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Journal articles on the topic 'Wind tunnel tests'

Author: Grafiati

Published: 4 June 2021

Last updated: 31 July 2024

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1

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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2

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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3

Zhou, Qi, Yuxiang Zhu, Yu Wang, and Jiceng Han. "CFD-Based Wind Field Correction Method for Terrain Wind Tunnel Tests." Journal of Physics: Conference Series 2083, no. 3 (November 1, 2021): 032083. http://dx.doi.org/10.1088/1742-6596/2083/3/032083.

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Abstract At present, the wind tunnel test results will have certain deviation and distortion when the wind tunnel test is conducted on certain mountainous terrain with complex local terrain and large variation of wind field characteristics due to the accuracy range of the measuring instruments used in wind tunnel test. In order to correct and obtain correct wind tunnel test results, the wind tunnel tests and numerical simulations were conducted on a super-large bridge in the mountainous area of Southwest China, and the wind parameters of the wind field at the bridge site were obtained. The CFD results were compared with the wind tunnel test results to confirm the credibility of the CFD results; a method was proposed to correct the deviated wind tunnel test data based on the CFD simulation results; the deviated wind tunnel test data were corrected and predicted with the above method, and a more satisfactory correction result was obtained.

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4

MAEDA, Tatsuo, and Yoshihiko KONDO. "RTRI's Large-scale Low-noise Wind Tunnel and Wind Tunnel Tests." Quarterly Report of RTRI 42, no. 2 (2001): 65–70. http://dx.doi.org/10.2219/rtriqr.42.65.

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5

Zhang, Ying Chao, Wei Ding, Zhe Zhang, and Jie Li. "Comparison Research on Aerodynamic Drags and Pressure Coefficients of Reference Car Models in Automotive Wind Tunnel." Advanced Materials Research 989-994 (July 2014): 2834–38. http://dx.doi.org/10.4028/www.scientific.net/amr.989-994.2834.

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The aerodynamic drags of different reference car models were investigated to calibrate the performance of the Automotive Wind Tunnel in Jilin University. The two kinds of reference models--MIRA and SAE reference car models were involved in this paper, considering the actual situation of the Automotive Wind Tunnel in Jilin University. The results of the research show that the Automotive Wind Tunnel in Jilin University can meet the demand for automotive wind tunnel tests and it can get the same performances as other wind tunnels have and reliable test data can be obtained in it.

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6

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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7

Samali, B., K. C. S. Kwok, G. S. Wood, and J. N. Yang. "Wind Tunnel Tests for Wind-Excited Benchmark Building." Journal of Engineering Mechanics 130, no. 4 (April 2004): 447–50. http://dx.doi.org/10.1061/(asce)0733-9399(2004)130:4(447).

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8

Tabatabaei, Narges, Ramis Örlü, Ricardo Vinuesa, and Philipp Schlatter. "Aerodynamic Free-Flight Conditions in Wind Tunnel Modelling through Reduced-Order Wall Inserts." Fluids 6, no. 8 (July 27, 2021): 265. http://dx.doi.org/10.3390/fluids6080265.

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Parallel sidewalls are the standard bounding walls in wind tunnels when making a wind tunnel model for free-flight condition. The consequence of confinement in wind tunnel tests, known as wall-interference, is one of the main sources of uncertainty in experimental aerodynamics, limiting the realizability of free-flight conditions. Although this has been an issue when designing transonic wind tunnels and/or in cases with large blockage ratios, even subsonic wind tunnels at low-blockage-ratios might require wall corrections if a good representation of free-flight conditions is intended. In order to avoid the cumbersome streamlining methods especially for subsonic wind tunnels, a sensitivity analysis is conducted in order to investigate the effect of inclined sidewalls as a reduced-order wall insert in the airfoil plane. This problem is investigated via Reynolds-averaged Navier–Stokes (RANS) simulations, and a NACA4412 wing at the angles of attack between 0 and 11 degrees at a moderate Reynolds number (400 k) is considered. The simulations are validated with well-resolved large-eddy simulation (LES) results and experimental wind tunnel data. Firstly, the wall-interference contribution in aerodynamic forces, as well as the local pressure coefficients, are assessed. Furthermore, the isolated effect of confinement is analyzed independent of the boundary-layer growth. Secondly, wall-alignment is modified as a calibration parameter in order to reduce wall-interference based on the aforementioned assessment. In the outlined method, we propose the use of linear inserts to account for the effect of wind tunnel walls, which are experimentally simple to realize. The use of these inserts in subsonic wind tunnels with moderate blockage ratio leads to very good agreement between free-flight and wind tunnel data, while this approach benefits from simple manufacturing and experimental realization.

