Journal articles: 'Wind tunnel testing'

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Shindo, Shojiro. "Wind Tunnel Testing." Journal of the Visualization Society of Japan 15, Supplement1 (1995): 277–80. http://dx.doi.org/10.3154/jvs.15.supplement1_277.

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Hasan, Inamul, R. Mukesh, P. Radha Krishnan, R. Srinath, Dhanya Prakash Babu, and Negash Lemma Gurmu. "Wind Tunnel Testing and Validation of Helicopter Rotor Blades Using Additive Manufacturing." Advances in Materials Science and Engineering 2022 (September 21, 2022): 1–13. http://dx.doi.org/10.1155/2022/4052208.

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This research paper aims to validate the aerodynamic performance of rotor blades using additive manufacturing techniques. Wind tunnel testing is a technique used to find the flow characteristics of the body. Computational fluid dynamics (CFD) techniques are used for aerodynamic analysis, and validation should be done using wind tunnel testing. In the aerodynamic testing of models, additive manufacturing techniques help in validating the results by making models easily for wind tunnels. Recent developments in additive manufacturing help in the aerodynamic testing of models in wind tunnels. The CFD analysis of helicopter rotor blades was analyzed in this research, and validation was done using additive manufacturing techniques. Computational analysis was carried out for static analysis for the forward speeds of Mach numbers 0.3, 0.4, and 0.5. The results obtained were satisfactory to the previous results and were validated with wind tunnel testing. Results proved that the error percentage was lower, and the computational analysis was valid. In this research, models were designed using the FDM technique for wind tunnel testing as it is cost-effective and easy to manufacture.

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Teo, Z. W., T. H. New, Shiya Li, T. Pfeiffer, B. Nagel, and V. Gollnick. "Wind tunnel testing of additive manufactured aircraft components." Rapid Prototyping Journal 24, no. 5 (July 9, 2018): 886–93. http://dx.doi.org/10.1108/rpj-06-2016-0103.

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Purpose This paper aims to report on the physical distortions associated with the use of additive manufactured components for wind tunnel testing and procedures adopted to correct for them. Design/methodology/approach Wings of a joined-wing test aircraft configuration were fabricated with additive manufacturing and tested in a subsonic closed-loop wind tunnel. Wing deflections were observed during testing and quantified using image-processing procedures. These quantified deflections were then incorporated into numerical simulations and results had agreed with wind tunnel measurement results. Findings Additive manufacturing provides cost-effective wing components for wind tunnel test components with fast turn-around time. They can be used with confidence if the wing deflections could be accounted for systematically and accurately, especially at the region of aerodynamic stall. Research limitations/implications Significant wing flutter and unsteady deflections were encountered at higher test velocities and pitch angles. This reduced the accuracy in which the wing deflections could be corrected. Additionally, wing twists could not be quantified as effectively because of camera perspectives. Originality/value This paper shows that additive manufacturing can be used to fabricate aircraft test components with satisfactory strength and quantifiable deflections for wind tunnel testing, especially when the designs are significantly complex and thin.

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Zhang, Zheng Yu, Xu Hui Huang, Jiang Yin, and Han Xuan Lai. "Videogrammetric Techniques for Wind Tunnel Testing and Applications." Advanced Materials Research 986-987 (July 2014): 1629–33. http://dx.doi.org/10.4028/www.scientific.net/amr.986-987.1629.

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Videogrammetric measurement is a research focus for the organizations of wind tunnel test because of its no special requirements on the test model, its key techniques for the vibration environment of the high speed wind tunnel are introduced by this paper, such as the solution of exterior parameters with big-angle large overlap, the algorithm of image processing for extracting marked point, the method of camera calibration and wave-front distortion field measurement. The great requirements and application prospects of videogrammetry in wind tunnel fine testing have been demonstrated by several practice experiments, including to measure test model’s angle of attack, dynamic deformations and wave-front distortion field in high speed wind tunnels whose test section size is 2 meters.

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Greenwell, D. I. "Transonic industrial wind tunnel testing in the 2020s." Aeronautical Journal 126, no. 1295 (December 2, 2021): 125–51. http://dx.doi.org/10.1017/aer.2021.107.

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AbstractWind tunnels remain an essential element in the design and development of flight vehicles. However, graduates in aerospace engineering tend to have had little exposure to the demands of industrial experimental work, particularly at high speed, a situation exacerbated by a lack of up-to-date reference material. In an attempt to fill this gap, this paper presents an overview of the current and near-term status and usage of transonic industrial wind tunnels. The review is aimed at recent entrants to the field, with the aim of helping them make the step from research projects in small university facilities to commercial projects in large industrial facilities. In addition, a picture has emerged from the review that contradicts received wisdom that the wind tunnel is in decline. Globally, the industrial transonic wind tunnel is undergoing somewhat of a renaissance. Numbers are increasing, investment levels are rising, capabilities are being enhanced, and facilities are busy.

