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Journal articles on the topic 'Wind tunnel balance'

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Author: Grafiati

Published: 10 December 2022

Last updated: 28 January 2023

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1

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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2

Vukovic, Djordje, and Dijana Damljanovic. "Thermal effects influencing measurements in a supersonic blowdown wind tunnel." Thermal Science 20, no. 6 (2016): 2101–12. http://dx.doi.org/10.2298/tsci160404175v.

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During a supersonic run of a blowdown wind tunnel, temperature of air in the test section drops which can affect planned measurements. Adverse thermal effects include variations of the Mach and Reynolds numbers, variation of airspeed, condensation of moisture on the model, change of characteristics of the instrumentation in the model, et cetera. Available data on thermal effects on instrumentation are pertaining primarily to long-run-duration wind tunnel facilities. In order to characterize such influences on instrumentation in the models, in short-run-duration blowdown wind tunnels, temperature measurements were made in the wing-panel-balance and main-balance spaces of two wind tunnel models tested in the T-38 wind tunnel. The measurements showed that model-interior temperature in a run increased at the beginning of the run, followed by a slower drop and, at the end of the run, by a large temperature drop. Panel-force balance was affected much more than the main balance. Ways of reducing the unwelcome thermal effects by instrumentation design and test planning are discussed.

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3

Burns, Devin E., and Peter A. Parker. "Additively Manufactured Wind-Tunnel Balance." Journal of Aircraft 57, no. 5 (September 2020): 958–63. http://dx.doi.org/10.2514/1.c035889.

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4

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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5

Ewald, B. "The accuracy of internal wind tunnel balances for wind tunnel force measurements, the problem of definition and verification." Aeronautical Journal 105, no. 1050 (August 2001): 443–49. http://dx.doi.org/10.1017/s0001924000012422.

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Abstract For the definition of the acccuracy of an internal strain gauge balance no general agreement exists. So it is difficult or even impossible, to compare balances from different manufacturers or balances used at different places. Since most wind tunnel tests at least in the aeronautical field are done on a reference basis i.e. the results are compared with earlier results achieved with a more or less different configuration, repeatability is at least as important as absolute accuracy or even more important. So also repeatability, which in a physical sense is quite different from accuracy, must be defined and proven for each balance. With the examples of several balances manufactured for the DNW (Deutsch-Niederländischer Windkanal) and ETW (European transonic tunnel) accuracy and repeatability definitions are discussed. A proposal for a generally binding definition of accuracy and repeatability is given.

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6

EWALD, B. "WIND TUNNEL INSTRUMENTATION TECHNIQUE BALANCE DESIGN PROBLEMS." International Conference on Aerospace Sciences and Aviation Technology 1, CONFERENCE (May 1, 1985): 1–8. http://dx.doi.org/10.21608/asat.1985.26474.

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7

Krajček Nikolić, Karolina, Anita Domitrović, and Slobodan Janković. "Estimation of Aerodynamic Coefficients in a Small Subsonic Wind Tunnel." PROMET - Traffic&Transportation 30, no. 4 (September 10, 2018): 457–63. http://dx.doi.org/10.7307/ptt.v30i4.2685.

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To apply the experimental data measured in a wind tunnel for a scaled aircraft to a free-flying model, conditions of dynamical similarity must be met or scaling procedures introduced. The scaling methods should correct the wind tunnel data regarding model support, wall interference, and lower Reynolds number. To include the necessary corrections, the current scaling techniques use computational fluid dynamics (CFD) in combination with measurements in cryogenic wind tunnels. There are a few methods that enable preliminary calculations of typical corrections considering specific measurement conditions and volume limitation of test section. The purpose of this paper is to present one possible approach to estimating corrections due to sting interference and difference in Reynolds number between the real airplane in cruise regime and its 1:100 model in the small wind tunnel AT-1. The analysis gives results for correction of axial and normal force coefficients. The results of this analysis indicate that the Reynolds number effects and the problem of installation of internal force balance are quite large. Therefore, the wind tunnel AT-1 has limited usage for aerodynamic coefficient determination of transport airplanes, like Dash 8 Q400 analyzed in this paper.

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8

Shi, Pengtao, Jihai Liu, Yingsong Gu, Zhichun Yang, and Pier Marzocca. "Full-Span Flying Wing Wind Tunnel Test: A Body Freedom Flutter Study." Fluids 5, no. 1 (March 16, 2020): 34. http://dx.doi.org/10.3390/fluids5010034.

