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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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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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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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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Shahidin, Haziq Idraki, Mohd Rosdzimin Abdul Rahman, Azam Che Idris, and Mohd Rashdan Saad. "3D Printed Models vs Conventional Models: Comparison of Aerodynamic Performance for Wind Tunnel Experiments." Jurnal Kejuruteraan si4, no. 2 (October 31, 2021): 101–4. http://dx.doi.org/10.17576/jkukm-2021-si4(2)-15.

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Traditionally, wind tunnel models are made of metal and the processes are very expensive. Since then, many researchers have been looking for new alternatives, hence 3D printing technology is the solution. Under right test conditions, 3D printed parts could be tested in a wind tunnel to get the aerodynamic performances. By using 3D printing technology, the cost and time can be significantly reduced to produce the wind tunnel models. This investigation was done to compare the aerodynamic performances which are drag and lift forces of the existing wind tunnel metal models with 3D printed wind tunnel models. Polylactic acid (PLA) was used as the printing materials by using two 3D printers which are Poseidon X and CR-10 S5. The wind tunnel testing covered the wind speed in the range of 0.57 m/s to 10.35 m/s at angle of-attack of 0°. Results from experiments show that the drag and lift forces of the 3D printed models show very close similarities with the metal models. It can be concluded that the wind tunnel models produced by using 3D printing technology can be used in wind tunnels for early testing.

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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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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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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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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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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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Jayawant, Shlok, Yuvraj Tiwari, Sarfaraz Khan, and Christy Pillay. "Design and Construction of a cost-efficient Laminar Flow Wind Tunnel for Aerodynamic Testing." International Scientific Journal of Engineering and Management 04, no. 03 (March 13, 2025): 1–6. https://doi.org/10.55041/isjem02370.

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The intention of this project is to design and build a cost-efficient laminar flow wind tunnel to test airfoil performance characteristics. While there are cost-efficient wind tunnels available for learning purposes, they are usually only designed to show the visual representation of airflow over the airfoil. This project will create accurate and repeatable measurements of performance characteristics, making it a budget friendly solution for college level research labs. The wind tunnel will be designed using CAD and scientifically tested for laminar and uninterrupted flow. The main measurement of lift/drag will come from load cells with an Arduino microcontroller measuring the amount of force exerted on the airfoil. When placed in the wind tunnel, the load cells situated on the airfoil will sense real- time pressure exerted on it, which can be measured in real-time as a measurement of static pressure deviation. Furthermore, this wind tunnel will serve as an enhancement for analyzing angle of attack relative to airfoil efficiency. Results will be analyzed relative to the angle of attack and flow separation, which are two of the most important factors for accurate airfoil comprehension in the aerospace industry. Index Terms: Aerodynamic testing, Airfoil performance, Arduino-based measurement, Laminar flow wind tunnel, Lift and drag analysis.

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Setiawan, M. Yasep, Andre Kurniawan, Ichsan, Toto Sugiarto, Nuzul Hidayat, Edy Susanto, Masykur, and Miswardi. "Subsonic Wind Tunnels Air Speed Control Devices Base on Arduino Controller." E3S Web of Conferences 500 (2024): 03026. http://dx.doi.org/10.1051/e3sconf/202450003026.

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This study discusses the process of making an airspeed control device for wind tunnels using Arduino as the main component of the controller unit. Wind tunnel testing is carried out at varying airspeeds to obtain optimal results. The fan motor is not equipped with an air speed controller as an airflow generator. This research aims to make a tool that can control wind tunnel airspeed according to the testing needs. This research was conducted using the research and development method. The power supply voltage output is set at 11.19 Volts as the Arduino voltage source, and for other components such as LCDs, servo motors, relay modules, and anemometer sensors supplied from the Arduino mainboard plus and arranged in parallel with the power supply source reduced using a stepdown to 5.069 Volts. This subsonic wind tunnel's airflow speed control device can regulate the speed from 10 m/s to 13 m/s stably. This speed meets the requirements of a subsonic wind tunnel and can be used to visualize the airflow in the wind tunnel.

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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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Vuković, Đorđe, and Dijana Damljanović. "A technique for reducing supersonic transient loads on internal wind tunnel balances." Tehnika 79, no. 2 (2024): 177–84. http://dx.doi.org/10.5937/tehnika2402177v.