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Stalker, R. J. "Modern developments in hypersonic wind tunnels." Aeronautical Journal 110, no. 1103 (January 2006): 21–39. http://dx.doi.org/10.1017/s0001924000004346.

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AbstractThe development of new methods of producing hypersonic wind-tunnel flows at increasing velocities during the last few decades is reviewed with attention to airbreathing propulsion, hypervelocity aerodynamics and superorbital aerodynamics. The role of chemical reactions in these flows leads to use of a binary scaling simulation parameter, which can be related to the Reynolds number, and which demands that smaller wind tunnels require higher reservoir pressure levels for simulation of flight phenomena. The use of combustion heated vitiated wind tunnels for propulsive research is discussed, as well as the use of reflected shock tunnels for the same purpose. A flight experiment validating shock-tunnel results is described, and relevant developments in shock tunnel instrumentation are outlined. The use of shock tunnels for hypervelocity testing is reviewed, noting the role of driver gas contamination in determining test time, and presenting examples of air dissociation effects on model flows. Extending the hypervelocity testing range into the superorbital regime with useful test times is seen to be possible by use of expansion tube/tunnels with a free piston driver.

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Lara, Andrés, Jonathan Toledo, and Robert Paul Salazar Romero. "Characterization, Design Testing and Numerical Modeling of a Subsonic-Low Speed Wind Tunnel." Ingeniería 27, no. 1 (January 4, 2022): e17973. http://dx.doi.org/10.14483/23448393.17973.

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Context: Wind tunnels are essential devices in the study of flow properties through objects and scaled prototypes. This work presents a numerical study to characterize an existing wind tunnel, proposing modifications with the aim to improve the quality of the flow in the test chamber. Method: Experimental measurements of the inlet velocity and pressure distribution of a wind tunnel are nperformed. These empirical values are used as parameters to define boundary conditions in simulations. The Finite Element Method (FEM) at low speeds is implemented to determine the stream function by using a standard Galerkin method. Polynomial interpolations are employed to modify the contraction section design, and numerical simulations are performed in order to compare the numerical results of the flow for the existing and the modified wind tunnels. Results: Experimental measurements of the flow at the wind tunnel entrance are presented. The velocity field and distribution of thermodynamic variables inside the tunnel are numerically determined. This computations are useful since it is experimentally difficult to make measurements inside the channel. Additionally, numerical calculations of these variables are presented under modifications in the tunnel geometry. Conclusions: A comparison between these simulations show that laminar flow at low velocities can be modeled as incompressible and irrotational fluid under a bidimensional approximation along its longitudinal section. It is observed that modifications in the geometry of the tunnel can improve the flow in the test section of the wind tunnel in the laminar regime.

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Tsushima, Natsuki, Kenichi Saitoh, Hitoshi Arizono, and Kazuyuki Nakakita. "Structural and Aeroelastic Studies of Wing Model with Metal Additive Manufacturing for Transonic Wind Tunnel Test by NACA 0008 Example." Aerospace 8, no. 8 (July 25, 2021): 200. http://dx.doi.org/10.3390/aerospace8080200.

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Additive manufacturing (AM) technology has a potential to improve manufacturing costs and may help to achieve high-performance aerospace structures. One of the application candidates would be a wind tunnel wing model. A wing tunnel model requires sophisticated designs and precise fabrications for accurate experiments, which frequently increase manufacturing costs. A flutter wind tunnel testing, especially, requires a significant cost due to strict requirements in terms of structural and aeroelastic characteristics avoiding structural failures and producing a flutter within the wind tunnel test environment. The additive manufacturing technique may help to reduce the expensive testing cost and allows investigation of aeroelastic characteristics of new designs in aerospace structures as needed. In this paper, a metal wing model made with the additive manufacturing technique for a transonic flutter test is studied. Structural/aeroelastic characteristics of an additively manufactured wing model are evaluated numerically and experimentally. The transonic wind tunnel experiment demonstrated the feasibility of the metal AM-based wings in a transonic flutter wind tunnel testing showing the capability to provide reliable experimental data, which was consistent with numerical solutions.

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Bak, Christian, Anders S. Olsen, Andreas Fischer, Oliver Lylloff, Robert Mikkelsen, Mac Gaunaa, Jimmie Beckerlee, et al. "Wind tunnel benchmark tests of airfoils." Journal of Physics: Conference Series 2265, no. 2 (May 1, 2022): 022097. http://dx.doi.org/10.1088/1742-6596/2265/2/022097.