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9

Krzysiak, A. "Bottom drag measurements in experimental wind tunnel tests." Journal of Physics: Conference Series 2367, no. 1 (November 1, 2022): 012001. http://dx.doi.org/10.1088/1742-6596/2367/1/012001.

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Abstract The paper presents the results of wind tunnel tests aimed at determining the model bottom drag in the case of rocket model tests. The balance measurement technique of the rocket model fixed in the wind tunnel test section by the rear sting was discussed. The model was equipped with the two parallel boosters. Based on the wind tunnel test of the rocket twin model the values of the bottom pressure was determined for tested Mach numbers. An algorithm of wind tunnel corrections was shown, which allowed the total drag determination in a case of the rocket active or passive rocket flight. The test results showed the necessity of the bottom drag measurements in wind tunnel tests.

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10

WANG, Wenjun, Hiroshi KUROYANAGI, and Kazunori YOSHIDA. "1A16 6 Force Component Balance for Wind Tunnel Model Tests." Proceedings of the Symposium on the Motion and Vibration Control 2010 (2010): _1A16–1_—_1A16–7_. http://dx.doi.org/10.1299/jsmemovic.2010._1a16-1_.

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11

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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12

MAEDA, Tatsuo. "Wind Tunnel Tests on Railway Vehicles." Wind Engineers, JAWE 34, no. 1 (2009): 24–29. http://dx.doi.org/10.5359/jawe.34.24.

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13

Cataldo, José, Valeria Durañona, Rodolfo Pienika, Pablo Pais, and Alfredo Gravina. "Wind damage on citrus fruit study: Wind tunnel tests." Journal of Wind Engineering and Industrial Aerodynamics 116 (May 2013): 1–6. http://dx.doi.org/10.1016/j.jweia.2013.01.008.

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14

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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15

Husain, Z., M. Z. Abdullah, and T. C. Yap. "Two-Dimensional Analysis of Tandem/Staggered Airfoils Using Computational Fluid Dynamics." International Journal of Mechanical Engineering Education 33, no. 3 (July 2005): 195–207. http://dx.doi.org/10.7227/ijmee.33.3.2.

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The two-dimensional analysis, using computational fluid dynamics (CFD), of tandem/staggered arranged airfoils of the canard and wing of an Eagle 150 aircraft and also the aerodynamic tests conducted in an open-circuit wind tunnel are presented in the paper. The wind tunnel tests were carried out at a speed of 38m/s in a test section of size 300 mm (width), 300 mm (height) and 600 mm (length), at Reynolds number 2.25 × 105. The tests were carried out with tandem and staggered placement of the airfoils in order to determine the optimum position of the wing with respect to the canard and also to determine the lift coefficient at various angles of attack. The CFD code FLUENT 5 was used to investigate the aerodynamic performance of a two-dimensional model to validate the wind tunnel results. The flow interaction was studied in the tandem and staggered arrangements in the wind tunnel as well as by the computational method. The k-ε turbulence model gave exceptionally good results.

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16

Wang, Lei, Fen Shi, Zheng Wang, and Shuguo Liang. "Blockage Effects in Wind Tunnel Tests for Tall Buildings with Surrounding Buildings." Applied Sciences 12, no. 14 (July 14, 2022): 7087. http://dx.doi.org/10.3390/app12147087.

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To study the blockage effects in wind tunnel tests for tall buildings with surrounding buildings and establish a reasonable calculation method for the blockage ratio, this paper carried out fifty-one test conditions of pressure model wind tunnel tests with three scale ratios. The tests considered the relative location, relative height, and model number of the surrounding buildings to those of the target building by the rigid pressure models. Based on the wind tunnel tests, the blockage effects on the pressure coefficients and drag coefficients were studied in detail. The results showed that the blockage effects were different when the relative positions of the surrounding models to the target model were different, even if the blockage ratio was the same. The blockage effects caused by the surrounding models with unit blockage ratio were usually more significant than those caused by the target pressure-measuring model itself. The existing correction methods for the blockage effects are mainly derived from the wind tunnel tests of an isolated building model. Using existing calculations to evaluate the blockage effect of wind tunnel tests for tall buildings with surrounding buildings may result in obvious deviations. Finally, the concept of the equivalent blockage ratio was proposed, which can be used to calculate the blockage ratio of wind tunnel tests of tall buildings with surrounding buildings. The proposed calculation method of this equivalent blockage ratio can provide a reference for the determination of scale ratios for wind tunnel test models of tall buildings.