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Design of slender supersonic missiles requires a comprehensive experimental support in the form of wind tunnel data for a wide range of flight parameters (angle of attack and Mach number). However, in supersonic wind tunnel testing, the problem exists of transient loads at the times of the starting and stopping of the supersonic flow. In the environments of pronounced transient loads, characteristic of blowdowin wind tunnels like the T-38 of the Military technical Institute in Belgrade, it is necessary to provide control of the use of internal wind tunnel balances in the permitted design load ranges. The presented technique is related to the definition and implementation of a methodology for reducing the transient loads on wind tunnel balances in supersonic wind tunnel tests. By limiting the clearance between the model and its tail support (sting) to a magnitude which permits normal tests, but results in model-support contact during the excessive loads, part of the loads is transferred to the support sting, relieving the balance. The technique improves control over the wind tunnel test process, improves measurement accuracy and prevents damage to sensitive instrumentation (wind tunnel balances).

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Abdel Aziz, Salem S., Essam B. Moustafa, and Abdel-Halim Saber Salem Said. "Experimental Investigation of the Flow, Noise, and Vibration Effect on the Construction and Design of Low-Speed Wind Tunnel Structure." Machines 11, no. 3 (March 7, 2023): 360. http://dx.doi.org/10.3390/machines11030360.

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A wind tunnel is needed for a lot of research and model testing in the field of engineering design. Commercial wind tunnels are large and expensive, making them unsuitable for small-scale aerodynamic model testing. This work aims to experimentally investigate the effects of flow, noise, and vibration on constructing and designing a low-speed wind tunnel structure. The flow uniformity in the wind tunnel has been tested by measuring the velocity profiles inside the empty test section with a pitot-static tube at various fan frequencies. The experiment results showed a good flow uniformity of more than 90% across the test section area, and the maximum wind velocity achieved was about 25.1 m/s. Due to the stability of the flow near the exit test section, the vibration measurement revealed that the entrance portion has larger vibration fluctuations than the exit part. Furthermore, as the axial fan frequency increases, the noise level increases. At 40 Hz, the noise level enters the hazardous zone, which has an impact on the person who performs the measurement process. The resonance of the wind tunnel structure is an important measurement test that affects vibration measurement.

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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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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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Yang, Aiwei, Dawei Liu, Guangwei Xiang, and Gun Li. "Design of cryogenic balance temperature control system based on MCGS and PLC and analysis of its influence relationship." Journal of Physics: Conference Series 2993, no. 1 (April 1, 2025): 012024. https://doi.org/10.1088/1742-6596/2993/1/012024.

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Abstract To address the issue of slow temperature adjustment in cryogenic balance, which severely affects the efficiency of wind tunnel tests, this study investigates the temperature control system for cryogenic balance. Considering the wide temperature range and deep cooling requirements of cryogenic wind tunnels, a comprehensive design of the temperature cryogenic was developed. Based on MCGS and PLC, the first domestically developed cryogenic balance temperature control system was implemented. After installation, equipment testing and wind tunnel experiments were conducted. The experimental results indicate that the newly developed system achieves stable temperature control from room temperature to 110 K, which operates reliably, conserves energy, and significantly improves the economic efficiency of cryogenic wind tunnel tests. Furthermore, an analysis of the relationships between balance temperature range, system pressure, and wind tunnel temperature on the system’s thermal performance during tests provides valuable insights for precise control in future applications.

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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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Poddaeva, Olga. "RESULT VERIFICATION FOR NUMERICAL MODELING OF WIND EFFECTS ON UNIQUE BUILDINGS AND STRUCTURES." Architecture and Engineering 9, no. 2 (June 28, 2024): 79–85. http://dx.doi.org/10.23968/2500-0055-2024-9-2-79-85.

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Introduction: Despite the fact that wind tunnel testing is quite expensive and time-consuming, physical modeling in wind tunnels remains the primary method for determining wind effects on unique buildings and structures. Computational fluid dynamics (CFD) provides more variability, calculations are performed faster and at a lower cost. However, the issue of accuracy of integral characteristics obtained as a result of numerical modeling and, accordingly, verification procedure remains open. Currently, when using numerical modeling results in structural aerodynamics, it is mandatory to verify them with experimental data. In recent years, studies have explored the CFD potential for accurate wind load predictions, but there have not been studies presenting a comprehensive description and implementation of a verification and validation system to analyze wind effects on unique buildings and structures. The purpose of the study was to compare the CFD results with the wind tunnel test data for three different objects, analyze the results, and propose a method for verification and validation of CFD analysis of wind effects on unique buildings and structures. The following methods were used: physical testing of models of unique buildings and structures in a wind tunnel, including a detailed method of experimental studies to determine integral aerodynamic characteristics, as well as numerical modeling of wind effects using ANSYS. Numerical modeling was performed in two setups: with and without virtual wind tunnel modeling. As a result, it is shown that virtual wind tunnel modeling makes it possible to achieve better data consistency when verifying numerical modeling results with physical modeling data, and the proper use of numerical modeling technology can significantly reduce the time and cost of experimental studies in a wind tunnel and/or reduce the design time by decreasing the number of considered loading scenarios.

