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Journal articles on the topic 'Wind Tunnel Test Rig'

Author: Grafiati

Published: 11 September 2021

Last updated: 8 February 2022

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1

Johl, G., M. Passmore, and P. Render. "Design and performance of thin, circular arc, wind-tunnel turning vanes." Aeronautical Journal 111, no. 1116 (February 2007): 115–18. http://dx.doi.org/10.1017/s0001924000001810.

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Although test rig data exists for ¼ circle turning vanes, the actual performance of these vanes once installed in a wind tunnel, and the extent to which test rig results are replicated, is rarely known. This paper compares pressure loss coefficient and velocity profile data from a vane test module with measurements taken in the low speed wind tunnel described in Ref. 1.

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2

SUZUKI, Minoru. "Wind Tunnel Test of Railway Vehicle Under Cross Wind Using Moving Model Rig." Wind Engineers, JAWE 36, no. 3 (2011): 258–63. http://dx.doi.org/10.5359/jawe.36.258.

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3

Wu, Han, Chuntai Zheng, Peng Zhou, Ryu Fattah, Xin Zhang, Guocheng Zhou, and Bao Chen. "The multi-functional rotor aerodynamic and aeroacoustic test platform at HKUST." INTER-NOISE and NOISE-CON Congress and Conference Proceedings 263, no. 2 (August 1, 2021): 4410–17. http://dx.doi.org/10.3397/in-2021-2695.

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This paper describes the multi-functional rotor noise and aerodynamics test platform at the Hong Kong University of Science and Technology (HKUST). To investigate the noise characteristics of propellers with aerodynamic flows, the test rig is installed in the 2.5×2 (m) low-speed and low-noise wind tunnel in the Aerodynamic and Acoustic Facility (AAF) at HKUST. The wind tunnel can facilitate flow from 0 to 40 m/s. The test rig is assembled in a turntable on the ceiling of the tunnel wall, which enables the testing range of pitch angle can vary from 0° (axial flow) to 90° (parallel flow), with an accuracy of 0.1°. The noise produced by the rotor is measured by a set of wall-mounted surface microphones. Semi-empirical calibration is conducted to quantify the noise reflection by the tunnel walls. A low-noise struct has been designed and manufactured to locate a set of far-field microphones equipped with nosecone, to improve the quality of acoustic measurement inside the flow. In addition, a synchronized system is developed to conduct the phase-locking Particle Image Velocimetry (PIV) measurement on the rotor, to study the flow pattern to better understand the noise generation mechanism.

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4

Huang, Min, Zhong-wei Wang, Xing-Bao Yang, Zhen-yun Guo, and Yao-bin Niu. "Preliminary Validation of the Wind Tunnel Based Flight Control System Evaluation Method." MATEC Web of Conferences 179 (2018): 03021. http://dx.doi.org/10.1051/matecconf/201817903021.

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As mathematical models of aircraft aerodynamics and rudder loadings always have to be built in the hardware-in-the-loop simulation, wind tunnel based flight control system (FCS) evaluation methods were proposed in order to test and evaluate the flight control systems under real aerodynamic and rudder loading environment. To validate the evaluation method, a wind tunnel based flight control system test was performed in a hypersonic wind tunnel facility. As the aircraft support rig in the wind tunnel is static, the aircraft angle of attack cannot be changed in this test. During the test, the elevator response, the lift force and the pitching moment were measured. By analysing the measured data, the elevator control performance of the pitch control system was determined, and the pitch angle was successfully predicted, but the open-loop pitch control performance was not determined. These results validate the feasibility of evaluating the elevator control performance and predicting the pitch angle of a FCS by the wind tunnel based FCS evaluation method.

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5

Kuk, T., and K. Ro. "Design, test and evaluation of an actively stabilised drogue refuelling system." Aeronautical Journal 117, no. 1197 (November 2013): 1103–18. http://dx.doi.org/10.1017/s0001924000008721.

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Abstract A scale model of aerial refuelling drogue is built and tested to investigate active drogue stabilisation and control concepts. A set of aerodynamic control surfaces is implemented to a conventional, aerodynamically stabilised refuelling drogue. The control surfaces are designed to reduce the response of the drogue motion to atmospheric disturbance and tanker motion. This paper presents the details of design concept and experimental results based on wind-tunnel testing of a ⅓ scale model fabricated for this study. To investigate the proposed active control concept, a dynamic test rig is built for wind-tunnel experiment. The rig basically represents a hose-drogue system in terms of a 4 degree-of-freedom (DoF), single link pendulum model. System identification technique is used to obtain a drogue dynamic model, based on which a feedback control law is developed. Closed-loop dynamic testing is carried out to evaluate the effectiveness of the aerodynamic surface control module and feedback control law.

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6

SUZUKI, Minoru. "G050015 Wind Tunnel Test of Railway Vehicle under Cross Wind by using Moving Model Rig." Proceedings of Mechanical Engineering Congress, Japan 2012 (2012): _G050015–1—_G050015–4. http://dx.doi.org/10.1299/jsmemecj.2012._g050015-1.

