This book was released on 1999 with total page 6 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Design and Evaluation of a Pulsating Flow Wind Tunnel written by Amir Tavakoli and published by . This book was released on 1982 with total page 320 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Design of a Low Speed Wind Tunnel written by Ernest Kleinfeld and published by . This book was released on 1946 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Atmospheric and Pressurized Low Speed Wind Tunnel Performance and Cost Comparisons written by N. Matheson and published by . This book was released on 1984 with total page 21 pages. Available in PDF, EPUB and Kindle. Book excerpt: In this Australian report, the performance of a series of low-speed wind tunnels designed to operate at various maximum pressures ranging from 2 to 5 atmospheres is estimated and compared with the performance of a similar atmospheric tunnel on the basis of capital cost and power input. The choice of the design of a new tunnel is usually influenced by cost and power considerations and it is important to provide the most capable design and to maximize performance within given limits of these variables. Pressurization offers a major advantage in allowing Reynolds number (RN) and Mach number (MN) effects to be investigated separately. This can be particularly important for tests of modern aircraft configurations operating at high lift. For the same capital cost and consumption, pressurization allows the maximum RN and MN to be increased substantially, but the working section is much smaller. This may make it difficult to satisfy some test requirements particularly for V/STOL aircraft. Models for a pressurized tunnel are also more complex and may be more costly because they must withstand much higher aerodynamic loads. To illustrate the effects of tunnel pressurization the analysis is applied to a tandem section low-speed tunnel previously suggested as suitable for future Australian test requirements. Keywords include: Subsonic wind tunnels, and Model tests.

Download or read book Journal of Fluids Engineering written by and published by . This book was released on 2008 with total page 266 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Design of a Low Speed two Dimensional Wind Tunnel written by Allen B. Barton and published by . This book was released on 1951 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Contraction Design for Small Low Speed Wind Tunnels written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: An iterative design procedure was developed for two- or three-dimensional contractions installed on small, low-speed wind tunnels. The procedure consists of first computing the potential flow field and hence the pressure distributions along the walls of a contraction of given size and shape using a three-dimensional numerical panel method. The pressure or velocity distributions are then fed into two-dimensional boundary layer codes to predict the behavior of the boundary layers along the walls. For small, low-speed contractions it is shown that the assumption of a laminar boundary layer originating from stagnation conditions at the contraction entry and remaining laminar throughout passage through the successful designs if justified. This hypothesis was confirmed by comparing the predicted boundary layer data at the contraction exit with measured data in existing wind tunnels. The measured boundary layer momentum thicknesses at the exit of four existing contractions, two of which were 3-D, were found to lie within 10 percent of the predicted values, with the predicted values generally lower. From the contraction wall shapes investigated, the one based on a fifth-order polynomial was selected for installation on a newly designed mixing layer wind tunnel. Bell, James H. and Mehta, Rabindra D. Unspecified Center NCC2-294; RTOP 505-60-31...