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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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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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Yanel, Karnova, and Asmara Yanto. "Design and Manufacturing of Wind Tunnel for Turbine Impeller Airfoil Testing." Jurnal Teknik Mesin 12, no. 2 (October 31, 2022): 124–30. http://dx.doi.org/10.21063/jtm.2022.v12.i2.124-130.

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In this study, the design of a wind tunnel was carried out to observe airflow through an airfoil, streamlines and turbine blades. To accommodate this, in this study a design was made of an open return wind tunnel. In this case, an open circuit wind tunnel type will be made because the construction is simpler and the manufacturing costs are relatively cheaper compared to the closed circuit wind tunnel type. The Wind Tunnel is designed with Open CLosed Wind Tunnel (OCWT) type. The OCWT is designed to consist of fan and housing, diffuser, test section, contraction, honeycomb. The OCWT design uses an operating fan to circulate air into the test section. The maximum air speed in the Test Section is 5 m/s with a flow that is closed to laminar. The recommended diffuser has a dimension of 50 cm on the side that is attached to the test section and 52 cm on the side facing the fan with an inclination angle of 1.79o. The driver uses a 16 inch exhaust fan with a power of 74 W to make the flow in the Test Section stable at a speed of 2 m/s.

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Dr. G.Venkateswarlu and Tejavath Rajesh. "MODELING AND STATIC AND MODAL ANALYSIS OF FUSELAGE BOMBARDIER CRJ 200 AIRCRAFT USING VARIOUS MATERIALS." International Journal of Engineering, Science and Advanced Technology 24, no. 10 (2024): 419–25. http://dx.doi.org/10.36893/ijesat.2024.v24i10.053.

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This study details the low-speed configuration development process of the CRJ-700, focussing on half-model high Reynolds number wind tunnel tests. The procedure included flight testing, wind tunnel testing, and CFD design and analysis. A 7% scale half-model was used for the experimental development of the flaps and slats in the IAR 5 x 5 ft High Reynolds Number wind tunnel. Decisions taken in the wind tunnel result in a brief and successful flight test program, and the results of these tests correlate extremely well with the data from the flight tests.

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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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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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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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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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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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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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Desai, Siddhant, Joseph A. Schetz, Rakesh K. Kapania, and Rikin Gupta. "Wind Tunnel Testing of Tethered Inflatable Wings." Journal of Aircraft 61, no. 6 (November 2024): 1717–34. https://doi.org/10.2514/1.c037437.

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A wind tunnel testing approach for tethered inflatable wings is presented. Use cases for such wings range from airborne wind energy systems to high-altitude communication platforms. The tests were conducted for two tethered inflatable wings, one made out of nylon fabric and the other an ultra-high-molecular-weight polyethylene fabric. They were tested within a speed range of 15–32.5 m/s for three tether attachment configurations. Stereo photogrammetry data, force and moment measurements, and wake pressure measurements were recorded for each speed and test configuration. These measurements provide an experimental database for aeroelastic model validation and comparison with high-fidelity computational fluid dynamics studies. The effects of wing fabric material and tether attachment configurations on aerodynamic performance were explored and found to have a profound impact. These tests also highlight the possibility of passive aeroelastic tailoring of the wing configuration to achieve desired aerodynamic performance in the form of high lift and load alleviation. Some testing challenges and possible sources of measurement uncertainty are also discussed.

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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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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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Syifa Fauziah Rahmani, Nanda, Sugianto Sugianto, and Deden Masruri. "Airflow Velocity Measurement Of Turbular Test Section Based On Rpm Setting Configuration In Open Circuit Subsonic Wind Tunnel." Journal of Applied Mechanical Engineering and Renewable Energy 4, no. 2 (July 25, 2024): 46–54. https://doi.org/10.52158/jamere.v4i2.914.