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Abstract This paper describes a benchmark of four airfoils in the Poul la Cour Tunnel (PLCT). The wind tunnel, the corrections used and the method of making adapters for the airfoils are also described. Very good agreement was in general observed between the measurements in PLCT and in other high quality wind tunnels. Some deviations were seen, but they were mainly attributed to the differences in separation on the airfoil. Apart from the benchmarking, this paper also highlights the challenges in testing airfoils in general such as obtaining 2D flow on thick airfoils that inherently shows separated flow and how to make adapters for airfoils tested in other wind tunnels.

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Daneshmand, Saeed, Cyrus Aghanajafi, and Hossein Shahverdi. "Investigation of rapid manufacturing technology with ABS material for wind tunnel models fabrication." Journal of Polymer Engineering 32, no. 8-9 (December 1, 2012): 575–84. http://dx.doi.org/10.1515/polyeng-2012-0089.

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Abstract Nowadays, several procedures are used for manufacturing wind tunnel models. These methods include machining, casting, molding and rapid prototyping. Raw materials such as metals, ceramics, composites and plastics are used in making these models. Dimension accuracy, surface roughness and material strength are significant parameters which are effective in wind tunnel manufacturing and testing. Wind tunnel testing may need several models. Traditional methods for constructing these models are both costly and time consuming. In this research, a study has been undertaken to determine the suitability of models constructed using rapid manufacturing (RM) methods for use in wind tunnel testing. The aim of this research is to improve the surface roughness, dimensional accuracy and material strength of rapid manufacturing models for testing in wind tunnels. Consequently, the aerodynamic characteristics of three models were investigated and compared. The first model is made of steel, the second model from FDM-M30, and the third model is a hybrid model. Results show that metal models can be replaced by hybrid models in order to measure aerodynamic characteristics, reduce model fabrication time, save fabrication cost and also to verify the accuracy of aerodynamic data obtained in aerospace industry.

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Hasan, Mohammed Munif, and Shabudin Mat. "Data Reduction Analysis on UTM-LST External Balance." International Journal for Research in Applied Science and Engineering Technology 10, no. 10 (October 31, 2022): 952–59. http://dx.doi.org/10.22214/ijraset.2022.47097.

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Abstract: The effective use of wind-tunnel testing in determining aerodynamic properties of a body is very much dependent upon the reliability and speed with which wind-tunnel data can be reduced. The operating efficiency of the wind tunnels is substantially improved by the capability of providing lower aerodynamic coefficients in real time, or online, which decreases the expensive wind-tunnel time necessary for each test. This paper describes a system for presenting reduced wind-tunnel data in real time for UTM-LST. The requirements for data-handling equipment and data reduction procedures for wind tunnels are quite diverse, and depend upon the wind tunnel design and the type of tests for which they are used. The supersonic wind tunnels mentioned in this description have a variety of force-balance systems and are used for force tests, pressure tests, and other research projects. Consequently, the problems associated with in order to solve this diversity we build a computerized program where we can find the transformation of axis and aerodynamic characteristics at ease. This program can find the values of different aerodynamic coefficients with certain angle of attacks.

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FUKAYA, HIROSHI. "BUILDING SMALL WIND TUNNEL AND TESTING." Journal of the Visualization Society of Japan 15, Supplement1 (1995): 309–10. http://dx.doi.org/10.3154/jvs.15.supplement1_309.

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Liu, Tianshu, L. N. Cattafesta, R. H. Radeztsky, and A. W. Burner. "Photogrammetry Applied to Wind-Tunnel Testing." AIAA Journal 38, no. 6 (June 2000): 964–71. http://dx.doi.org/10.2514/2.1079.

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Majowiecki, Massimo, and Nicola Cosentino. "Design Assisted By Wind Tunnel Testing." IABSE Symposium Report 97, no. 18 (January 1, 2010): 1–8. http://dx.doi.org/10.2749/222137810796025627.

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Ruyten, Wim. "More Photogrammetry for Wind-Tunnel Testing." AIAA Journal 40, no. 7 (July 2002): 1277–83. http://dx.doi.org/10.2514/2.1814.

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Liu, Tianshu, L. N. Cattafesta III, R. H. Radeztsky, and A. W. Burner. "Photogrammetry applied to wind-tunnel testing." AIAA Journal 38 (January 2000): 964–71. http://dx.doi.org/10.2514/3.14504.

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Ruyten, W. "More photogrammetry for wind-tunnel testing." AIAA Journal 40 (January 2002): 1277–83. http://dx.doi.org/10.2514/3.15194.

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Reid, W. M., and J. Travers. "Wind tunnel testing of sports stadiums." Construction and Building Materials 5, no. 3 (September 1991): 120–22. http://dx.doi.org/10.1016/0950-0618(91)90061-o.

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Cooper, Kevin R., Edzard Mercker, and Jürg Müller. "The necessity for boundary corrections in a standard practice for the open-jet wind tunnel testing of automobiles." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 231, no. 9 (April 26, 2017): 1245–73. http://dx.doi.org/10.1177/0954407017701287.