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Aiming at the experimental test of the body freedom flutter for modern high aspect ratio flexible flying wing, this paper conducts a body freedom flutter wind tunnel test on a full-span flying wing flutter model. The research content is summarized as follows: (1) The full-span finite element model and aeroelastic model of an unmanned aerial vehicle for body freedom flutter wind tunnel test are established, and the structural dynamics and flutter characteristics of this vehicle are obtained through theoretical analysis. (2) Based on the preliminary theoretical analysis results, the design and manufacturing of this vehicle are completed, and the structural dynamic characteristics of the vehicle are identified through ground vibration test. Finally, the theoretical analysis model is updated and the corresponding flutter characteristics are obtained. (3) A novel quasi-free flying suspension system capable of releasing pitch, plunge and yaw degrees of freedom is designed and implemented in the wind tunnel flutter test. The influence of the nose mass balance on the flutter results is explored. The study shows that: (1) The test vehicle can exhibit body freedom flutter at low airspeeds, and the obtained flutter speed and damping characteristics are favorable for conducting the body freedom flutter wind tunnel test. (2) The designed suspension system can effectively release the degrees of freedom of pitch, plunge, and yaw. The flutter speed measured in the wind tunnel test is 9.72 m/s, and the flutter frequency is 2.18 Hz, which agree well with the theoretical results (with flutter speed of 9.49 m/s and flutter frequency of 2.03 Hz). (3) With the increasing of the mass balance at the nose, critical speed of body freedom flutter rises up and the flutter frequency gradually decreases, which also agree well with corresponding theoretical results.

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9

Lynn, Keith C., Sean A. Commo, and Peter A. Parker. "Wind-Tunnel Force Balance Characterization for Hypersonic Research Applications." Journal of Aircraft 49, no. 2 (March 2012): 556–65. http://dx.doi.org/10.2514/1.c031567.

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10

Landman, Drew, Kenneth G. Toro, Sean A. Commo, and Keith C. Lynn. "Prediction Interval Development for Wind-Tunnel Balance Check-Loading." Journal of Aircraft 52, no. 3 (May 2015): 884–89. http://dx.doi.org/10.2514/1.c032930.

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11

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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12

Chen, Zengshun, Yemeng Xu, Hailin Huang, and Kam Tim Tse. "Wind Tunnel Measurement Systems for Unsteady Aerodynamic Forces on Bluff Bodies: Review and New Perspective." Sensors 20, no. 16 (August 17, 2020): 4633. http://dx.doi.org/10.3390/s20164633.

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Wind tunnel tests have become one of the most effective ways to evaluate aerodynamics and aeroelasticity in bluff bodies. This paper has firstly overviewed the development of conventional wind tunnel test techniques, including high frequency base balance technique, static synchronous multi-pressure sensing system test technique and aeroelastic test, and summarized their advantages and shortcomings. Subsequently, two advanced test approaches, a forced vibration test technique and hybrid aeroelastic- force balance wind tunnel test technique have been comprehensively reviewed. Then the characteristics and calculation procedure of the conventional and advanced wind tunnel test techniques were discussed and summarized. The results indicated that the conventional wind tunnel test techniques ignored the effect of structural oscillation on the measured aerodynamics as the test model is rigid. A forced vibration test can include that effect. Unfortunately, a test model in a forced vibration test cannot respond like a structure in the real world; it only includes the effect of structural oscillation on the surrounding flow and cannot consider the feedback from the surrounding flow to the oscillation test model. A hybrid aeroelastic-pressure/force balance test technique that can observe unsteady aerodynamics of a test model during its aeroelastic oscillation completely takes the effect of structural oscillation into consideration and is, therefore, effective in evaluation of aerodynamics and aeroelasticity in bluff bodies. This paper has not only advanced our understanding for aerodynamics and aeroelasticity in bluff bodies, but also provided a new perspective for advanced wind tunnel test techniques that can be used for fundamental studies and engineering applications.

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13

Zhai, Mingda, Wentao Xia, Zhiqiang Long, and Fengshan Dou. "Numerical Computation and Analysis of Electromagnetic Field in Magnetic Suspension and Balance System." Magnetochemistry 7, no. 3 (February 26, 2021): 33. http://dx.doi.org/10.3390/magnetochemistry7030033.

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The magnetic suspension wind tunnel balance (MSBS) is an entirely new device for aerodynamic measurement, and it makes the best of the electromagnetic force to suspend the aircraft model in the wind tunnel without contact. Compared with conventional wind tunnel balance, it absolutely abandons the model support and airflow interference. Therefore, the aerodynamic measurement environment is more authentic and the aerodynamic measurement results are more accurate. The electromagnetic field in MSBS plays a major role in bearing the force of wind. The numerical computation and finite element numerical analysis are performed to investigate key factors of electromagnetic force under different conditions. The calculation results based on finite element method (FEM) have revealed that the diameter and the spacing of of the axial coil, the number of segments and the pitch angle of the suspension model are key factors of electromagnetic force. Based on the above key factors, the structure of the magnetic suspension balance is optimized to maximize the electromagnetic force under multiple constraints.