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Speed measurements in the test section based on the RPM setting configuration of the open-type subsonic wind tunnel with a turbular test section to obtain the properties of the airflow in the test section based on the RPM setting configuration in the open-type subsonic wind tunnel. The simulation process is carried out using software Computational Fluid Dynamics (CFD) , ANSYS Fluent. The simulation process is carried out by the method Moving Reference Frame (MRF) that the fluid phenomenon is moved to move the fan in the wind tunnel to obtain airflow properties in the turbular test section, open-type subsonic wind tunnel. In the testing process, airflow velocity measurements were carried out in the turbular test section of the open-type subsonic wind tunnel using an air velocity measuring instrument, namely anemometer and hotwire. The software Computer Aided Design (CAD), Solidworks, serves to create the geometry of the open-type subsonic wind tunnel and has a turbular test section inspired by the Didacta Italia PN21 D open-type subsonic wind tunnel. The properties that occur in the test section based on the configuration of the RPM setting in the open-type subsonic wind tunnel turbular test section are expected to achieve results to obtain the value of the velocity distribution, pressure distribution and turbulence intensity value so that it is useful and supports the operation and testing process to be carried out in an open-type subsonic wind tunnel with a turbular test section.

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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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Asghar, Umair, Muhammad Anas Wazir, Muhammad Kaleem Wazir, Abbas Khan, Muhammad Usama, and Osama Subhan. "Design and Fabrication of Low-Speed Wind Tunnel (LSWT)." Pakistan Journal of Engineering and Technology 6, no. 4 (February 12, 2024): 23–32. http://dx.doi.org/10.51846/vol6iss4pp23-32.

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The design and fabrication of a low-speed wind tunnel (LSWT), which is a critical component for testing and comprehending aircraft aerodynamics, is presented in this study. Despite the increasing prominence of computational fluid dynamics (CFDs) in manufacturing engineering, wind tunnels remain essential for the intricate development of aircraft and automobile designs with complex flow interactions. Using SolidWorks, we focused on controlling flow turbulence approaching the test section, emphasizing performance and quality parameters. The construction of the wind tunnel used plywood with an axial fan regulating the airspeed, and Arduino facilitated data acquisition. The drag and lift on the Y Clerk Airfoil were quantified by two load cells along the XY-axis, complemented by a Pitot Static Tube and a multitube inclined plane manometer for pressure and velocity calculation. Fusion 360 simulation software was used to analyze pressure and velocity profiles at speeds ranging from 10 to 20 m/s, providing a comprehensive quantitative evaluation of the wind tunnel’s capabilities. By emphasizing both design innovation and quantitative performance metrics, this study underscores the continuing significance of wind tunnels in engineering.

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Auhl, Richard R., Dennis K. McLaughlin, and Philip J. Morris. "Design, assembly and testing of an upgraded aeroacoustics wind tunnel facility." International Journal of Aeroacoustics 23, no. 3-4 (May 9, 2024): 285–98. http://dx.doi.org/10.1177/1475472x241230650.

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The Aeroacoustics Laboratory in the Department of Aerospace Engineering at Penn State currently serves several areas of experimental research. Most notable in the laboratory is the Anechoic Chamber of which the Aeroacoustics Wind Tunnel is an integral part. In recent years the dominant areas of research have included model aircraft exhaust jets and model rotors for helicopter applications involving detailed noise experiments. In the jet noise area, the applications have included aircraft in both flyover and take-off configurations. In the flyover application the air flow surrounding the exhaust jet has a significant effect on the radiated noise and must be simulated to produce experimental results that will be most useful in preliminary design of noise suppression applications. The Aeroacoustics Wind Tunnel at Penn State serves the purpose for this simulation. During aircraft take-off, the aircraft airspeed is in a range exceeding 250 ft per second, or Mach number of over M = 0.22. In the years preceding 2022, the velocity of the free jet flow of the Penn State facility was limited to less than 200 ft/sec. This paper reports on a project to design upgrades to the existing wind tunnel to improve the test section flow velocity to values closer to the 250 ft/sec target. The approach began with a preliminary design of the return flow ducting to convert the open jet, open return wind tunnel to a closed return tunnel. The concept is to make use of the flow energy in the exhaust of the tunnel to boost the input energy to the inlet fan that drives the flow to the test section. An integral part of the preliminary design involved making use of an upgraded flow analysis computer code to predict the gain in test section velocity of the new facility. For the available horsepower of two fans in the facility, the configurations of the existing and upgraded wind tunnel were entered into this analysis code based on a quasi-one-dimensional formulation. The code included empirical data formulated to include the various shapes of the components of the tunnels. The relative flow velocities in each section used simple incompressible continuity to calculate all velocities in the component sections. The average dynamic pressure in each section is calculated from the flow (constant) density and the velocity squared. Each section had a non-dimensional pressure loss parameter calculated from empirical data (from the relevant literature). The basic code (using the Excel algorithms) was based on a predictor-corrector concept in which the calculation was initialized with the estimated velocity and pressure of the flow at the entrance to the test section. The loss in each following section is estimated to determine the loss in the total pressure and the cumulated loss compared to the gains made at the two fans in the circuit. The initial guess is adjusted based on the total pressure value at the end of the circuit. During the related experiments, measurements of the total and dynamic pressure were performed at several joints between sections and compared to the values predicted in the analysis code. Various settings of the horsepower of the drive fans were used and the results were compared to flow measurements for the tunnel configurations (predominantly for the open return and closed return tunnel setups available before and after the upgrade project.) Results of the analysis and experiments are presented and analyzed together with the remaining activities planned for the coming months.