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7

SUZUKI, Masahiro, Koji NAKADE, and Minoru SUZUKI. "1312 A wind tunnel test for railway vehicle under cross wind using a moving model rig." Proceedings of the Transportation and Logistics Conference 2009.18 (2009): 231–32. http://dx.doi.org/10.1299/jsmetld.2009.18.231.

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8

Shun, Simon, and Noor Alam Ahmed. "Design of a Dynamic Stall Test Rig." Applied Mechanics and Materials 215-216 (November 2012): 785–95. http://dx.doi.org/10.4028/www.scientific.net/amm.215-216.785.

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Dynamic stall is an aerodynamic phenomenon that may occur when an airfoil is subjected to rapid, cyclical changes in angle of attack with respect to the incident ambient flow. This phenomenon can often produce repeated and significant changes in lift and moment coefficients within very short time frames, which manifest as severe and rapid changes in structural loads. Rotorcraft such as helicopters and wind turbines are particularly susceptible to dynamic stall, which is a highly undesirable operating condition. The condition plays a part in limiting the forward speed of a helicopter whilst also producing cyclical loads that accelerate fatigue. The structural issues are more severe for wind turbines, where blade spans approaching seventy to eighty metres are becoming common. Research into techniques for reducing the severity of the undesirable effects of dynamic stall is often conducting in laboratory environments using wind tunnels as the main investigative tool. The required cyclical changes in angle of attack are achieved by using machines that oscillate the test airfoil about an axis parallel to the span of the wing. Such mechanisms can be powered electrically, mechanically, pneumatically or hydraulically, and have various combinations of complexity, advantages and disadvantages. The current work describes the design process of an electrically powered dynamical stall test rig. The use of CAD / CAM to assist in the performing of design calculations and a comparison of the rig with other mechanisms is presented.

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9

Natili, Francesco, Francesco Castellani, Davide Astolfi, and Matteo Becchetti. "Experimental and Signal Processing Techniques for Fault Diagnosis on a Small Horizontal-Axis Wind Turbine Generator †." Vibration 2, no. 2 (May 9, 2019): 187–200. http://dx.doi.org/10.3390/vibration2020012.

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Small horizontal-axis wind turbine (HAWT) is a technology characterized by non-trivial critical points, basically because it is targeted for domestic use and therefore cheap manufacturing and control must conjugate with good efficiency under possibly complex flow conditions (especially in urban environment). Therefore, dynamical control optimization and noise and vibration mitigation are pressing issues for this kind of technology. Despite this, it is peculiar of small HAWTs that the generator constitutes a non-negligible fraction of the total mass and therefore the electromechanical coupling is relevant, condition monitoring of small HAWT generators is an overlooked topic. The present work is a test case study of damage diagnosis on a permanent magnet generator of a HAWT having 3 kW of maximum power and 2 m of rotor diameter. The experimental analysis is conducted through wind tunnel tests and on a generator test rig where a damaged and an undamaged generators have been driven at different rotational speeds. Vibration measurements are collected in the wind tunnel through radial accelerometers near the rear bearing of the shaft and in the test rig through uni-axial accelerometers (fixed in radial positions, in order to be aligned with front and rear bearings). The test rig data results are particularly useful for studying the low-frequency tail of the vibration spectrum, where the characteristic frequencies of the bearing are located. The experimental data are analyzed in the time and frequency domain for feature extraction: a fault in the cage of the bearing supporting the generator is diagnosed using in particular the spectral coherence analysis.

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10

Lee, Junsik, and Jae-Hak Lee. "Study on Turbulence Intensity Behavior under a Large Range of Temperature Variation." Processes 8, no. 11 (November 3, 2020): 1403. http://dx.doi.org/10.3390/pr8111403.

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The turbulence intensity (TI) is defined as the ratio of fluctuation from the standard deviation of wind velocity to the mean value. Many studies have been performedon TI for flow dynamics and adapted various field such as aerodynamics, jets, wind turbines, wind tunnel apparatuses, heat transfer, safety estimation of construction, etc.The TI represents an important parameter for determining the intensity of velocity variation and flow quality in industrial fluid mechanics. In this paper, computational fluid dynamic (CFD) simulation of TI alteration with increasing temperature has been performed using the finite volume method. A high-temperature—maximum 300 degrees Celsius (°C)—wind tunnel test rig has been used as theapparatus, and velocity was measured by an I-type hot-wire anemometer. The velocity and TI of the core test section were operated at several degrees of inlet temperatures at anair velocity of 20 m/s. The magnitude of TI has a relationship with boundary layer development. The TI increased as temperature increased due to turbulence created by the non-uniformities.

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11

PIRVU, Catalin, Mihai Victor PRICOP, Jean-Philippe PRÉAUD, and Louis WALPOT. "Pitch damping identification in high speed regimes with a free-to-tumble rig." INCAS BULLETIN 12, no. 4 (December 4, 2020): 261–65. http://dx.doi.org/10.13111/2066-8201.2020.12.4.24.