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This paper is intended to provide a summary of the necessary adjustments required for road-representative open-jet wind tunnel measurements on automobiles. The open-jet wind tunnel provides accurate measurements, but they are made in a finite-sized jet that differs from the unconfined open-road conditions. Furthermore, measurements on a given automobile made in different open-jet wind tunnels disagree with each other, and with measurements in closed-wall wind tunnels that were corrected for the influences of their solid boundaries. There appears to be reticence at some company levels to making ‘corrections’ to open-jet measurements. Perhaps non-specialist managers think that the need for a ‘correction’ means an erroneous measurement. It does not! Any high-quality wind tunnel measurement is accurate, but it needs to be ‘calibrated’ to on-road conditions through an appropriate set of procedures. Closed-wall wind tunnels measure higher drag coefficients, in comparison with those in an unconstrained on-road flow. Open-jet wind tunnels frequently measure a lower value. The closed-wall adjustments lower the drag coefficient to the unconstrained value. Open-jet adjustments should also adjust the drag coefficient to the same unconstrained value. This paper explores the range of effects from the finite jet and elucidates the effectiveness of a two-measurement correction procedure. It is shown that not every data point must be measured twice, only a small selected subset. Since approximately 20% of tunnel occupancy is in the fan-on condition, then the additional cost of correct accurate on-road-equivalent data is low.

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Ishiguro, Mitsuo, and Yoshiaki Miyake. "Parametric Study for Directional Stability of Tumbling Plates by Wind Tunnel Testing." Journal of the Institute of Industrial Applications Engineers 10, no. 1 (January 25, 2022): 1–10. http://dx.doi.org/10.12792/jiiae.10.1.

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Kuester, Matthew S., Kenneth Brown, Timothy Meyers, Nanyaporn Intaratep, Aurélien Borgoltz, and William J. Devenport. "Wind Tunnel Testing of Airfoils for Wind Turbine Applications." Wind Engineering 39, no. 6 (December 2015): 651–60. http://dx.doi.org/10.1260/0309-524x.39.6.651.

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Flamand, Olivier, Philippe Delpech, Pierre Palier, and Jean-Paul Bouchet. "Benefit of Wind Tunnels with Large Test Sections for Wind Engineering Applications." Mathematical Modelling in Civil Engineering 15, no. 2 (June 1, 2019): 14–19. http://dx.doi.org/10.2478/mmce-2019-0005.

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Abstract Atmospheric Boundary layer wind tunnels (ABLWT) dedicated to building safety and comfort have been operated by CSTB in Nantes since 1971. Because ABLWT only deal with reduced scale models of real structures, the necessity of a larger wind tunnel, the Jules Verne Climatic wind tunnel (CWT), able to reproduce extreme wind loads on real scale structures arose in the years 80. Hence, it became a major European facility operating for improvement of the safety, quality and environmental impact of buildings and civil engineering works as well as products from industrial fields (transportation, energy…) with respect to strong winds and other climatic hazards. Both wind tunnel types, the ABLWT and the CWT are complementary and used for studying the effect of wind on the same structures at two different scales, when the effect of wind scaling is important. During the 2018 year, several modifications were made to the CWT facility. The atmospheric test section of the existing facility was elongated preserving the initial advantages, very large test section (approximately 120 m2) with wind velocity performance compatible with many applications (up to 90 km/h). This new test section makes it possible to simulate turbulent wind and driving rain testing. The sand winds capabilities have been maintained in the new design, despite the closed loop configuration, by fitting a filtering. The modifications of the wind tunnel geometry now offer a long test section upstream the turning vanes where a whole set of new tests can be carried out, as windmill field, natural ventilation of urban environments, slender structures (large bridges, pylons, cable transport systems,)

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Nagai, Shinji, and Hidetoshi Iijima. "Uncertainty Identification of Supersonic Wind-Tunnel Testing." Journal of Aircraft 48, no. 2 (March 2011): 567–77. http://dx.doi.org/10.2514/1.c031159.

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Scanlan, R. H. "Book Review: Low-Speed Wind Tunnel Testing." Journal of Engineering Mechanics 125, no. 8 (August 1999): 986. http://dx.doi.org/10.1061/(asce)0733-9399(1999)125:8(986).

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Collins, S. W., B. W. Westra, J. C. Lin, G. S. Jones, and C. H. Zeune. "Wind tunnel testing of powered lift, all-wing STOL model." Aeronautical Journal 113, no. 1140 (February 2009): 129–37. http://dx.doi.org/10.1017/s0001924000002840.