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14

Jia, Zhenyuan, Yifei Gao, Zongjin Ren, Shengnan Gao, and Yongyan Shang. "Design and calibration method for a novel six-component piezoelectric balance." Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science 227, no. 8 (July 30, 2013): 1841–52. http://dx.doi.org/10.1177/0954406213499285.

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Wind tunnel balance is one of the most important measurement equipments in aerodynamic testing. In this paper, a new six-component piezoelectric balance is developed to measure the dynamic impact loading force in the wind tunnel. The arrangement mode of the triaxial piezoelectric load cells is confirmed based on the theory analysis. Furthermore, the mathematical model is established according to the calibration experimental results. Support vector machine is proposed to develop the piezoelectric balance calibration. It is an effective method to predict the model using small samples and reduce the duration of the calibration. The results of prediction are compared to the conventional calibration and the dynamic step response. The linearity and repeatability of the balance are within 0.2% and 0.5%, respectively, and the interference error has been reduced using the support vector machine method. The experimental results have shown that the four supports arrangement mode can reduce the area of attack and enhance the measuring range of the balance. The dynamic characteristics of the piezoelectric balance performed by the step response test show that the designed balance is feasible to measure the dynamic impact airloads in a wind tunnel.

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15

Mikhailov, Yu S., and Yu G. Stepanov. "SIMULATION OF 2D FLOW AROUND OF AIRFOILS AT LOW-SPEED WIND TUNNEL WITH OPEN JET TEST-SECTION." Civil Aviation High TECHNOLOGIES 22, no. 1 (February 27, 2019): 51–62. http://dx.doi.org/10.26467/2079-0619-2019-22-1-51-62.

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At present, there is a great interest in the development of new airfoils for wind turbines and high-lift wings of unmanned aerial vehicles (UAV). The requirements for such airfoils differ from conventional aircraft airfoils, because of structural reasons and extreme operating conditions. So, wind turbine airfoils operate frequently under fully separated flow when stall is used for power regulation at high wind speeds. At the same time design of airfoils for wings UAV poses the problem of availability of high-lift at low Reynolds number. Modern airfoils are to a large extent developed from numerical methods. However, the complex flow conditions such as separation at high angles of attack, laminar separation bubbles and the transition from laminar to turbulent flow are difficult to predict accurately. Hence, testing of airfoils at a two-dimensional condition is an important phase in airfoil design. The development and validation of a 2D testing facility for investigation of single and multi-element airfoils in the wind tunnel Т-102 with open test section are considered in this article. T-102 is a continuous-operation, closed-layout wind tunnel with two reverse channels. The test section has an elliptical cross-section of 4 ×2,33 m and a length of 4 m. Two big flat panels of the L × H=3 ×3,9 m size installed upright on balance frame aligned with the free stream are used for simulating two-dimensional flow in the tunnel test section. The airfoil section in the layout of a rectangular wing is mounted horizontally between flat panels with minimum gaps to ensure 2D flow conditions. The aerodynamic forces and pitch moment acting on the model were measured by wind tunnel balance. To determine boundary corrections for a new test section of wind tunnel, the experimental investigation of three geometrically similar models has been executed. The use of boundary corrections has provided good correlation of the test data of airfoil NACA 6712 with the results obtained from the wind tunnel except for lift and drag coefficient values at high angles of attack.

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16

CRIVELLI, PHILIP, ENRICO PATERNA, and MICHAEL LEHNING. "Spatiotemporal dynamics of snow erosion, deposition and horizontal mass flux." Journal of Glaciology 65, no. 250 (March 22, 2019): 249–62. http://dx.doi.org/10.1017/jog.2019.3.

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ABSTRACTThe quantification of snow transport, both in wind tunnels and the field, apply particle counting methods limited to punctual sampling of relatively small volumes. Particle counting can only capture horizontal mass fluxes, failing to measure snow erosion or deposition. Herein, we present a novel low-cost sensor tool, based on a Microsoft Kinect, adapted to capture snow surface changes during snow drifting at unprecedented spatial and temporal resolutions. In the wind tunnel setting of these experiments we observe a balance between erosion and deposition at low wind speeds, while erosion is dominant at higher wind speeds. Significant differences in power spectral densities of surface mass flux and horizontal particle mass flux are observed. We show that for the saltation-length-scale parameter λ = 1, the integrated particle flux can be used to estimate the total surface mass flux in the wind tunnel. This provides an important basis to interpret mass flux measurements in the field.