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17

Qu, Xiyao, Zijing Liu, Baiyang Yu, Wei An, Xuejun Liu, and Hongqiang Lyu. "Predicting pressure coefficients of wing surface based on the transfer of spatial dependency." AIP Advances 12, no. 5 (May 1, 2022): 055225. http://dx.doi.org/10.1063/5.0093144.

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Multi-conditional holographic pressure coefficients over a wing are crucial for wing design, and a wind tunnel test is an indispensable means to obtain this profile. However, it is resource-consuming to obtain wind tunnel data under different conditions and only a limited number of sensors can be placed on the wing model during one test, which results in sparse pressure coefficient data with distribution inconsistency across cross sections and conditions. Thus, how to obtain pressure coefficients of more cross sections or even the whole wing surface with multiple conditions from the distribution-inconsistent sensor data becomes a challenging problem. Therefore, a deep learning framework based on transfer learning is proposed in this paper, in which the spatial dependency captured by a long short-term memory model between the obtained multi-conditional sensor data is transferred to other cross sections with few-condition data on the wing. The results demonstrate that the proposed framework achieves high accuracy on the pressure coefficients prediction of distribution-inconsistent cross sections on wind tunnel test data, and thus improves data utilization and cuts costs by reducing wind tunnel tests under different design conditions. Our work proves the possibility of reconstructing the holographic flow field from sparse sensor data of wind tunnel tests and puts forward recommendations on the placement of sensors for achieving this goal.

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18

Yi, Zijing, Lingjun Wang, Xiao Li, Zhigang Zhang, Xu Zhou, and Bowen Yan. "Computational Fluid Dynamics-Aided Simulation of Twisted Wind Flows in Boundary Layer Wind Tunnel." Applied Sciences 14, no. 3 (January 24, 2024): 988. http://dx.doi.org/10.3390/app14030988.

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The twisted wind flow (TWF), referring to the phenomenon of wind direction varying with height, is a common feature of atmospheric boundary layer (ABL) winds, noticeably affecting the wind-resistant structural design and the wind environment assessment. The TWF can be effectively simulated by a guide vane system in wind tunnel tests, but the proper design and configuration of the guide vanes pose a major challenge as practical experience in using such devices is still limited in the literature. To address this issue, this study aims to propose an approach to determining the optimal wind tunnel setup for TWF simulations using a numerical wind tunnel, which is a replica of its physical counterpart, using computational fluid dynamics (CFD) techniques. By analyzing the mechanisms behind guide vanes for generating TWF based on CFD results, it was found that the design must take into account three key parameters, namely, (1) the distance from the vane system to the side wall, (2) the distance from the vane system to the model test region, and (3) the separation between the vanes. Following the optimal setup obtained from the numerical wind tunnel, TWF profiles matching both the power-law and Ekman spiral models, which, respectively, reflect the ABL and wind twist characteristics, were successfully generated in the actual wind tunnel. The findings of this study provide useful information for wind tunnel tests as well as for wind-resistant structural designs and wind environment assessment.

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19

Popov, Andrei V., Lucian T. Grigorie, Ruxandra Botez, Mahmood Mamou, and Youssef Mebarki. "Real Time Morphing Wing Optimization Validation Using Wind-Tunnel Tests." Journal of Aircraft 47, no. 4 (July 2010): 1346–55. http://dx.doi.org/10.2514/1.47431.

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20

Vyalkov, Andrey Viktorovitch. "INERTIAL TECHNOLOGY OF WIND TUNNEL SPIN TESTS." TsAGI Science Journal 47, no. 5 (2016): 537–52. http://dx.doi.org/10.1615/tsagiscij.2017019332.

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21

Warnitchai, Pennung, Suksit Sinthuwong, and Kobchai Poemsantitham. "Wind Tunnel Model Tests of Large Billboards." Advances in Structural Engineering 12, no. 1 (February 2009): 103–14. http://dx.doi.org/10.1260/136943309787522650.

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22

Belloli, Marco, Federico Cheli, Ilmas Bayati, Stefano Giappino, and Fabio Robustelli. "Handbike Aerodynamics: Wind Tunnel Versus Track Tests." Procedia Engineering 72 (2014): 750–55. http://dx.doi.org/10.1016/j.proeng.2014.06.127.

