Relevant bibliographies by topics / Wind tunnel testing

Academic literature on the topic 'Wind tunnel testing'

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Published: 4 June 2021
Last updated: 10 March 2023

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Journal articles on the topic "Wind tunnel testing"

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Shindo, Shojiro. "Wind Tunnel Testing." Journal of the Visualization Society of Japan 15, Supplement1 (1995): 277–80. http://dx.doi.org/10.3154/jvs.15.supplement1_277.

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Hasan, Inamul, R. Mukesh, P. Radha Krishnan, R. Srinath, Dhanya Prakash Babu, and Negash Lemma Gurmu. "Wind Tunnel Testing and Validation of Helicopter Rotor Blades Using Additive Manufacturing." Advances in Materials Science and Engineering 2022 (September 21, 2022): 1–13. http://dx.doi.org/10.1155/2022/4052208.

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This research paper aims to validate the aerodynamic performance of rotor blades using additive manufacturing techniques. Wind tunnel testing is a technique used to find the flow characteristics of the body. Computational fluid dynamics (CFD) techniques are used for aerodynamic analysis, and validation should be done using wind tunnel testing. In the aerodynamic testing of models, additive manufacturing techniques help in validating the results by making models easily for wind tunnels. Recent developments in additive manufacturing help in the aerodynamic testing of models in wind tunnels. The CFD analysis of helicopter rotor blades was analyzed in this research, and validation was done using additive manufacturing techniques. Computational analysis was carried out for static analysis for the forward speeds of Mach numbers 0.3, 0.4, and 0.5. The results obtained were satisfactory to the previous results and were validated with wind tunnel testing. Results proved that the error percentage was lower, and the computational analysis was valid. In this research, models were designed using the FDM technique for wind tunnel testing as it is cost-effective and easy to manufacture.
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Teo, Z. W., T. H. New, Shiya Li, T. Pfeiffer, B. Nagel, and V. Gollnick. "Wind tunnel testing of additive manufactured aircraft components." Rapid Prototyping Journal 24, no. 5 (July 9, 2018): 886–93. http://dx.doi.org/10.1108/rpj-06-2016-0103.

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Purpose This paper aims to report on the physical distortions associated with the use of additive manufactured components for wind tunnel testing and procedures adopted to correct for them. Design/methodology/approach Wings of a joined-wing test aircraft configuration were fabricated with additive manufacturing and tested in a subsonic closed-loop wind tunnel. Wing deflections were observed during testing and quantified using image-processing procedures. These quantified deflections were then incorporated into numerical simulations and results had agreed with wind tunnel measurement results. Findings Additive manufacturing provides cost-effective wing components for wind tunnel test components with fast turn-around time. They can be used with confidence if the wing deflections could be accounted for systematically and accurately, especially at the region of aerodynamic stall. Research limitations/implications Significant wing flutter and unsteady deflections were encountered at higher test velocities and pitch angles. This reduced the accuracy in which the wing deflections could be corrected. Additionally, wing twists could not be quantified as effectively because of camera perspectives. Originality/value This paper shows that additive manufacturing can be used to fabricate aircraft test components with satisfactory strength and quantifiable deflections for wind tunnel testing, especially when the designs are significantly complex and thin.
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Zhang, Zheng Yu, Xu Hui Huang, Jiang Yin, and Han Xuan Lai. "Videogrammetric Techniques for Wind Tunnel Testing and Applications." Advanced Materials Research 986-987 (July 2014): 1629–33. http://dx.doi.org/10.4028/www.scientific.net/amr.986-987.1629.

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Videogrammetric measurement is a research focus for the organizations of wind tunnel test because of its no special requirements on the test model, its key techniques for the vibration environment of the high speed wind tunnel are introduced by this paper, such as the solution of exterior parameters with big-angle large overlap, the algorithm of image processing for extracting marked point, the method of camera calibration and wave-front distortion field measurement. The great requirements and application prospects of videogrammetry in wind tunnel fine testing have been demonstrated by several practice experiments, including to measure test model’s angle of attack, dynamic deformations and wave-front distortion field in high speed wind tunnels whose test section size is 2 meters.
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Greenwell, D. I. "Transonic industrial wind tunnel testing in the 2020s." Aeronautical Journal 126, no. 1295 (December 2, 2021): 125–51. http://dx.doi.org/10.1017/aer.2021.107.