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17

Chen, Jian Zhong, and Pei Qing Liu. "Test Technique Research for the Hinge Moment of a Grid Fin in High Speed Wind Tunnel." Applied Mechanics and Materials 574 (July 2014): 480–84. http://dx.doi.org/10.4028/www.scientific.net/amm.574.480.

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In order to study the test technique for the hinge moment of a grid fin in wind tunnel, a platform based on half model support technique was established in FL-23 and FL-31 wind tunnel in China Aerodynamics Research & Development Center (CARDC). The platform developed a wind tunnel test balance, rudder control system and the aerodynamics measurement system. This test technique was important to optimize aerodynamic configurations of a grid fin, design or evaluate the capability of the rudder control system. Nomenclature

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18

Shan, Wen Shan, Bo Li, Jing Bo Yang, and Yang Liu. "Wind Tunnel Test on Wind-Induced Aerodynamic Force of Transmission Tower." Applied Mechanics and Materials 578-579 (July 2014): 427–31. http://dx.doi.org/10.4028/www.scientific.net/amm.578-579.427.

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Wind-induced aerodynamic force is the important parameter for transmission tower design. Based on force balance test, the tower and cross arm of typical 500kV power transmission tower have been investigated in wind tunnel using three wind speeds considering Reynolds effect. The test results show that the shape coefficient keeps the same at different wind speed, which means that Reynolds effect on transmission tower can be ignored. Then, the shape coefficients of tower and cross arm are provided.

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19

Matys, Piotr, and Andrzej Flaga. "Wind tunnel model tests of Magnus type wind rotors with a horizontal rotation axis." Budownictwo i Architektura 12, no. 2 (June 11, 2013): 151–56. http://dx.doi.org/10.35784/bud-arch.2115.

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The paper presents results of wind tunnel tests of horizontal axis wind rotors of Magnus type. Firstly, measurements of aerodynamic side (lift) force and aerodynamic drag on rotating cylinder attached to horizontal aerodynamic balance were performed. Secondly, the model of single-blade rotor with counterbalance was tested.

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20

Virmavirta, Mikko, Juha Kivekäs, and Paavo Komi. "Ski Jumping Takeoff in a Wind Tunnel With Skis." Journal of Applied Biomechanics 27, no. 4 (November 2011): 375–79. http://dx.doi.org/10.1123/jab.27.4.375.

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The effect of skis on the force–time characteristics of the simulated ski jumping takeoff was examined in a wind tunnel. Takeoff forces were recorded with a force plate installed under the tunnel floor. Signals from the front and rear parts of the force plate were collected separately to examine the anteroposterior balance of the jumpers during the takeoff. Two ski jumpers performed simulated takeoffs, first without skis in nonwind conditions and in various wind conditions. Thereafter, the same experiments were repeated with skis. The jumpers were able to perform very natural takeoff actions (similar to the actual takeoff) with skis in wind tunnel. According to the subjective feeling of the jumpers, the simulated ski jumping takeoff with skis was even easier to perform than the earlier trials without skis. Skis did not much influence the force levels produced during the takeoff but they still changed the force distribution under the feet. Contribution of the forces produced under the rear part of the feet was emphasized probably because the strong dorsiflexion is needed for lifting the skis to the proper flight position. The results presented in this experiment emphasize that research on ski jumping takeoff can be advanced by using wind tunnels.

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21

Aboelezz, Ahmed, Yunes Elqudsi, Mostafa Hassanalian, and Ahmed Desoki. "WIND TUNNEL CALIBRATION, CORRECTIONS AND EXPERIMENTAL VALIDATION FOR FIXED-WING MICRO AIR VEHICLES MEASUREMENTS." Aviation 23, no. 4 (February 17, 2020): 104–13. http://dx.doi.org/10.3846/aviation.2019.11975.

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The increase in the number of Unmanned Aerial Vehicles (UAVs) and Micro Air Vehicles (MAVs), which are used in a variety of applications has led to a surge in low Reynolds number aerodynamics research. Flow around fixedwing MAVs has an unusual behavior due to its low aspect ratio and operates at low Reynolds number, which demanded to upgrade the used wind tunnel for this study. This upgrade enables measuring the small aerodynamics forces and moment of fixed-wing MAVs. The wind tunnel used in this work is upgraded with a state of art data acquisition system to deal with the different sensors signals in the wind tunnel. For accurate measurements, the sting balance, angle sensor, and airspeed sensor are calibrated. For validation purposes, an experiment is made on a low aspect ratio flat plate wing at low Reynolds number, and the measured data are corrected and compared with published results. The procedure presented in this paper for the first time gave a detailed and complete guide for upgrading and calibrating old wind tunnel, all the required corrections to correct the measured data was presented, the turbulence level correction new technique presented in this paper could be used to estimate the flow turbulence effect on the measured data and correct the measured data against published data.