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23

MIZUNO, Takeshi, Yasuhiro SAKAI, Masaya TAKASAKI, and Yuji ISHINO. "A103 Wind-Tunnel for Spinning Body Using Magnetic Suspension : 5th report: Wind-tunnel Tests." Proceedings of the Symposium on the Motion and Vibration Control 2011.12 (2011): 29–32. http://dx.doi.org/10.1299/jsmemovic.2011.12.29.

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24

Bosak, Grzegorz. "Wind tunnel tests of wind action on a high-rise building." Budownictwo i Architektura 13, no. 2 (June 11, 2014): 163–71. http://dx.doi.org/10.35784/bud-arch.1891.

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The paper summarizes the results of wind tunnel tests of a wind action on a high-rise building design in Warsaw. Measurements were accomplished in Wind Engineering Laboratory of Cracow University of Technology. Wind pressures on external surfaces of the building model were acquired. A study of the character of the wind action on a tower of the building was the main aim of the paper. A triangle shape with rounded corners of the cross section of the tower and a complex group of neighbor buildings support aerodynamic analysis in a wind tunnel. Wind pressure coefficients on the external building surfaces and the global horizontal wind action on the building tower on full scale were analyzed.

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25

Selig, Michael S., and Bryan D. McGranahan. "Wind Tunnel Aerodynamic Tests of Six Airfoils for Use on Small Wind Turbines." Journal of Solar Energy Engineering 126, no. 4 (November 1, 2004): 986–1001. http://dx.doi.org/10.1115/1.1793208.

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This paper presents detailed wind tunnel tests data taken on six airfoils having application to small wind turbines. In particular, lift, drag and moment measurements were taken at Reynolds numbers of 100,000, 200,000, 350,000 and 500,000 for both clean and rough conditions. In some cases, data were also taken at a Reynolds number of 150,000. The airfoils included the E387, FX 63-137, S822, S834, SD2030, and SH3055. Prior to carrying out the tests, wind tunnel flow quality measurements were taken to document the low Reynolds number test environment. Oil flow visualization data and performance data taken on the E387 compare favorably with measurements taken at NASA Langley in the Low Turbulence Pressure Tunnel. Highlights of the performance characteristics of the other five airfoils are presented.

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26

Maria Viola, Ignazio, and Richard G. J. Flay. "Sail Aerodynamics: On-Water Pressure Measurements on a Downwind Sail." Journal of Ship Research 56, no. 04 (December 1, 2012): 197–206. http://dx.doi.org/10.5957/jsr.2012.56.4.197.

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Pressures on three horizontal sections of a downwind sail were measured for several wind directions and sail trims. The pressure distributions were compared with wind tunnel tests; similarities and differences were found, the latter as a result of the dynamic effects, which were not modeled in the wind tunnel. A pressure distribution at the head of the spinnaker resembling that from a delta wing was measured at an apparent wind angle of 120°.

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27

Li, Chunguang, Yan Han, Ji Zhang, Shuqian Liu, and C. S. Cai. "Wind Tunnel Tests on Wind Pressure Characteristics of Sawtooth Roofs." Journal of Aerospace Engineering 31, no. 6 (November 2018): 04018107. http://dx.doi.org/10.1061/(asce)as.1943-5525.0000931.

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28

Verelst, D. R. S., T. J. Larsen, and J. W. van Wingerden. "Wind tunnel tests of a free yawing downwind wind turbine." Journal of Physics: Conference Series 555 (December 16, 2014): 012103. http://dx.doi.org/10.1088/1742-6596/555/1/012103.

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29

Liu, Xianzhi, Yan Han, C. S. Cai, Marc Levitan, and Dimitris Nikitopoulos. "Wind tunnel tests for mean wind loads on road vehicles." Journal of Wind Engineering and Industrial Aerodynamics 150 (March 2016): 15–21. http://dx.doi.org/10.1016/j.jweia.2015.12.004.

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30

Tsutsumi, J., T. Katayama, and M. Nishida. "Wind tunnel tests of wind pressure on regularly aligned buildings." Journal of Wind Engineering and Industrial Aerodynamics 43, no. 1-3 (January 1992): 1799–810. http://dx.doi.org/10.1016/0167-6105(92)90592-x.