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Many re-entry bodies, even if they are debris or not, have nonlinear dynamic stability characteristics that produce oscillations in flight. The free-to-tumble techniques can be used to extract damping coefficient of specific body for planetary entry. The curve fitting approach is used to predict oscillatory behavior and the damping coefficient for the various test conditions of the wind tunnel obtained after the experimental data. The analysis presented provides an overview of the free-to-tumble test techniques and illustrates the effects of dynamic stability of the inter-stage tronconical system. It is proposed that these test techniques and curve fitting solution be refined in the future to better define the dynamic stability curves for the re-entry bodies.

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12

Li, Xiaozhen, Yiling Tan, Xiaowei Qiu, Zhenhua Gong, and Ming Wang. "Wind tunnel measurement of aerodynamic characteristics of trains passing each other on a simply supported box girder bridge." Railway Engineering Science 29, no. 2 (February 26, 2021): 152–62. http://dx.doi.org/10.1007/s40534-021-00231-4.

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AbstractThe aerodynamic performance of high-speed trains passing each other was investigated on a simply supported box girder bridge, with a span of 32 m, under crosswinds. The bridge and train models, modeled at a geometric scale ratio of 1:30, were used to test the aerodynamic forces of the train, with the help of a designed moving test rig in the XNJD-3 wind tunnel. The effects of wind speed, train speed, and yaw angle on the aerodynamic coefficients of the train were analyzed. The static and moving model tests were compared to demonstrate how the movement of the train influences its aerodynamic characteristics. The results show that the sheltering effect introduced by trains passing each other can cause a sudden change in force on the leeward train, which is further influenced by the wind and running speeds. Detailed analyses related to the effect of wind and train speeds on the aerodynamic coefficients were conducted. The relationship between the change in aerodynamic coefficients and yaw angle was finally described by a series of proposed fitting formulas.

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13

I. Ismail, N., H. Yusoff, Hazim Sharudin, Arif Pahmi, H. Hafi, and Mahadzir M.M. "Lift distribution of washout twist morphing MAV wing." International Journal of Engineering & Technology 7, no. 4.13 (October 9, 2018): 89. http://dx.doi.org/10.14419/ijet.v7i4.13.21337.

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Micro Air Vehicle, or also commonly known as MAV, is a miniature aircraft that has been gaining interest in the industry. MAV is defined as a flying platform with 15cm wingspan and operates at a speed of around 10m/s. Recently, MAV has been exposed with the latest development and link towards the biologically-inspired designs such as morphing wing. Twist morphing wing is one of the latest MAV wing design developments. The application of Twist Morphing (TM) on MAV wing has been previously known to produce better aerodynamic performance. Previous study in washin TM wing has shown a promising possibility of generating higher lift force. Despite the benevolent performance exhibited by the washin TM wing, the lift distribution for the washout type of TM MAV is relatively unknown and still open to be explored. This is probably due to the lack of experimental test rig to produce the washout twist morphing motion on the MAV wing. Therefore, this research aims to produce a special test rig for washout TM wing that is compatible for wind tunnel experimental testing. By using the special test rig, the experimental investigation on the lift performance of washout TM MAV wing can be done. Based on the wing deformation results, it clearly shows that the proposed test rig is capable to produce up to 19.5mm tip deflection at the morphing point, which is also resulting in a significant morphing motion. Higher morphing force induces larger morphing motion. Based on the lift distribution results, they show that the morphing motion has significantly affected the overall lift distribution on the MAV wing. The morphing motion on TM wing has produced at least 17.6% and 5.33% lower CL and CLmax magnitude, respectively, with the membrane wing especially at the pre-stall region. However, the TM wing is still able to maintain the stall angle similar to the baseline wing at αstall= 31°. By maintaining high αstall value with lower CL and CLmax magnitude, TM wing produces more agility for the MAV maneuverability that will be useful for indoor mission or obstacle avoidance flight.

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14

Slama, Vaclav, Bartolomej Rudas, Jiri Ira, Ales Macalka, Petr Eret, and Volodymyr Tsymbalyuk. "CFD prediction of flutter of turbine blades and comparison with an experimental test case." MATEC Web of Conferences 168 (2018): 02005. http://dx.doi.org/10.1051/matecconf/201816802005.

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Last stage blades are a key element of steam turbines and in many ways determine the turbine configuration alongside with the overall turbine performance. The total efficiency of the low pressure turbine section can be increased by extending the last stage blades. The design process of such long blades involves a flutter analysis using CFD tools which have to be validated by measurements in test facilities under various operating conditions. Experimental data obtained from a subsonic wind tunnel with an oscillating turbine blade cascade, which is available at the Department of Power System Engineering at the University of West Bohemia, was compared with simulations in ANSYS CFX currently used in the Doosan Škoda Power. The paper provides a brief summary of experimental rig description, CFD tool setup and the results for the case of a travelling wave mode with the pure torsion motion of amplitude of 0.5°, Ma = 0.2, reduced frequency of 0.38 and angle of attack +5°.