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Abstract Short take-off and landing (STOL) systems can offer significant capabilities to warfighters and, for civil operators thriving on maximising efficiencies they can improve airspace use while containing noise within airport environments. In order to provide data for next generation systems, a wind tunnel test of an all-wing cruise efficient, short take-off and landing (CE STOL) configuration was conducted in the National Aeronautics and Space Administration (NASA) Langley Research Center (LaRC) 14ft by 22ft Subsonic Wind Tunnel. The test’s purpose was to mature the aerodynamic aspects of an integrated powered lift system within an advanced mobility configuration capable of CE STOL. The full-span model made use of steady flap blowing and a lifting centerbody to achieve high lift coefficients. The test occurred during April through June of 2007 and included objectives for advancing the state-of-the-art of powered lift testing through gathering force and moment data, on-body pressure data, and off-body flow field measurements during automatically controlled blowing conditions. Data were obtained for variations in model configuration, angles of attack and sideslip, blowing coefficient, and height above ground. The database produced by this effort is being used to advance design techniques and computational tools for developing systems with integrated powered lift technologies.

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Hui, Zhu, and Zhi Gang Yang. "Design for Wind Tunnel Testing of Scaled Model by CFD Method." Applied Mechanics and Materials 275-277 (January 2013): 567–71. http://dx.doi.org/10.4028/www.scientific.net/amm.275-277.567.

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The numerical investigations presented in this paper deal with wind tunnel testing scheme design for 1/4 scaled MIRA model including supporting system. Based on the structure of aerodynamic and aero-acoustic full scale wind tunnel, using computational fluid dynamics (CFD), focus on MIRA model and supporting system, the drag force of scaled models and supporting system were calculated. By comparing with the wind tunnel testing results and drag force coefficient of reference, it is certain that the wind tunnel testing scheme is available and effective and that the value calculated by CFD is in good agreement with experiments.

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Allen, N., S. Lawson, M. Maina, and J. Alderman. "Qualification of the ARA TWT for laminar flow testing." Aeronautical Journal 118, no. 1209 (November 2014): 1349–58. http://dx.doi.org/10.1017/s0001924000010009.

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Abstract The current drive towards reducing the environmental impact of aircraft necessitates the ability to evaluate techniques for promoting natural laminar flow in a large scale wind tunnel facility. A test was undertaken on the M2355 variable sweep model to obtain temperature sensitive paint (TSP) and hot-film data from which the transition locations at a range of sweep angles and flow conditions could be identified. The TSP technique has been shown to be a reliable method for determining transition on suitably treated wind tunnel models. Pressure data were also acquired and interpolated to provide the input to the laminar boundary layer code, BL2D, the output from which was used in the linear stability analysis code, CoDS, to calculate the N-factor for the ARA TWT (Transonic Wind Tunnel) facility. Two sets of N-factors were calculated, firstly using incompressible analysis with stationary crossflow and secondly using compressible analysis with travelling crossflow. In both analyses the Tollmien-Schlichting and crossflow cases were calculated together, rather than separating the cases before running the analysis. The resulting N-factors indicate a degree of scatter typical for experimental data. The N-factor based on incompressible theory for crossflow was found to be approximately 7 and for Tollmien-Schlichting (T-S), approximately 11. The results of the wind tunnel test and the analysis carried out are considered to be the first steps towards establishing a methodology for performance testing, in atmospheric tunnels such as the TWT, for aircraft designed to have significant regions of laminar flow. The project has also provided a body of experimental test data which will be valuable for future research into development and validation of laminar flow methods.

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Nanos, Emmanouil M., Kutay Yilmazlar, Alex Zanotti, Alessandro Croce, and Carlo L. Bottasso. "Wind tunnel testing of a wind turbine in complex terrain." Journal of Physics: Conference Series 1618 (September 2020): 032041. http://dx.doi.org/10.1088/1742-6596/1618/3/032041.

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Bottasso, Carlo L., Filippo Campagnolo, and Vlaho Petrović. "Wind tunnel testing of scaled wind turbine models: Beyond aerodynamics." Journal of Wind Engineering and Industrial Aerodynamics 127 (April 2014): 11–28. http://dx.doi.org/10.1016/j.jweia.2014.01.009.

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Green, Johnathan, and Subajan Sivandran. "Wind tunnel testing and computational fluid dynamics in FLNG and floating production system design." APPEA Journal 56, no. 2 (2016): 613. http://dx.doi.org/10.1071/aj15119.

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Demonstrating how numerical modelling, such as computational fluid dynamics (CFD), can be used to validate results from detailed physical wind tunnel models of FLNG vessels and floating systems is the objective of this extended abstract. 3D rapid prototyping is used to build detailed physical wind tunnel models. This physical model (normally of an approximate scale of 1:200) is then placed in a wind tunnel facility to measure the time histories of the wind loads for a full range of wind directions and a range of drafts. CFD is then used to validate the wind tunnel modelling results. Numerical modelling can also be used to analyse a number of different issues such as the impact of turbine exhaust dispersion, and turbulence on helicopter operations and resulting helideck availability. This extended abstract discusses the importance of wind tunnel testing and numerical modelling during the design phase. The idea that numerical modelling does not replace pure theoretical or experimental results, but acts to complement them with gaining a greater overall picture, will be highlighted. Findings will be presented to discuss the advantages and disadvantages of both approaches, and highlight results such as wind shear and turbulence impacts being best calculated through wind tunnel testing. The extended abstract demonstrates that, ideally during the design process, wind tunnel testing should be followed by numerical modelling to interpolate results.