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31

Xu, Xin, Qiang Li, Dawei Liu, Keming Cheng, and Dehua Chen. "Geometric Effects Analysis and Verification of V-Shaped Support Interference on Blended Wing Body Aircraft." Applied Sciences 10, no. 5 (February 28, 2020): 1596. http://dx.doi.org/10.3390/app10051596.

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A special V-shaped support for blended wing body aircraft was designed and applied in high-speed wind tunnel tests. In order to reduce the support interference and explore the design criteria of the V-shaped support, interference characteristics and geometric parameter effects of V-shaped support on blended wing body aircraft were numerically studied. According to the numerical results, the corresponding dummy V-shaped supports were designed and manufactured, and verification tests was conducted in a 2.4 m × 2.4 m transonic wind tunnel. The test results were in good agreement with the numerical simulation. Results indicated that pitching moment of blended wing body aircraft is quite sensitive to the V-shaped support geometric parameters, and the influence of the inflection angle is the most serious. To minimize the pitching moment interference, the straight-section diameter and inflection angle should be increased while the straight-section length should be shortened. The results could be used to design special V-shaped support for blended wing body aircraft in wind tunnel tests, reduce support interference, and improve the accuracy of test results.

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32

Migliore, Paul, and Stefan Oerlemans. "Wind Tunnel Aeroacoustic Tests of Six Airfoils for Use on Small Wind Turbines*." Journal of Solar Energy Engineering 126, no. 4 (November 1, 2004): 974–85. http://dx.doi.org/10.1115/1.1790535.

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Aeroacoustic tests of seven airfoils were performed in an open jet anechoic wind tunnel. Six of the airfoils are candidates for use on small wind turbines operating at low Reynolds numbers. One airfoil was tested for comparison to benchmark data. Tests were conducted with and without boundary layer tripping. In some cases, a turbulence grid was placed upstream in the test section to investigate inflow turbulence noise. An array of 48 microphones was used to locate noise sources and separate airfoil noise from extraneous tunnel noise. Trailing-edge noise was dominant for all airfoils in clean tunnel flow. With the boundary layer untripped, several airfoils exhibited pure tones that disappeared after proper tripping was applied. In the presence of inflow turbulence, leading-edge noise was dominant for all airfoils.

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33

Wakimoto, Ken, Kazuhisa Chiba, Hiroyuki Kato, and Kazuyuki Nakakita. "Acquisition of Swept Aerodynamic Data by the Consecutive Changing of Wing Model Configuration in a Wind Tunnel Test Using Remote Feedback Control." Aerospace 8, no. 8 (August 7, 2021): 217. http://dx.doi.org/10.3390/aerospace8080217.

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This study conducted wind tunnel tests with consecutive deflection angle changes on a three-dimensional (3D) wing with a control surface to procure aerodynamic data by sweeping the deflection angle. Configuration changes of a wind tunnel test model, such as changing the deflection angle of control surfaces, are usually performed manually with the ventilation suspended. Hence, the number of configurations that can be implemented within a confined test period is restricted; the aerodynamic data gained are discrete values. To accomplish continuous angular modulation would dramatically improve the ability by sweeping through the aerodynamic data in wind tunnel tests, enhancing the test system as a tool for discussing complex physical phenomena. Thus, this study created a compact remote feedback control system using optical measurement to continuously obtain high-precision aerodynamic data without stopping the wind tunnel, eliminating human operation. In particular, this study targets a 3D wing wind tunnel model with a control surface, which is more challenging to fabricate, miniaturizing the system in a model. The system consequently attained consecutive aerodynamic data multiple times under numerous configurations, which had been impracticable to reach in the past, within a wind tunnel test period of several days, thereby dramatically increasing the testing capability. The reproducibility was quantitatively verified by comparing the multiple data for the identical configurations. Furthermore, the reliability was demonstrated using discrete data obtained by conventional stepwise deflection angle adjustments. Eventually, the system was able to grasp physical phenomena involving hysteresis.

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34

Tse, K. T., A. U. Weerasuriya, and K. C. S. Kwok. "Simulation of twisted wind flows in a boundary layer wind tunnel for pedestrian-level wind tunnel tests." Journal of Wind Engineering and Industrial Aerodynamics 159 (December 2016): 99–109. http://dx.doi.org/10.1016/j.jweia.2016.10.010.