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15

Wang, Chang, Minqi Huang, Xianmin Peng, Guichuan Zhang, Min Tang, and Haowen Wang. "Wind Tunnel Studies on Hover and Forward Flight Performances of a Coaxial Rigid Rotor." Aerospace 8, no. 8 (July 28, 2021): 205. http://dx.doi.org/10.3390/aerospace8080205.

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The aerodynamic performance of a reduced-scale coaxial rigid rotor system in hover and steady forward flights was experimentally investigated to gain insights into the effect of interference between upper and lower rotors and the influences of the advance ratio, shaft tilt angle and lift offset. The rotor system featured by 2 m-diameter, four-bladed upper and lower hingeless rotors and was installed in a coaxial rotor test rig. Experiments were conducted in the Φ3.2 m wind tunnel at China Aerodynamics Research and Development Center (CARDC). The rotor system was tested in hover states at collective pitches ranging from 0° to 13° and it was also tested in forward flights at advance ratios up to 0.6, with specific focus on the shaft tilt angle and lift offset sweeps. To ensure that the coaxial rotor was operating in a similar manner to that of the real flight, the torque difference was trimmed to zero in hover flight, whilst the constant lift coefficient was maintained in forward flight. An isolated single-rotor configuration test was also conducted with the same pitch angle setting in the coaxial rotor. The hover test results demonstrate that the figure of merit (FM) value of the lower rotor is lower than that of the upper rotor, and both are lower than that of the isolated single rotor. Moreover, the coaxial rotor configuration can contribute to better hover efficiency under the same blade loading coefficient (CT/σ). In forward flight, the effective lift-to-drag (L/De) ratio of the coaxial rigid rotor does not monotonously change as the advance ratio increases. Increases in the required power and drag in the case with a high advance ratio of 0.6 leads to the decreasing L/De ratio of the rotor. Meanwhile, the L/De ratio of the rotor is relatively high when the rotor shaft is tilted backward. The increasing lift offset tends to result in reduced required rotor power and an increase in the rotor drag. When the effect of the reduced rotor power is greater than that of the increased rotor drag, the L/De ratio increases as the lift offset increases. The L/De ratio can benefit significantly from lift offset at a high advance ratio, but it is much less influenced by lift offset at a low advance ratio. The forward performance efficiency of the upper rotor is poorer than that of the lower rotor, which is significantly different from the case in the hover flight.

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16

Barrett, R. V. "Transition detection for laminar flow aircraft using microphones beneath the surface of laser drilled suction panels." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 214, no. 3 (March 1, 2000): 143–55. http://dx.doi.org/10.1243/0954410001531971.

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The possibility of detecting transition through the very small laser drilled perforations in panels representing the suction surface of a hybrid laminar flow aircraft is examined. The method uses miniature microphones to detect changes to the noise received from the boundary layer. Tests using a flat plate rig in a low-turbulence wind tunnel at Reynolds numbers up to 3.8 million per metre, demonstrate that the boundary layer state can be defined in this manner, most simply through measurement of the root mean square (r.m.s.) of the microphone signal. It is shown that the r.m.s. reaches a peak in the transition zone and that when the boundary layer is fully turbulent the value is still significantly higher than it was before transition. Porosity in the range 0.8-6.4 percent was examined, with nominal hole diameters of 0.06 and 0.10 mm in 0.9 mm thick laser drilled suction surface specimens. Suction flow through the surface was found not adversely to affect the operation of the system. The experiment was limited to low Reynolds numbers because the high background noise in the wind tunnel made detection of the boundary layer element of the signal increasingly difficult to define as speed increased. It is considered that test in flight will be needed to prove fully the validity of the method. A preliminary design of an installation for this purpose is suggested that allows the suction flow to be maintained over the measuring region.

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17

Guo, Huiqian, Jing Wang, Jiangbo Wu, and Xiaoze Du. "Study on Spray Evaporation Treatment of Desulfurization Wastewater." Coatings 11, no. 4 (April 4, 2021): 418. http://dx.doi.org/10.3390/coatings11040418.

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Limestone-gypsum wet flue gas desulfurization (WFGD) often produces a certain amount of wastewater with complex water quality and heavy metal pollution which should be treated properly before release. Spaying the desulfurization wastewater into flue duct and using exhausted flue gas heat for evaporation is a promising and economical technology for achieving zero wastewater discharge in thermal power plant. To enable a more in-depth understanding on evaporation of FGD wastewater spray, a visual wind tunnel test rig based on the atomized droplet laser measuring system was built to reveal the impact factors on droplet thermal-fluid behavior. The dominant impact factors such as compressed air pressure and flow rate in air-blast spray nozzle, hot air temperature and velocity in the evaporation tunnel were analyzed to discuss the droplet size distribution and evaporation performance through alternating operate condition. A discrete mathematical model that combines both Eulerian and Lagrangian framework was established to validate the experiment result. It is concluded that introducing high pressure compressed air into the nozzle can contribute to the dispersion of droplets and enhance the evaporation rate. Proper flow rate in spray nozzle is required to avoid incomplete droplets evaporation. Air temperature and velocity in the evaporation tunnel apply positive impact on droplet size distribution and evaporation performance. Numerical simulation results of both dominant factors impact on evaporation behavior and total evaporation rate showed consistency with the experimental outcome.