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Hubová, Oľga, and Peter Lobotka. "The Multipurpose New Wind Tunnel STU." Civil and Environmental Engineering 10, no. 1 (May 1, 2014): 1–9. http://dx.doi.org/10.2478/cee-2014-0001.

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Abstract BLWT STU tunnel, which is currently in test mode, will in its two measuring sections allow to prepare measurements with laminar and turbulent wind flow. The front section will fulfill technical parameters of steady flow for testing sectional models and dynamically similar models. In the rear operating section it is necessary to reproduce correctly the roughness of the earth surface covering different terrain categories and to prepare boundary layer suitable for experimental testing. Article deals with the brief description of the preparation and testing laminar flow and boundary layer for the urban terrain, which was simulated with rough elements and barriers of different heights. The attention is focused in getting get at least 1 meter height of boundary layer, which allows to optimize scale similarity of model.

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Stenfelt, G., and U. Ringertz. "Design and construction of aeroelastic wind tunnel models." Aeronautical Journal 119, no. 1222 (December 2015): 1585–99. http://dx.doi.org/10.1017/s0001924000011416.

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AbstractThe design and building of accurately scaled aeroelastic wind-tunnel models is difficult, time consuming and very costly. With the increasing usefulness of computational methods for predicting aeroelastic phenomena, few complex models have been built in recent years. New fighter aircraft projects are also becoming more and more scarce, and transport aircraft have essentially the same configuration since half a decade. This also significantly reduces the need for aeroelastic wind-tunnel models. However, there still is an interest in the results from aeroelastic testing. In some cases new and radical configurations may warrant wind-tunnel testing and in other cases complex phenomena arising in fight testing may need carefully performed experiments to resolve problems. However, there is definitely a trend towards building models and performing testing in the support of the development of computational methods.The developments in computer technology do not only improve the computational methods for aeroelasticity. Modern Computer Aided Design and Manufacturing techniques can significantly improve the quality and efficiency of the design and build process for aeroelastic models. There have also been some recent improvements in measurement techniques which have proven very useful for testing of aeroelastic wind-tunnel models. The paper will present some new design and build techniques developed for the manufacturing of a large scale wind-tunnel model of a canard delta wing fighter aircraft configuration. In the build process fiber-reinforced composites will be used, hence, challenges and possible solutions concerning the ability to produce a model with well defined material properties and fiber angles will be discussed. Further challenges arise when both measurement equipment and adjustable control surfaces should be attached inside the model using techniques that are possible to describe with computational methods. In addition, equipment, such as pressure taps, and control surface mechanics need to fit and function in a flexible structure. As a result, the above requirements will lead to necessary compromises in the design, hence, the paper will present the choices taken during the build process and for which reasons. The use of an optical positioning measurement system will also be discussed for both the validation of model properties and non-contact measurement of model deformations during wind-tunnel testing.

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Yu, Mei, Hai Li Liao, Ming Shui Li, Cun Ming Ma, and Ming Liu. "Analysis of Flutter Stability of the Xihoumen Bridge in the Completed Stage." Advanced Materials Research 243-249 (May 2011): 1629–33. http://dx.doi.org/10.4028/www.scientific.net/amr.243-249.1629.

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Aerodynamic stability is an issue in the wind-resistant design of long-span bridges, flutter is an aerodynamic instability phenomenon that occurs due to interactions between wind and structural motion. The Xihoumen Bridge is the second long suspension bridge in the world, the aeroelastic performance of the Xihoumen Bridge is investigated by wind tunnel testing and an analytical approach. In the case, wind-tunnel testing was performed using an aeroelastic full model of the bridge, and two section models of the bridge. Flutter derivatives of bridge decks are routinely extracted from wind tunnel section model experiments for the assessment of performance against wind loading, the analytical method used here were a two-dimensional flutter analysis and a multi-mode analysis in the frequency domain. The analytical results were compared with the wind tunnel test data; it showed that the flutter analysis results were good agreement with the wind-tunnel test data.

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Campagnolo, Filippo, Robin Weber, Johannes Schreiber, and Carlo L. Bottasso. "Wind tunnel testing of wake steering with dynamic wind direction changes." Wind Energy Science 5, no. 4 (October 8, 2020): 1273–95. http://dx.doi.org/10.5194/wes-5-1273-2020.