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35

Ouyang, Yan, Kaichun Zeng, Xiping Kou, Yingsong Gu, and Zhichun Yang. "Experimental and Numerical Studies on Static Aeroelastic Behaviours of a Forward-Swept Wing Model." Shock and Vibration 2021 (June 10, 2021): 1–12. http://dx.doi.org/10.1155/2021/5535192.

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The static aeroelastic behaviours of a flat-plate forward-swept wing model in the vicinity of static divergence are investigated by numerical simulations and wind tunnel tests. A medium fidelity model based on the vortex lattice method (VLM) and nonlinear structural analysis is proposed to calculate the displacements of the wing structure with large deformation. Follower forces effect and geometric nonlinearity are considered to calculate the deformation of the wing by finite element method (FEM). In the wind tunnel tests, the divergence dynamic pressure is predicted by the Southwell method, and the static aeroelastic displacement is measured by a photogrammetric method. The results obtained by the medium fidelity model calculations show reasonable agreement with wind tunnel test results. A high fidelity model based on coupled computational fluid dynamics (CFD) and computational structural dynamics (CSD) predicts better results of the wing tip displacement when the freestream dynamic pressure is approaching the divergence dynamic pressure.

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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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Yu, Li, Bin Bin Lv, Yu Yan, Hong Tao Guo, Jun Zha, and Chang Rong Zhang. "Introduction to Automatic Shutdown System for Flutter Test of High Speed Wind Tunnel." Advanced Materials Research 1030-1032 (September 2014): 1584–87. http://dx.doi.org/10.4028/www.scientific.net/amr.1030-1032.1584.

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This paper introduces an automatic shutdown system for model protection during the flutter test in high speed wind tunnels. This automatic shutdown system can be used to determine any unsafe condition through model flutter signals before triggering shutdown of wind tunnels, solving problems of delayed response and mistakes happen during manual measurement of subcritical state of model flutter. The reliability and effectiveness of this system have been proved good via wind tunnel tests, hence the possibility of damage to the model caused by flutter during the flutter test of high speed wind tunnels can be decreased.

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Gibertini, G., F. Auteri, G. Campanardi, C. Macchi, A. Zanotti, and A. Stabellini. "Wind-tunnel tests of a tilt-rotor aircraft." Aeronautical Journal 115, no. 1167 (May 2011): 315–22. http://dx.doi.org/10.1017/s0001924000005790.

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Abstract A wide aerodynamic test campaign has been carried out on the tiltrotor aircraft ERICA at the Large Wind Tunnel of Politecnico di Milano by means of a modular 1:8 scale model in order to produce a dataset necessary to better understand the aerodynamic behaviour of the aircraft and to state its definitive design. The target of the tests was the measurement of the aerodynamic forces and moments in several different configurations and different attitudes. The test program included some conditions at very high incidence and sideslip angles that typically belong to the helicopter-mode flight envelope and measurements of forces on the tail and on the tilting wings. A large amount of data has been collected that will be very useful to refine the aircraft design. In general the aircraft aerodynamics do not present any critical problems, but further optimisation is still possible. From the viewpoint of drag in the cruise configuration, the sponsons of the landing gear seem to be worth some further design refinement since they are responsible for a 20% drag increase with respect to the pure fuselage configuration. On the contrary, the wing fairing has proved to work well when the aircraft longitudinal axis is aligned with the wind, providing just a slight drag increase. Two other interesting aspects are the quite nonlinear behaviour of the side force for the intermediate sideslip angles as well as the noticeable hysteresis in the moment coefficient at very high incidence angles.

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Yang, Wei, Meng Yu, Bowen Yan, Guoqing Huang, Qingshan Yang, Senqin Zhang, Tianhao Hong, Xu Zhou, and Xiaowei Deng. "Wind Tunnel Tests of Wake Characteristics for a Scaled Wind Turbine Model Based on Dynamic Similarity." Energies 15, no. 17 (August 25, 2022): 6165. http://dx.doi.org/10.3390/en15176165.

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This wind tunnel study was conducted to investigate the similarity laws involved in the reasonable simulation of the wake characteristics of a full-scale wind turbine. A 5 MW scaled wind turbine model was designed using an optimization method based on the blade element momentum (BEM) theory. Subsequently, wind tunnel tests were carried out on the geometrically similar model and the thrust-optimized model, with different yaw angles and under various upstream flow conditions. The results indicated that the wake development of the wind turbine model was closely related to the thrust forces of the wind turbine, and both kinematic and dynamic similarity laws should be observed to achieve wake characteristics that are reasonably similar to those of a full-scale wind turbine. This study investigated the aerodynamic similarity principles of small-scale wind turbine models to develop a more effective method for simulating full-scale turbine wake characteristics in wind tunnel tests. The outcomes of this study revealed the limitations of the anomalously low thrust coefficients in geometrically similar wind turbine models and present reasonable model design methodologies for small-scale wind turbine models in wind tunnel tests.