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22

Landman, Drew, and David Yoder. "Wind-Tunnel Balance Calibration with Temperature Using Design of Experiments." Journal of Aircraft 51, no. 3 (May 2014): 841–48. http://dx.doi.org/10.2514/1.c032416.

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23

Kai, Daiki, Hiroki Sugiura, and Asei Tezuka. "Magnetic Suspension and Balance System for High-Subsonic Wind Tunnel." AIAA Journal 57, no. 6 (June 2019): 2489–95. http://dx.doi.org/10.2514/1.j057679.

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24

Traub, Lance W. "Design of a Low-Cost Rapid-Prototyped Wind-Tunnel Balance." Journal of Aircraft 55, no. 5 (September 2018): 2149–53. http://dx.doi.org/10.2514/1.c034982.

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Ho, T. C. Eric, Un Yong Jeong, and Peter Case. "Components of wind -tunnel analysis using force balance test data." Wind and Structures 18, no. 4 (April 25, 2014): 347–73. http://dx.doi.org/10.12989/was.2014.18.4.347.

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26

Kaltenhauser, Albert, Siegfried Kolb, Frank Ullrich, and Lubomir Polansky. "New balance platform module in the BMW acoustic wind tunnel." ATZ worldwide 108, no. 12 (December 2006): 11–14. http://dx.doi.org/10.1007/bf03225199.

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27

Li, Shichao, Zihao Liu, Fan Zhao, and Hongli Gao. "A New Hypersonic Wind Tunnel Force Measurement System to Reduce Additional Bending Moment and Avoid Time-Varying Stiffness." Sensors 22, no. 7 (March 27, 2022): 2572. http://dx.doi.org/10.3390/s22072572.

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In order to improve traditional hypersonic wind tunnel airframe/propulsion integrated aerodynamic testing technology for hypersonic vehicles, a new force measurement system called the aerodynamic force measuring support (AFMS) was designed. The AFMS effectively overcomes the defect that the traditional internal box-balance occupies a large amount of internal space in the aircraft test model, which makes the airframe/propulsion integrated aerodynamic test more difficult. The AFMS also alleviates the interference of the additional bending moment caused by the non-coincidence between the calibration center of traditional external box-balance and the gravity center of the aircraft test model, innovatively designing a convex structure in the joint part of the force measuring system. Furthermore, the AFMS effectively overcomes the time-varying stiffness of joints caused by test model vibration in hypersonic wind tunnel testing, which eventually leads to test errors. Compared with the traditional box-balance, the AFMS proposed in this study has sufficient design space. This ensures more thorough aerodynamic decomposition of the AFMS and less interference between channels, whilst also having the advantages of the large support stiffness of traditional box-balance. Thus, the AFMS provides a new technical path for airframe/propulsion integrated aerodynamic testing of air-breathing hypersonic vehicles in a hypersonic wind tunnel.

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López-de-Celis, Carlos, Daniel Zegarra-Chávez, Aïda Cadellans-Arróniz, Andoni Carrasco-Uribarren, Pedro Izquierdo-Nebreda, Max Canet-Vintró, Jacobo Rodríguez-Sanz, and Albert Pérez-Bellmunt. "Study on Balance and Postural Control According to the Stabilometry in Indoor Skydivers: A Cross-Sectional Study." International Journal of Environmental Research and Public Health 20, no. 1 (December 30, 2022): 635. http://dx.doi.org/10.3390/ijerph20010635.

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Background: The wind tunnel is a compression cabin through which a stream of air rises homogeneously, generated by fans. To perform different acrobatics, indoor skydivers have to change their body position by turning their body and orientation in reference to the space. Thus, the vestibular, visual and somatosensory systems are subjected to multiple disturbances. Postural control could be affected by altering the visual, vestibular and somatosensory systems during indoor skydiving in the wind tunnel. The aim of this study is to describe the influence of a standard wind tunnel training session on postural control in a normal gravitational situation in indoor skydiving. Methods: Ten indoor skydivers registered with the Royal Spanish Aeronautical Federation, who had participated in national or international competitions one year ago, were recruited. A single 30 min training session was performed. Postural control was assessed through posturographic analysis using a stabilometric platform immediately before and after the training session. The variables studied were related to the relative position and length of the centre of pressure. Results: No statistically significant changes were found between the initial and final assessment for the posturographic variables studied. Conclusions: No differences in postural control were found after a standard wind tunnel training session in indoor competition skydivers.