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Abstract. The performance of an open-loop wake-steering controller is investigated with a new unique set of wind tunnel experiments. A cluster of three scaled wind turbines, placed on a large turntable, is exposed to a turbulent inflow and dynamically changing wind directions, resulting in dynamically varying wake interactions. The changes in wind direction were sourced and scaled from a field-measured time history and mirrored onto the movement of the turntable. Exploiting the known, repeatable, and controllable conditions of the wind tunnel, this study investigates the following effects: fidelity of the model used for synthesizing the controller, assumption of steady-state vs. dynamic plant behavior, wind direction uncertainty, the robustness of the formulation in regard to this uncertainty, and a finite yaw rate. The results were analyzed for power production of the cluster, fatigue loads, and yaw actuator duty cycle. The study highlights the importance of using a robust formulation and plant flow models of appropriate fidelity and the existence of possible margins for improvement by the use of dynamic controllers.

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Koreanschi, A., O. Sugar-Gabor, and R. M. Botez. "Numerical and experimental validation of a morphed wing geometry using Price-Païdoussis wind-tunnel testing." Aeronautical Journal 120, no. 1227 (May 2016): 757–95. http://dx.doi.org/10.1017/aer.2016.30.

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ABSTRACTAn experimental validation of an optimised wing geometry in the Price-Païdoussis subsonic wind tunnel is presented. Two wing models were manufactured using optimised glass fibre composite and tested at three speeds and various angle-of-attack. These wing models were constructed based on the original aerofoil shape of the ATR 42 aircraft and an optimised version of the same aerofoil for a flight condition of Mach number equal to 0.1 and angle-of-attack of 0°. The aerofoil's optimisation was realised using an ‘in-house’ genetic algorithm coupled with a cubic spline reconstruction routine, and was analysed using XFoil aerodynamic solver. The optimisation was concentrated on improving the laminar flow on the upper surface of the wing, between 10% and 70% of the chord. XFoil-predicted pressure distributions were compared with experimental data obtained in the wind tunnel. The transition position was estimated from the experimental pressure data using a second derivative methodology and was compared with the transition predicted by XFoil code. The results have shown the agreement between numerical and experimental data. The wind-tunnel tests have shown that the improvement of the laminar flow of the optimised wing is higher than the value predicted numerically.

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Jia, Sijia, Zhenkai Zhang, Haibo Zhang, Chen Song, and Chao Yang. "Wind Tunnel Tests of 3D-Printed Variable Camber Morphing Wing." Aerospace 9, no. 11 (November 9, 2022): 699. http://dx.doi.org/10.3390/aerospace9110699.

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This paper introduces the realization and wind tunnel testing of a novel variable camber wing equipped with compliant morphing trailing edges. Based on the aerodynamic shape and compliant mechanisms that were optimized in advance, a wind tunnel model called mTE4 was developed, in which the rigid leading edge, rigid wing box, and compliant trailing edge were manufactured by 3D printing technology using three different materials. Due to difficulties in the detailed design of a small-scale model, special attention is devoted to the implementation procedure. Additionally, the static and dynamic characteristics of the proposed wind tunnel model were evaluated by ground tests, and the aerodynamic characteristics were evaluated by numerical methods. Then, the aerodynamic performance and the static aeroelastic deformation of the compliant trailing edge were investigated in a low-speed wind tunnel. The load-bearing ability of the proposed compliant morphing trailing edge device was validated and the continuous outer mold surface was found to persist throughout the entire testing period. Notably, a maximum deflection range of 37.9° at the airspeed of 15 m/s was achieved. Additionally, stall mitigation was also achieved by periodically deflecting the morphing trailing edge, enabling a stall angle delay of approximately 1° and 13% increase in post-stall lift coefficient. Finally, the development procedure was validated by comparing the lift between numerical and experimental results.

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Tran, Anh Tien, and Nam Ngoc Linh Hoang. "Design and installation of vibration testing system for spring mounted model of wing." Science and Technology Development Journal 18, no. 4 (December 30, 2015): 179–87. http://dx.doi.org/10.32508/stdj.v18i4.1004.

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This paper presents the design and installation of measuring vibration system in wind tunnel area 1m x 1m. The theoretical analysis of the spring structure in this model help we possible to design a system for wind tunnel by yourself with suitable area, wind speed as well as survey wing model to obtain results desire. This system helps us to observe the oscillation of wing survey by eyes, but to know exactly how wing fluctuates, also the pitching angle of wing, we use ultrasonic sensors to measure the distance variation, will be presented in more detail in the text. At the same time, the article also shows how to make a simple and durable wing model with NACA 0015 airfoil - wing model will be surveyed ranged in system above. The aerodynamic phenomena affect to the vibration of the wing are also mentioned and overcome in the design of the wing. Finally we process the data after measured to see the similarities between the experiment and the theoretical dynamics of aviation.

