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Journal articles on the topic 'Wind tunnel testing'

Author: Grafiati

Published: 4 June 2021

Last updated: 25 July 2025

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1

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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2

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

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3

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

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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 (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 st

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5

Stalker, R. J. "Modern developments in hypersonic wind tunnels." Aeronautical Journal 110, no. 1103 (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 discusse

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6

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 (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 tun

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7

Greenwell, D. I. "Transonic industrial wind tunnel testing in the 2020s." Aeronautical Journal 126, no. 1295 (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 univ

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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 (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 fo

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9

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 (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 su

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10

Bak, Christian, Anders S. Olsen, Andreas Fischer, et al. "Wind tunnel benchmark tests of airfoils." Journal of Physics: Conference Series 2265, no. 2 (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 sepa

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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 (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

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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 (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

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Setiawan, M. Yasep, Andre Kurniawan, Ichsan, et al. "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 s

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Arif Pratama, Riza, Muhammad Ikhsan, Dhimas Wicaksono, M. Safiq Rieza, and Munir Zainal Abidin. "Analisis Intensitas Turbulensi Terhadap Kestabilan Kecepatan Angin Test Section pada Struktur Wind Tunnel." Infotekmesin 16, no. 1 (2025): 269–75. https://doi.org/10.35970/infotekmesin.v16i1.2511.

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Wind tunnels in aerodynamic testing always have very large sizes to avoid high turbulence intensity. Turbulence intensity analysis is used to determine the size of a smaller wind tunnel to be more efficient in limited space. The use of epoxy fiber resin material is because lighter than aluminum with a thickness of 5mm. The purpose of the study was to produce a wind tunnel with a small size with low turbulence intensity and minimize large manufacture costs. The method used is constructive to analyze the wind tunnel design in determining the maximum wind flow speed at test section does not excee

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15

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 (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 (transportatio

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16

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

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17

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 (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

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18

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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19

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

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20

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

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21

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

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22

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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23

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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24

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

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25

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 g

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26

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 (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

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27

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 (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

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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 (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 th

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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 (2015): 651–60. http://dx.doi.org/10.1260/0309-524x.39.6.651.

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30

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

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31

Yanel, Karnova, and Asmara Yanto. "Design and Manufacturing of Wind Tunnel for Turbine Impeller Airfoil Testing." Jurnal Teknik Mesin 12, no. 2 (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

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32

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 (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 t

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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 (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. F

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35

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 (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

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37

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 (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

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

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39

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

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40

Desai, Siddhant, Joseph A. Schetz, Rakesh K. Kapania, and Rikin Gupta. "Wind Tunnel Testing of Tethered Inflatable Wings." Journal of Aircraft 61, no. 6 (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 prov

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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 (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 ch

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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 (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, ope

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Hubová, Oľga, and Peter Lobotka. "The Multipurpose New Wind Tunnel STU." Civil and Environmental Engineering 10, no. 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

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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 (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 ax

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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 (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 exhaus

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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 (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 t

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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 (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: fid

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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 (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

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