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29

Qiu, Huacheng, Fu Min, Yanguang Yang, Zengling Ran, and Jinxin Duan. "Hypersonic Aerodynamic Force Balance Using Micromachined All-Fiber Fabry–Pérot Interferometric Strain Gauges." Micromachines 10, no. 5 (May 11, 2019): 316. http://dx.doi.org/10.3390/mi10050316.

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This paper presents high-sensitivity, micromachined all-fiber Fabry–Pérot interferometric (FFPI) strain gauges and their integration in a force balance for hypersonic aerodynamic measurements. The FFPI strain gauge has a short Fabry–Pérot cavity fabricated using an excimer laser etching process, and the deformation of the cavity is detected by a white-light optical phase demodulator. A three-component force balance, using the proposed FFPI gauges as sensing elements, was fabricated, calibrated, and experimentally evaluated. To reduce thermal output of the balance, a simple and effective self-temperature compensation solution, without external temperature sensors, is proposed and examined through both oven heating and wind tunnel runs. As a result of this approach, researchers are able to use the balance continuously throughout a wide range of temperatures. During preliminary testing in a hypersonic wind tunnel with a free stream Mach number of 12, the measurement accuracies of the balance were clearly improved after applying the temperature self-compensation.

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30

Boom, R., Y. Eyssa, G. McIntosh, M. Abdelsalam, R. Scurlock, Y. Wu, M. Goodyer, K. Balcerek, J. Eskins, and C. Britcher. "Superconducting electromagnets for large wind tunnel magnetic suspension and balance systems." IEEE Transactions on Magnetics 21, no. 2 (March 1985): 444–47. http://dx.doi.org/10.1109/tmag.1985.1063793.

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31

Yang, Shuang-Long, and Ke-Jun Xu. "Frequency-Domain Decoupling-Correction Method for Wind Tunnel Strain-Gauge Balance." IEEE Transactions on Instrumentation and Measurement 62, no. 9 (September 2013): 2596–608. http://dx.doi.org/10.1109/tim.2013.2259100.

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32

Raju, S. P. Govinda, and K. R. Y. Simha. "Timoshenko-Wagner-Kappus torsion bending theory and wind tunnel balance design." Resonance 7, no. 10 (October 2002): 54–58. http://dx.doi.org/10.1007/bf02835543.

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33

Li, Yan, Fang Feng, Sheng Mao Li, Wen Qiang Tian, and Kotaro Tagawa. "Wind Tunnel Test on Icing on a Straight Blade for Vertical Axis Wind Turbine." Advanced Materials Research 301-303 (July 2011): 1735–39. http://dx.doi.org/10.4028/www.scientific.net/amr.301-303.1735.

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Icing on blade surface of the wind turbine set in cold regions is a serious problem. To invest the mechanism of icing and ice accretion on blade surface, wind tunnel tests were carried out on a static straight blade used for the straight-bladed vertical axis wind turbine by using an icing wind tunnel. The icing and ice accretions on blade surface at some typical angles of attack were observed and recorded in a fixed wind speed and steady flow discharge. The mass of ice accretions on the surface of blade were also measured and compared. At the same time, the drag and lift coefficients were tested by a three-component force balance. Based on the test results, the factors affecting the mass and characteristic of ice accretions and the drag and lift coefficients of the straight blade were discussed.

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34

Wang, Yeguang, Shitong Jian, Zhigang Wang, Rui Fan, Peng Han, and Yongxi Lyu. "An Intelligent Algorithm for Aerodynamic Parameters Calibration of Wind Tunnel Experiment at a High Angle of Attack." International Journal of Aerospace Engineering 2023 (January 7, 2023): 1–15. http://dx.doi.org/10.1155/2023/3093526.

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In this paper, an intelligent algorithm for the aerodynamic parameter calibration of wind tunnel experiments of advanced layout aircraft at a high angle of attack is proposed. The proposed algorithm is based on a homologous comparison and tuning algorithm, and it can effectively improve the accuracy of the wind tunnel experiment model. First, based on the analysis of large oscillation wind tunnel experimental data of an advanced layout scaled aircraft, the high angle of attack wind tunnel experimental model composed of static derivative, dynamic derivative, and rotating balance derivative is established. Second, to improve the accuracy of the wind tunnel experimental model effectively, the idea of combing layered calibration and intelligent algorithm for high angle of attack homologous comparison correction is proposed. The proposed method solves the problems of complex structure, a large amount of data, and poor accuracy in homologous comparison of high angle of attack aerodynamic models of advanced layout aircraft. Finally, the homologous comparison interface software is designed based on MATLAB GUI, which integrates the proposed methods and ideas and realizes effective adjustment of aerodynamic parameters of high angle of attack simulation flight wind tunnel test of an advanced layout aircraft. This study provides a reliable engineering and technical means for subsequent high angle of attack flight test verification of the advanced layout aircraft.