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18

Yan, Yu Xiu, Xiu Yi, Jian Wei Tao, Min Bo Lin, and Rong Qi Li. "Research on the Influence of the Fabric Organization to Wind-Resistant Property of Sportswear." Advanced Materials Research 331 (September 2011): 646–49. http://dx.doi.org/10.4028/www.scientific.net/amr.331.646.

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Selected four organizations in those are most frequently-used in sportswear, then weaved a common sports-vest by the seamless knitting machines. Used the methods of wind tunnel test and data analysis, reached a conclusion about the influence of the organizations to wind-resistant property of sportswear: in the winding speed scope of the experiments, when the winding speed are between 3.3 m/s and 11.55 m/s, the wind-resistant property of the four organizations are almost the same; when the winding speed are between 11.55 m/s and 18.70 m/s, the wind-resistant property are different, the order from bad to good is 1×2 false rib organization, one road off staggered 1×1 false rib organization, mesh organization, plain weave, and reached the fitting curve equation. The study provides theoretical and practical reference for the research and development of sportswear.

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19

Heinemann, Till, and Stefan Becker. "Axial Fan Performance under the Influence of a Uniform Ambient Flow Field." International Journal of Rotating Machinery 2018 (2018): 1–10. http://dx.doi.org/10.1155/2018/6718750.

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In their application to air-cooled condensers, axial fans are often subject to the detrimental influence of ambient flow fields at their inlet or outlet. While effects have been investigated mostly under perpendicular cross-flow conditions on fans operating as part of an array in their target design point, this study aims at examining the integral influence of uniform ambient flow fields on a single axial fan over a wide operating range. For this purpose, a wind tunnel fan test rig has been designed and assessed. Multiple angles between uniform ambient flow field and fan axis are examined in their integral influence on the characteristic curve of two distinct industrial axial fans with varying inlet modifications. Increasingly with the fan flow rate, perpendicular inlet cross-flow was found to always have a detrimental influence on fan performance. The straight bladed fan reacted less sensitively than the forward skewed fan, and the adverse cross-flow influence could be reduced with an inlet guard grille and with short conical shroud extensions. Cross-flow at the fan outlet showed potential static fan pressure increases at low flow rates.

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20

Seitz, Arne, Anaïs Luisa Habermann, Fabian Peter, Florian Troeltsch, Alejandro Castillo Pardo, Biagio Della Corte, Martijn van Sluis, et al. "Proof of Concept Study for Fuselage Boundary Layer Ingesting Propulsion." Aerospace 8, no. 1 (January 13, 2021): 16. http://dx.doi.org/10.3390/aerospace8010016.

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Key results from the EU H2020 project CENTRELINE are presented. The research activities undertaken to demonstrate the proof of concept (technology readiness level—TRL 3) for the so-called propulsive fuselage concept (PFC) for fuselage wake-filling propulsion integration are discussed. The technology application case in the wide-body market segment is motivated. The developed performance bookkeeping scheme for fuselage boundary layer ingestion (BLI) propulsion integration is reviewed. The results of the 2D aerodynamic shape optimization for the bare PFC configuration are presented. Key findings from the high-fidelity aero-numerical simulation and aerodynamic validation testing, i.e., the overall aircraft wind tunnel and the BLI fan rig test campaigns, are discussed. The design results for the architectural concept, systems integration and electric machinery pre-design for the fuselage fan turbo-electric power train are summarized. The design and performance implications on the main power plants are analyzed. Conceptual design solutions for the mechanical and aero-structural integration of the BLI propulsive device are introduced. Key heuristics deduced for PFC conceptual aircraft design are presented. Assessments of fuel burn, NOx emissions, and noise are presented for the PFC aircraft and benchmarked against advanced conventional technology for an entry-into-service in 2035. The PFC design mission fuel benefit based on 2D optimized PFC aero-shaping is 4.7%.

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21

Abuaf, N., R. Bunker, and C. P. Lee. "Heat Transfer and Film Cooling Effectiveness in a Linear Airfoil Cascade." Journal of Turbomachinery 119, no. 2 (April 1, 1997): 302–9. http://dx.doi.org/10.1115/1.2841113.

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A warm (315°C) wind tunnel test facility equipped with a linear cascade of film cooled vane airfoils was used in the simultaneous determination of the local gas side heat transfer coefficients and the adiabatic film cooling effectiveness. The test rig can be operated in either a steady-state or a transient mode. The steady-state operation provides adiabatic film cooling effectiveness values while the transient mode generates data for the determination of the local heat transfer coefficients from the temperature–time variations and of the film effectiveness from the steady wall temperatures within the same aerothermal environment. The linear cascade consists of five airfoils. The 14 percent cascade inlet free-stream turbulence intensity is generated by a perforated plate, positioned upstream of the airfoil leading edge. For the first transient tests, five cylinders having roughly the same blockage as the initial 20 percent axial chord of the airfoils were used. The cylinder stagnation point heat transfer coefficients compare well with values calculated from correlations. Static pressure distributions measured over an instrumented airfoil agree with inviscid predictions. Heat transfer coefficients and adiabatic film cooling effectiveness results were obtained with a smooth airfoil having three separate film injection locations, two along the suction side, and the third one covering the leading edge showerhead region. Near the film injection locations, the heat transfer coefficients increase with the blowing film. At the termination of the film cooled airfoil tests, the film holes were plugged and heat transfer tests were conducted with non-film cooled airfoils. These results agree with boundary layer code predictions.