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Krzysiak, Andrzej. "Wind Tunnel Tests of the Tu-154M Aircraft Aerodynamic Characteristics." Journal of KONES 26, no. 3 (September 1, 2019): 113–20. http://dx.doi.org/10.2478/kones-2019-0064.

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Abstract Determination of possible manoeuvres to be performed by the aircraft requires knowledge of its aerodynamic characteristics including, in particular, characteristics of the aircraft at configuration with deflected control surfaces. In this article, the wind tunnel tests results of the model of passenger Tu-154M aircraft manufactured at the scale 1:40 are presented. The model was designed and manufactured by the Military University of Technology based on the Tu-154M aircraft geometry obtained by full-scale object scanning. The model mapped all aircraft control surfaces, along with the gaps between these surfaces and the main wing part. During the tests all the model’s control surface like, flaps, ailerons, spoilers, slots, rudder, elevator and tail plane were deflected at the same deflection angles range as they are used in the full scale aircraft. The aerodynamic characteristics of the tested Tu-154M aircraft model were measured by the 6-component internal balance. Based on the obtained measurements the aircraft model aerodynamic coefficients were calculated. In the article the basic aerodynamic characteristics of the tested Tu-154M aircraft model i.e. lift, drag coefficients as well as pitching, yawing and rolling moment coefficients versus model angles of attack and sideslip angles were presented. The tests were performed in the Institute of Aviation low speed wind tunnels T-1 of the 1.5 m diameter test section at the undisturbed velocity, V∞ = 40 m/s.

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41

Zhao, Yi, Ruibin Li, Lu Feng, Yan Wu, and Naiping Gao. "Boundary layer wind tunnel tests of outdoor airflow field around urban buildings: A review of methods and status." E3S Web of Conferences 356 (2022): 04031. http://dx.doi.org/10.1051/e3sconf/202235604031.

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Outdoor airflow fields have received increasing attention in the building aerodynamics community due to that the airflow distributions around outdoor buildings are closely related to issues such as thermal comfort, building ventilation, and pollutant dispersion. The focus of this paper is on the airflow distributions around buildings obtained through wind tunnel tests, and such studies are mostly conducted in boundary layer wind tunnel with long test section. This paper reviews current techniques for boundary layer wind tunnel tests of airflow distributions in urban outdoor environments. Then, the characteristics of airflow distributions around buildings in three typical configurations from previous studies (i.e. isolated building, street canyon, and building complexes) are reviewed. This review highlights that the proposed building models should be carefully assessed in combination with wind tunnel tests at the design stage. In addition, it is important to obtain wind tunnel test data for buildings with thermal effects, and the importance of arranging the underlying surfaces during the test is also emphasized.

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Ma, Ziqing, Ewoud J. J. Smeur, and Guido C. H. E. de Croon. "Wind tunnel tests of a wing at all angles of attack." International Journal of Micro Air Vehicles 14 (January 2022): 175682932211109. http://dx.doi.org/10.1177/17568293221110931.

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Tailsitters have complex aerodynamics that make them hard to control throughout the entire flight envelope, especially at very high angle of attack (AoA) and reverse flow conditions. The development of controllers for these vehicles is hampered by the absence of publicly available data on forces and moments experienced in such conditions. In this paper, wind tunnel experiments are performed under different flap deflections and throttle settings at all possible AoA. The dataset is made open access. Our analysis of the data shows for the tested wing, flap deflections greatly affect the lift coefficient and stall occurs at [Formula: see text] AoA as well as [Formula: see text]. Wing-propeller interaction is studied by analyzing the propeller induced force in the axis orthogonal to the thrust axis, which is dependent on AoA, airspeed, flap deflections and thrust in a nonlinear and coupled manner. The influence of inverse flow on the wing is also discussed: The data confirm that when the airflow over the wing is reversed, flap deflections will affect the pitch moment in an opposite way compared to the non-reversed case, but this opposite effect can be avoided by increasing the throttle setting. The data show the exact relationship between flap deflections and forces in this condition. Moreover, it is found that the flap control effectiveness for a wing with or without spinning propellers is usually higher around zero degrees AoA than at [Formula: see text] and it is more effective to change the flaps from [Formula: see text] to [Formula: see text] than from [Formula: see text] to the respective [Formula: see text].