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35

Xia, Daqiao, and Kangfu Peng. "Wind Load and Wind Vibration Response of a TV Tower Based on Force Measurement Test in a Wind Tunnel." Advances in Civil Engineering 2022 (January 29, 2022): 1–12. http://dx.doi.org/10.1155/2022/7629438.

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Television towers have a complex aerodynamic shape and low damping characteristics. As such, the wind load and the wind induction response are key factors in their design and maintenance. To study these two parameters of high-rise TV towers, a wind tunnel force test was conducted at a height of 280 m using the Foshan TV tower as a model. The TV tower model was divided into seven detachable sections. Three wind fields with different turbulence intensities were simulated in the wind tunnel, corresponding to different sections, and lateral force tests were performed on each section using a high-frequency dynamic balance. The experimental results were used to calculate the wind-induced response when considering the modal (first three-order) coupled response and were compared with the wind-induced response calculated using the complete quadratic combination (CQC) method. The results revealed that equivalent static wind loads (ESQL) and CQC calculation methods were used in this study, and a higher degree of coincidence was observed, which may be useful in engineering practice.

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Doolan, Con J. "Numerical Evaluation of Contemporary Low-Speed Wind Tunnel Contraction Designs." Journal of Fluids Engineering 129, no. 9 (May 31, 2007): 1241–44. http://dx.doi.org/10.1115/1.2771578.

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A potential flow and viscous flow solver have been coupled to produce a robust computational tool useful for the design of low-speed wind tunnel contractions. After validation against published numerical and experimental wind tunnel data, the method is used to evaluate recently proposed contraction shapes from the literature. The results show that, on balance, a fifth-order polynomial provides a good design solution. Newly proposed shapes will either improve available flow area at the expense of contraction outlet flow uniformity or vice versa.

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Wang, Shu Liang, Shu Guo Liang, Liang Hao Zou, and Xiang Yang Zhou. "Research on the Wind Tunnel Force Balance Tests of Long-Span Closed Coal Trestle." Applied Mechanics and Materials 477-478 (December 2013): 797–802. http://dx.doi.org/10.4028/www.scientific.net/amm.477-478.797.

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Structures with long span and high flexibility are very sensitive to the wind forces, so it is necessary to study on the wind effects on such structures. In this paper, based on section model wind tunnel high-frequency force balance tests, two horizontal base bending moments and shear forces of the typical supporting columns as well trestle bridge deck of the closed coal trestle under different wind directions were measured. The shape coefficients and their variations with the wind directions of the typical supporting columns as well trestle bridge deck were calculated then analyzed by the mean values of base forces. The experimental values of the shape coefficients were compared with those in the Chinese Load Code, the results shown that both were in good agreement, which verified the reliability of the test, which also illustrated that wind-resistant design of the coal trestle in accordance with the Code was reasonable. Based on analysis of the variances of base forces between overall model with and without surrounding buildings, influences of surroundings buildings were studied. Interference factors were proposed which provided the basis for the base forces checking and wind-resistant design of the long-span closed coal trestle structures.

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Chen, Jinjin, Xing Shen, Fanfan Tu, and Ehtesham Mustafa Qureshi. "Experimental Research on an Active Sting Damper in a Low Speed Acoustic Wind Tunnel." Shock and Vibration 2014 (2014): 1–10. http://dx.doi.org/10.1155/2014/524351.

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Wind tunnels usually use long cantilever stings to support aerodynamic models in order to reduce support system flow interference on experimental data. However, such support systems are a potential source of vibration problems which limit the test envelope and affect data quality due to the inherently low structural damping of the systems. When exposed to tunnel flow, turbulence and model flow separation excite resonant Eigenmodes of a sting structure causing large vibrations due to low damping. This paper details the development and experimental evaluation of an active damping system using piezoelectric devices with balance signal feedback both in a lab and a low speed acoustic wind tunnel and presents the control algorithm verification tests with a simple cantilever beam. It is shown that the active damper, controlled separately by both PID and BP neural network, has effectively attenuated the vibration. For sting mode only, 95% reduction of displacement response under exciter stimulation and 98% energy elimination of sting mode frequency have been achieved.

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39

Ryś, Jan, and Marcin Augustyn. "Innovative Construction of 3-Component Aerodynamic Balance." Key Engineering Materials 542 (February 2013): 171–77. http://dx.doi.org/10.4028/www.scientific.net/kem.542.171.