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22

Mi, Da Hai, Rui Yang, Liang Zhou, Yang Liu, and Dong Ming Guo. "Optimal Structural Frequency Design of Stiffened Shell." Applied Mechanics and Materials 157-158 (February 2012): 1636–39. http://dx.doi.org/10.4028/www.scientific.net/amm.157-158.1636.

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Frequency-aimed optimal structural design of stiffened shell is concerned. It is a reverse design problem for the first several modal frequencies to converge to a set of target value. A design method combined modified bi-directional evolutionary structural optimization (BESO) and size optimization is presented. Optimization model consists of skin and regular grid frame structure. To solve irregular branches and holes that often exist in ordinary topology optimization results, instead of elements, the existence states of ribs in the frame are used as design variables and sensitivity of the rib is discussed. Detailed design is conducted by size optimization. Example shows that frequency requirements are achieved. And the optimum structure is regular and clear, the localized modes problem is avoid. This is very suitable for designing airplane wind tunnel flutter test models.

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23

NISHIMURA, Hiroaki. "Wind Tunnel Experiment and Wind Tunnel Test." Wind Engineers, JAWE 39, no. 4 (2014): 333–34. http://dx.doi.org/10.5359/jawe.39.333.

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24

Jin, Liu, Chen Nong, Song Yuhui, Hu Jing, and Xie Ke. "New Dynamic Stability Rig for Tri-sonic Wind-tunnel." Procedia Engineering 99 (2015): 1591–96. http://dx.doi.org/10.1016/j.proeng.2014.12.711.

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25

NAKAMURA, Osamu. "Wind Tunnel Test for Wind Environment." Wind Engineers, JAWE 34, no. 1 (2009): 18–23. http://dx.doi.org/10.5359/jawe.34.18.

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26

ASAMI, Yutaka. "WIND TUNNEL TEST FOR MEMBRANE STRUCTURE." Wind Engineers, JAWE 1999, no. 78 (1999): 49–50. http://dx.doi.org/10.5359/jawe.1999.49.

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27

Zhang, Jing Hua, Ren Huang Wang, and Hong Wei Yue. "Badminton Performance Test of Wind Tunnel." Advanced Materials Research 860-863 (December 2013): 1517–20. http://dx.doi.org/10.4028/www.scientific.net/amr.860-863.1517.

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The badminton wind tunnel experiment quality classification was influenced by a lot of factors, such as the size of the wind tunnel wind speed Settings, the selection of the wind hole diameter size, Experiment parameter Settings of the test system software used standard and experimental error and so on. Therefore, a factorys wind tunnel experimental facility would be used by this paper, in order to make the quality of badminton, wind tunnel wind speed and wind hole diameter are researched further. Through the experiment testing, and combined with badminton wind tunnel experiment of theory knowledge, get the impact of these factors on the quality of badminton classification rule. Theoretical analysis is the same as the result of experiment, which this conclusion is indicated by the experiment that what we do. So as to choose the right wind tunnel device and system software of the test parameters Settings provide certain reference. Also the Badminton the judgment of the quality grade classification standard was provided the important reference frame by it.

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28

SASA, Shuichi, Masaaki YANAGIHARA, Seizou SUZUKI, and Fukuo FUKUI. "Cable-Mount Dynamic Wind-Tunnel Test." Journal of the Japan Society for Aeronautical and Space Sciences 42, no. 482 (1994): 159–63. http://dx.doi.org/10.2322/jjsass1969.42.159.

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29

ISHIBASHI, Ryukichi. "Modeling of Wind Breaks for Environmental Wind Tunnel Test." Journal of the Japanese Institute of Landscape Architecture 64, no. 5 (2000): 777–82. http://dx.doi.org/10.5632/jila.64.777.

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30

Wang, Weihua, Haili Liao, Mingshui Li, and Hanjie Huang. "Similarity Study on Snowdrift Wind Tunnel Test." Open Journal of Civil Engineering 03, no. 03 (2013): 13–17. http://dx.doi.org/10.4236/ojce.2013.33b003.

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31

Stroub, Robert H., Larry A. Young, Charles N. Keys, and Matthew H. Cawthorne. "Free-Tip Rotor Wind Tunnel Test Results." Journal of the American Helicopter Society 31, no. 3 (July 1, 1986): 19–26. http://dx.doi.org/10.4050/jahs.31.19.

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32

Stroub, Robert H., Larry A. Young, Charles N. Keys, and Matthew H. Cawthorne. "Free‐Tip Rotor Wind Tunnel Test Results." Journal of the American Helicopter Society 31, no. 3 (July 1, 1986): 19–26. http://dx.doi.org/10.4050/jahs.31.3.19.