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Krzysiak, Andrzej. "Wind Tunnel Tests of Damage to the Tu-154M Aircraft Wing." Journal of Aerospace Engineering 32, no. 6 (November 2019): 04019083. http://dx.doi.org/10.1061/(asce)as.1943-5525.0001087.

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Muggiasca, Sara, Federico Taruffi, Alessandro Fontanella, Simone Di Carlo, and Marco Belloli. "Aerodynamic and Structural Strategies for the Rotor Design of a Wind Turbine Scaled Model." Energies 14, no. 8 (April 10, 2021): 2119. http://dx.doi.org/10.3390/en14082119.

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Experimental tests performed in a wind tunnel or in a natural laboratory represent a fundamental research tool to develop floating wind technologies. In order to obtain reliable results, the wind turbine scale model rotor must be designed so to obtain a fluid-structure interaction comparable to the one experienced by a real machine. This implies an aerodynamic design of the 3D blade geometry but, also, a structural project to match the main aeroelastic issues. For natural laboratory models, due to not controlled test conditions, the wind turbine rotor model must be checked also for extreme winds. The present paper will focus on all the strategies adopted to scale a wind turbine blade presenting two studied cases: the first is a 1:75 scale model for wind tunnel applications and the second a 1:15 model for natural laboratory tests.

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KATAGIRI, Junji. "Wind Tunnel Tests for Wind Resistance Design of High-rise Buildings." Wind Engineers, JAWE 34, no. 1 (2009): 10–17. http://dx.doi.org/10.5359/jawe.34.10.

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46

Llorente, E., A. Gorostidi, M. Jacobs, W. A. Timmer, X. Munduate, and O. Pires. "Wind Tunnel Tests of Wind Turbine Airfoils at High Reynolds Numbers." Journal of Physics: Conference Series 524 (June 16, 2014): 012012. http://dx.doi.org/10.1088/1742-6596/524/1/012012.

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Jing, Xiao-kun, and Yuan-qi Li. "Wind Tunnel Tests for Wind Pressure Distribution on Gable Roof Buildings." Scientific World Journal 2013 (2013): 1–11. http://dx.doi.org/10.1155/2013/396936.

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Gable roof buildings are widely used in industrial buildings. Based on wind tunnel tests with rigid models, wind pressure distributions on gable roof buildings with different aspect ratios were measured simultaneously. Some characteristics of the measured wind pressure field on the surfaces of the models were analyzed, including mean wind pressure, fluctuating wind pressure, peak negative wind pressure, and characteristics of proper orthogonal decomposition results of the measured wind pressure field. The results show that extremely high local suctions often occur in the leading edges of longitudinal wall and windward roof, roof corner, and roof ridge which are the severe damaged locations under strong wind. The aspect ratio of building has a certain effect on the mean wind pressure coefficients, and the effect relates to wind attack angle. Compared with experimental results, the region division of roof corner and roof ridge from AIJ2004 is more reasonable than those from CECS102:2002 and MBMA2006.The contributions of the first several eigenvectors to the overall wind pressure distributions become much bigger. The investigation can offer some basic understanding for estimating wind load distribution on gable roof buildings and facilitate wind-resistant design of cladding components and their connections considering wind load path.

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Kong, L., and G. V. Parkinson. "A 3-D tolerant wind tunnel for general wind engineering tests." Journal of Wind Engineering and Industrial Aerodynamics 69-71 (July 1997): 975–85. http://dx.doi.org/10.1016/s0167-6105(97)00221-3.

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Amoroso, Samuel, Kirby Hebert, and Marc Levitan. "Wind tunnel tests for mean wind loads on partially clad structures." Journal of Wind Engineering and Industrial Aerodynamics 98, no. 12 (December 2010): 689–700. http://dx.doi.org/10.1016/j.jweia.2009.08.009.

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Bayati, Ilmas, Marco Belloli, Luca Bernini, and Alberto Zasso. "Aerodynamic design methodology for wind tunnel tests of wind turbine rotors." Journal of Wind Engineering and Industrial Aerodynamics 167 (August 2017): 217–27. http://dx.doi.org/10.1016/j.jweia.2017.05.004.

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