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This paper deals with a description of a new type an aerodynamic balance used in a wind tunnel for measuring forces acting on a model. A concept of the strain gauge balance in which the three component of aerodynamically force can be measured was presented. The tests proved good measuring accuracy of this construction. On the basis of such a solution three component of force and aerodynamic load factors can be easily evaluated.

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Naruse, Renji, Hiroshi Nishimura, and Norikazu Maeno. "Structural Characteristics of Snow Drifts and Cornices." Annals of Glaciology 6 (1985): 287–88. http://dx.doi.org/10.3189/1985aog6-1-287-288.

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Sorting effects of snow particles during deposition were studied in field observations of snow cornices and wind-tunnel experiment of snow drifts. Grain size, density and hardness were larger at the upper part (root) of a cornice than at the lower part (scarp). Experiments with the use of a horizontal step in a wind-tunnel revealed the importance of redistribution of snow particles on the formation of drifts: at wind speed of 5 m/s, about 40% of particles fallen onto the surface behind a 0.1-m high step were removed by erosion, rebound and creep. The surface mass balance controlling the growth and shape of a drift are briefly discussed.

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Naruse, Renji, Hiroshi Nishimura, and Norikazu Maeno. "Structural Characteristics of Snow Drifts and Cornices." Annals of Glaciology 6 (1985): 287–88. http://dx.doi.org/10.1017/s026030550001065x.

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Sorting effects of snow particles during deposition were studied in field observations of snow cornices and wind-tunnel experiment of snow drifts. Grain size, density and hardness were larger at the upper part (root) of a cornice than at the lower part (scarp). Experiments with the use of a horizontal step in a wind-tunnel revealed the importance of redistribution of snow particles on the formation of drifts: at wind speed of 5 m/s, about 40% of particles fallen onto the surface behind a 0.1-m high step were removed by erosion, rebound and creep. The surface mass balance controlling the growth and shape of a drift are briefly discussed.

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42

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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43

Xu, An, Haidong Lin, Jiyang Fu, and Weixing Sun. "Wind-resistant structural optimization of supertall buildings based on high-frequency force balance wind tunnel experiment." Engineering Structures 248 (December 2021): 113247. http://dx.doi.org/10.1016/j.engstruct.2021.113247.

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44

Aguirre, Miguel Angel, Ramiro Bracco, Fabio Milanese, and Matías Meroniuc. "Design of an external six-component wind tunnel balance with floating frame." International Journal of Aerodynamics 7, no. 2 (2021): 105. http://dx.doi.org/10.1504/ijad.2021.112709.

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Aguirre, Miguel Angel, Matías Meroniuc, Fabio Milanese, and Ramiro Bracco. "Design of an external six-component wind tunnel balance with floating frame." International Journal of Aerodynamics 7, no. 2 (2021): 105. http://dx.doi.org/10.1504/ijad.2021.10034916.

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46

Wu, Chen-Wu, Cong Liu, Deng-Liang Hu, Hong-Li Liu, and He-Ji Huang. "Design of a milli-newton force balance for hypersonic rarefied wind tunnel." Measurement 185 (November 2021): 110006. http://dx.doi.org/10.1016/j.measurement.2021.110006.

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47

Burns, Devin E., Kenneth G. Toro, Peter A. Parker, S. Melissa Rivers, Harald Quix, and Martin Wright. "Evaluation of Cryogenic Force Balance Calibration Methodologies Relative to Wind Tunnel Results." Journal of Aircraft 56, no. 4 (July 2019): 1398–406. http://dx.doi.org/10.2514/1.c035211.

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48

Xu, Xin, Dawei Liu, Yujie Shi, Dehua Chen, and Keming Cheng. "Flange balance application in high speed wind tunnel test of BWB aircraft." Journal of Physics: Conference Series 1324 (October 2019): 012055. http://dx.doi.org/10.1088/1742-6596/1324/1/012055.

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TAKITA, Kazuyuki, Koki YAMAMOTO, Hiroki OGURI, Tatsuya TAKATSUKA, Yusuke ARAKI, Takeshi NARUO, and Taketo MIZOTA. "G1101 Trial development of wind tunnel balance with air suspended load cell." Proceedings of the Fluids engineering conference 2013 (2013): _G1101–01_—_G1101–04_. http://dx.doi.org/10.1299/jsmefed.2013._g1101-01_.

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TAKATSUKA, Tatsuya, Yuusuke ARAKI, Hiroki Oguri, Hikaru NAGAMINE, Katsutoshi TANAKA, and Taketo MIZOTA. "C14 Trial development of wind tunnel balance with air suspended road cell." Proceedings of Conference of Kyushu Branch 2012 (2012): 87–88. http://dx.doi.org/10.1299/jsmekyushu.2012.87.

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