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33

Jin, Dun, Yue Ming Yang, Jie Wu, Li Min Song, and Song Li. "Static Force Measurement Technology Wind Tunnel Test." Applied Mechanics and Materials 423-426 (September 2013): 1689–92. http://dx.doi.org/10.4028/www.scientific.net/amm.423-426.1689.

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Static force measurement aerodynamic wind tunnel test data provided by the aircraft normally used to predict the stall characteristics, predicted aircraft deviated,spin Sensitivities, numerical simulation of aircraft stall, spin dynamics and so on. Based on practical flight, the paper analyzed the harm of limit state flight-spin to the flight safe, emphasized the static force test techniques at high angles of attack, and obtained a series of aerodynamic test date, managed them to spin prediction analysis.

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34

NABAE, Akira, Kuniaki TOYODA, Tutomu UEMATU, and Harunori NAGATA. "3331 Wind tunnel test of CAMUI model." Proceedings of the JSME annual meeting 2005.5 (2005): 389–90. http://dx.doi.org/10.1299/jsmemecjo.2005.5.0_389.

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35

An, Young-Gab, and Rho-Shin Myong. "Scaling Methods for Icing Wind Tunnel Test." Journal of the Korean Society for Aeronautical & Space Sciences 40, no. 2 (February 1, 2012): 146–56. http://dx.doi.org/10.5139/jksas.2012.40.2.146.

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36

INATANI, Yoshifumi. "Wind tunnel test of winged space vehicle." Journal of the Japan Society for Aeronautical and Space Sciences 38, no. 435 (1990): 199–204. http://dx.doi.org/10.2322/jjsass1969.38.199.

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Jindeog, Chung, Cho Tahwan, Lee Jangyeon, and Sung Bongzoo. "Wind tunnel test of a canard airplane." KSME International Journal 16, no. 1 (January 2002): 125–31. http://dx.doi.org/10.1007/bf03185163.

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OKADA, Hisashi. "Wind tunnel test on behavior of rooftiles under strong wind." Wind Engineers, JAWE 1988, no. 35 (1988): 1–15. http://dx.doi.org/10.5359/jawe.1988.35_1.

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39

Duthinh, Dat, Adam L. Pintar, and Emil Simiu. "Influence of Wind Tunnel Test Duration on Wind Load Factors." Journal of Structural Engineering 144, no. 11 (November 2018): 06018005. http://dx.doi.org/10.1061/(asce)st.1943-541x.0002202.

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40

Davison, Paul M., Mark H. Lowenberg, and Mario di Bernardo. "Experimental Analysis and Modeling of Limit Cycles in a Dynamic Wind-Tunnel Rig." Journal of Aircraft 40, no. 4 (July 2003): 776–85. http://dx.doi.org/10.2514/2.3158.

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41

Lee, Geun-Ho, Young-Jun Park, Ju-Seok Nam, Joo-Young Oh, and Jeong-Gil Kim. "Design of a Mechanical Power Circulation Test Rig for a Wind Turbine Gearbox." Applied Sciences 10, no. 9 (May 7, 2020): 3240. http://dx.doi.org/10.3390/app10093240.

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We developed a mechanical power circulation test rig for a wind turbine gearbox with a power rating of 5.8 MW or less. The test rig consists of an electric motor, two auxiliary gearboxes, a torque-applying device, lubrication systems, cooling systems, and control systems. The torque generating device consists of a planetary gearbox and a hydraulic control system and is used to apply the desired torque to the test gearbox. The hydraulic control system applies the torque on the ring gear of the planetary gearbox. The gears and bearings of the two auxiliary gearboxes and planetary gearboxes met the design criteria for a safety factor of over 1.2 and a bearing life of 30,000 h. In addition, the master and slave gearboxes were connected to the test rig to verify whether the torque-applying device had applied variable torque in real-time during the test. The device was only able to induce a variable torque of up to 45.2 kN-m due to the limitation of the rated torque of the master and slave gearboxes. The test rig can test not only efficiency, vibration, and noise but also durability and overloading.

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42

Ngo, Khanh Hieu, Quoc Hung Pham, and Trung Tien Tran. "Designing a test rig for structural static-load testing of small horizontal axis wind turbine rotor blades." Science & Technology Development Journal - Engineering and Technology 3, SI3 (January 22, 2021): first. http://dx.doi.org/10.32508/stdjet.v3isi3.739.