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Tian, Haigang, Tianyi Hao, Chao Liu, Han Cao, and Xiaobiao Shan. "Investigation of a Portable Wind Tunnel for Energy Harvesting." Aerospace 8, no. 12 (December 9, 2021): 386. http://dx.doi.org/10.3390/aerospace8120386.

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Current wind tunnels possess a large space volume and high manufacturing cost, which are not suitable for investigating micro energy harvesters. This paper aims to design and fabricate a small, portable and low-speed wind tunnel for energy harvesting. A wind tunnel structure was first designed, a finite element analyses is then utilized to obtain the airflow velocity and turbulence intensity at the testing section, and the influence of the structural parameters of the wind tunnel on the flow field performance is finally investigated to achieve better performance. An experimental prototype of the wind tunnel was fabricated to verify the simulation results. Results demonstrated that the distribution uniformity and average turbulence intensity at the test section decrease first and then increase with the increase of both the diffuser and contraction lengths. The rectifying and damping effect of the honeycomb increase with increasing porosity and thickness. When the diffuser and contraction lengths are 850 mm and 480 mm, respectively, a better distribution uniformity and a lower turbulence intensity can be achieved. Experimental results were in good agreement with the simulation values. The maximum airflow velocity can reach up to 24.74 m/s, and the minimum error was only 1.23%. The designed wind tunnel achieved low-speed, small, portable and stable functions. This work provides an important guidance for further investigating the piezoelectric energy harvesting.

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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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Hussain, Ihsan Y., Maki H. Majeed, Anmar H. Ali, and Wail S. Sarsam. "DESIGN, CONSTRUCTION AND TESTING OF LOW SPEED WIND TUNNEL WITH ITS MEASUREMENT AND INSPECTION DEVICES." Journal of Engineering 17, no. 06 (December 1, 2011): 1550–65. http://dx.doi.org/10.31026/j.eng.2011.06.20.

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A low speed open circuit wind tunnel has been designed, manufactured and constructed at theMechanical Engineering Department at Baghdad University - College of Engineering. The work is one ofthe pioneer projects adapted by the R & D Office at the Iraqi MOHESR. The present paper describes thefirst part of the work; that is the design calculations, simulation and construction. It will be followed by asecond part that describes testing and calibration of the tunnel. The proposed wind tunnel has a testsection with cross sectional area of (0.7 x 0.7 m2) and length of (1.5 m). The maximum speed is about (70m/s) with empty test section. The contraction ratio is (8.16). Three screens are used to minimize flowdisturbances in the test section. The design philosophy is discussed and methods for wind tunnelcalculation are outlined. Simulation of wind tunnel using ANSYS shows no separation of flow alongwind tunnel. Construction steps are also included in present work.

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Zhao, Xiaoyi, Zhile Shu, and Xiangjun Pei. "Research and Perspectives on Fire-Fighting Systems in Tunnels under Strong Piston Wind Action." Buildings 13, no. 2 (February 4, 2023): 435. http://dx.doi.org/10.3390/buildings13020435.

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Guided by the technical requirements for tunnel fire safety, an overview of tunnel piston wind, combustion models, and full-size and small tunnel fire tests is presented. Firstly, the theoretical model and numerical calculation methods for piston wind tunnel fires are presented from the perspective of numerical simulation. Then, full-scale and small-scale test models for tunnel fires are presented, and the advantages and disadvantages of single-row, multi-row, single-fire source, and multi-fire source test methods are described. Finally, key breakthrough directions for future numerical and experimental research on piston winds and tunnel fires are proposed, specifically the mastery of underground tunnel fire development prediction methods. This involves mastering the full-scene elemental fire testing technology for underground tunnel operation systems; developing multi-channel data acquisition technology for fire tests under the effect of multiple disturbances such as high temperature and high humidity; and mastering the smoke flow law during fires in complex tunnel projects.

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Journal articles on the topic 'Wind tunnel testing'

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