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Daryanto, Yanto, Joko Purwono, and Subagyo. "Wing configuration on Wind Tunnel Testing of an Unmanned Aircraft Vehicle." Journal of Physics: Conference Series 1005 (April 2018): 012032. http://dx.doi.org/10.1088/1742-6596/1005/1/012032.

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Ghazal, Tarek, Moustafa Aboutabikh, Haitham Aboshosha, and Mohamed Abdelwahab. "Thunderstorm wind load evaluation on storm shelters using wind tunnel testing." Engineering Structures 262 (July 2022): 114350. http://dx.doi.org/10.1016/j.engstruct.2022.114350.

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40

Zaghi, S., R. Muscari, and A. Di Mascio. "Assessment of blockage effects in wind tunnel testing of wind turbines." Journal of Wind Engineering and Industrial Aerodynamics 154 (July 2016): 1–9. http://dx.doi.org/10.1016/j.jweia.2016.03.012.

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Cooper, K. R. "The wind tunnel simulation of wind turbulence for surface vehicle testing." Journal of Wind Engineering and Industrial Aerodynamics 38, no. 1 (June 1991): 71–81. http://dx.doi.org/10.1016/0167-6105(91)90028-u.

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Fu, Ji-yang, Jiu-rong Wu, and Shu-guo Liang. "Wind tunnel testing of wind pressures on a large gymnasium roof." Journal of Central South University 18, no. 2 (April 2011): 521–29. http://dx.doi.org/10.1007/s11771-011-0726-2.

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Katz, Joseph, and Robert Walters. "Effects of large blockage in wind-tunnel testing." Journal of Aircraft 32, no. 5 (September 1995): 1149–52. http://dx.doi.org/10.2514/3.46852.

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Gopinath, L., and S. Ravishankar. "Manufacturability of Aircraft Winglet for Wind Tunnel Testing." Materials Science Forum 830-831 (September 2015): 100–103. http://dx.doi.org/10.4028/www.scientific.net/msf.830-831.100.

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The form, shape and dimensions of the scaled down winglet model become small and thin bringing complexity to manufacturing. The trailing edge tapers to a thickness varying from 0.065mm to 0.099mm along its length. The mounting portion of the winglet is provided with a close tolerance having a slot gap of 5mm and a depth of 35 mm with an angle. Additionally, wind tunnel models require good surface finish on the aerodynamic surfaces and this involves adopting a manufacturing strategy with a control over on the metal cutting parameters to be implemented on a three axes CNC machining centre. The winglet surface is divided into segments in order to handle the cutting forces on the varying aerodynamic cross section. Various metal cutting parameters such as tool path, cutter diameter, feed rate, depth of cut, spindle speed, etc., are evaluated by monitoring segments where the metal cutting is carried out [1] and flow of chips observed. Fixtures and lugs are planned effectively to accommodate the machining of the angular slot in a three axes machining centre itself. Routing of operations to handle the varying thin sections and realisation of the close tolerance slot has enabled a reliable manufacturing approach in an economical way.

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Mahmoud, N. H., A. A. El-Haroun, E. Wahba, and M. H. Nasef. "SAVONIUS ROTOR PROTOTYPE BASED ON WIND TUNNEL TESTING." ERJ. Engineering Research Journal 34, no. 1 (January 1, 2011): 27–35. http://dx.doi.org/10.21608/erjm.2011.67254.

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Chang, Byeong-Hee, Bongzoo Sung, and Keun-Shik Chang. "Unsteady adaptive wall models for wind-tunnel testing." AIAA Journal 33, no. 8 (August 1995): 1536–38. http://dx.doi.org/10.2514/3.12584.

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Allen, Richard M. "Tone injected nacelle for aeroacoustic wind tunnel testing." Journal of the Acoustical Society of America 88, no. 4 (October 1990): 2050. http://dx.doi.org/10.1121/1.400169.

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Krause, Joshua S., Alfram V. Bright, Mark J. Moeller, Judith M. Gallman, and Robert D. White. "Micromachined reconfigurable microphone array for wind tunnel testing." Journal of the Acoustical Society of America 129, no. 4 (April 2011): 2674. http://dx.doi.org/10.1121/1.3588960.

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ul-Haque, Anwar, Waqar Asrar, Ashraf Ali Omar, Erwin Sulaeman, and JS Mohamed Ali. "Wind tunnel testing of hybrid buoyant aerial vehicle." Aircraft Engineering and Aerospace Technology 89, no. 1 (January 3, 2017): 99–105. http://dx.doi.org/10.1108/aeat-06-2015-0165.

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Mark, D., C. P. Lyons, S. L. Upton, and L. C. Kenny. "Wind tunnel testing of personal inhalable aerosol samplers." Journal of Aerosol Science 28, no. 2 (March 1997): 331. http://dx.doi.org/10.1016/s0021-8502(97)86831-0.

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Journal articles on the topic 'Wind tunnel testing'

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