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This paper presents a design of a test rig for structural static load testing of small horizontal wind turbine blades. It is a next step after the success of the DeVie project, a join-research project to boost the wind energy knowhow between Germany and Vietnam. According to the IEC-61400-23 standard for full scale structural testing of rotor blades, and based on existing facilities of HCMUT, especially the aerospace engineering lab. and the engineering mechanics lab., we propose a prototype of a test-rig for structural static load testing of rotor blades. A rotor blade of 4 meters in length, manufactured by China, is used in the case study of our structural static-load test-rig. This paper used the reverse engineering method to determine the blade geometry and performance, since the blade was provided and not designed from scratch. Detailed steps to determine the test load for the rig are the most important, based on the blade design and the wind condition of Vietnam, a study case was set to start the process. Since that required a lot of experience and know-how, beside the work and research from our university, other critically important information was kindly provided by the German's experts in the field. Result of the blade tip displacement are wildly used in this industry to validate the blade design. Our test rig result in 0.289 meters were compared to the reverse engineering and simulation result of 0.28 meter with QBlade/FAST in the same blade loading shown well similarity, this result validated our work process. Future revision of the test rig is promised to provide more function such as fatigue test mode, higher load capacity, faster testing time as well as more accurate result, aiding the domestic market of composite wind turbine blade manufacturing which is still in its infancy.

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43

HATANAKA, Akihide, and Hiroshi KOBAYASHI. "Active simulation of wind gust for two dimensional wind tunnel test." Doboku Gakkai Ronbunshu, no. 432 (1991): 89–97. http://dx.doi.org/10.2208/jscej.1991.432_89.

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44

Hwang, Jae-Seung, Ahsan Kareem, and Hongjin Kim. "Wind load identification using wind tunnel test data by inverse analysis." Journal of Wind Engineering and Industrial Aerodynamics 99, no. 1 (January 2011): 18–26. http://dx.doi.org/10.1016/j.jweia.2010.10.004.

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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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46

Chang, Cheng Hsin, Jen Mu Wang, and Chii Ming Cheng. "Numerical Simulation and Wind Tunnel Studies of the Wind Load on Wind Turbine Structures." Advanced Materials Research 250-253 (May 2011): 3811–14. http://dx.doi.org/10.4028/www.scientific.net/amr.250-253.3811.

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This paper investigated the structural responses of the wind turbine due to wind loads by performing the wind tunnel test and the Computational Fluid Dynamics, (CFD). The base shear force and the base moment of the wind turbine measured by the wind tunnel test were compared with the numerical simulation results. Both the numerical dynamic mesh and sliding mesh models were selected for the numerical simulations. The results showed that the dynamic mesh model was better than the sliding model by comparing to the wind tunnel test result. In the case of the k-epsilon RNG turbulence model, the prediction of the bending moment affecting by acrossswind was more than 50%, and the prediction of the force affecting by acrosswind was less than 3%. The both simulation results of the prototype and the full scale wind turbine were obtained by CFD model. The comparisons of the result showed that the error of Fxwas about 15% and Mywas about 13.5%.

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47

Woods, William C., Scott D. Holland, and Michael DiFulvio. "Hyper-X Stage Separation Wind-Tunnel Test Program." Journal of Spacecraft and Rockets 38, no. 6 (November 2001): 811–19. http://dx.doi.org/10.2514/2.3770.

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48

Cole, Stanley R. "Exploratory flutter test in a cryogenic wind tunnel." Journal of Aircraft 23, no. 12 (December 1986): 904–11. http://dx.doi.org/10.2514/3.45399.

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49

NAGAMINE, Futoshi, Hiroaki KISHIGE, Mitsuru IKEDA, Takeshi MITSUMOJI, and Masahiro SUZUKI. "J0501-3-4 Optimization of aerodynamic shape using deformable wind tunnel model for wind tunnel test." Proceedings of the JSME annual meeting 2009.7 (2009): 29–30. http://dx.doi.org/10.1299/jsmemecjo.2009.7.0_29.

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50

Cheng, XX, X. Chen, YJ Ge, H. Jiang, and L. Zhao. "A new atmospheric boundary layer wind tunnel simulation methodology for wind effects on large cooling towers considering wind environment variations." Advances in Structural Engineering 22, no. 5 (November 4, 2018): 1194–210. http://dx.doi.org/10.1177/1369433218809899.

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The traditional atmospheric boundary layer wind tunnel model test practice employs wind fields, the flow characteristics of which are in accordance with the empirical formulae of the atmospheric turbulence presented in Codes of Practice and monographs. However, the empirical formulae presented in Codes of Practice and monographs cannot truthfully reflect the high variations of the realistic atmospheric turbulence which sometimes aggravates wind effects on structures. Based on model tests conducted in a multiple-fan actively controlled wind tunnel, it is found that most wind effects on large cooling towers change monotonically with the increase in free-stream turbulence, and the model test results are more unfavorable for a flow field of low turbulence intensity than for a flow field of high turbulence intensity with respect to the measured coherences. Thus, a new atmospheric boundary layer wind tunnel simulation methodology for wind effects on circular cylindrical structures is proposed to overcome the deficiency of the traditional atmospheric boundary layer wind tunnel model tests. The new simulation methodology includes the simulation of two realistic atmospheric boundary layer flow fields with the highest and the lowest turbulence intensities in the wind tunnel and the envelopment of model test results obtained in the two flow fields (e.g. the mean and fluctuating wind pressure distributions, the power spectral density, the coherence function, and the correlation coefficient). The superiority of the new atmospheric boundary layer wind tunnel simulation methodology over the traditional model test practice is demonstrated by comparing the model test results with the full-scale measurement data.

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