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AbstractWind tunnels remain an essential element in the design and development of flight vehicles. However, graduates in aerospace engineering tend to have had little exposure to the demands of industrial experimental work, particularly at high speed, a situation exacerbated by a lack of up-to-date reference material. In an attempt to fill this gap, this paper presents an overview of the current and near-term status and usage of transonic industrial wind tunnels. The review is aimed at recent entrants to the field, with the aim of helping them make the step from research projects in small university facilities to commercial projects in large industrial facilities. In addition, a picture has emerged from the review that contradicts received wisdom that the wind tunnel is in decline. Globally, the industrial transonic wind tunnel is undergoing somewhat of a renaissance. Numbers are increasing, investment levels are rising, capabilities are being enhanced, and facilities are busy.
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Stalker, R. J. "Modern developments in hypersonic wind tunnels." Aeronautical Journal 110, no. 1103 (January 2006): 21–39. http://dx.doi.org/10.1017/s0001924000004346.

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AbstractThe development of new methods of producing hypersonic wind-tunnel flows at increasing velocities during the last few decades is reviewed with attention to airbreathing propulsion, hypervelocity aerodynamics and superorbital aerodynamics. The role of chemical reactions in these flows leads to use of a binary scaling simulation parameter, which can be related to the Reynolds number, and which demands that smaller wind tunnels require higher reservoir pressure levels for simulation of flight phenomena. The use of combustion heated vitiated wind tunnels for propulsive research is discussed, as well as the use of reflected shock tunnels for the same purpose. A flight experiment validating shock-tunnel results is described, and relevant developments in shock tunnel instrumentation are outlined. The use of shock tunnels for hypervelocity testing is reviewed, noting the role of driver gas contamination in determining test time, and presenting examples of air dissociation effects on model flows. Extending the hypervelocity testing range into the superorbital regime with useful test times is seen to be possible by use of expansion tube/tunnels with a free piston driver.
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Lara, Andrés, Jonathan Toledo, and Robert Paul Salazar Romero. "Characterization, Design Testing and Numerical Modeling of a Subsonic-Low Speed Wind Tunnel." Ingeniería 27, no. 1 (January 4, 2022): e17973. http://dx.doi.org/10.14483/23448393.17973.

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Context: Wind tunnels are essential devices in the study of flow properties through objects and scaled prototypes. This work presents a numerical study to characterize an existing wind tunnel, proposing modifications with the aim to improve the quality of the flow in the test chamber. Method: Experimental measurements of the inlet velocity and pressure distribution of a wind tunnel are nperformed. These empirical values are used as parameters to define boundary conditions in simulations. The Finite Element Method (FEM) at low speeds is implemented to determine the stream function by using a standard Galerkin method. Polynomial interpolations are employed to modify the contraction section design, and numerical simulations are performed in order to compare the numerical results of the flow for the existing and the modified wind tunnels. Results: Experimental measurements of the flow at the wind tunnel entrance are presented. The velocity field and distribution of thermodynamic variables inside the tunnel are numerically determined. This computations are useful since it is experimentally difficult to make measurements inside the channel. Additionally, numerical calculations of these variables are presented under modifications in the tunnel geometry. Conclusions: A comparison between these simulations show that laminar flow at low velocities can be modeled as incompressible and irrotational fluid under a bidimensional approximation along its longitudinal section. It is observed that modifications in the geometry of the tunnel can improve the flow in the test section of the wind tunnel in the laminar regime.
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Tsushima, Natsuki, Kenichi Saitoh, Hitoshi Arizono, and Kazuyuki Nakakita. "Structural and Aeroelastic Studies of Wing Model with Metal Additive Manufacturing for Transonic Wind Tunnel Test by NACA 0008 Example." Aerospace 8, no. 8 (July 25, 2021): 200. http://dx.doi.org/10.3390/aerospace8080200.

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Additive manufacturing (AM) technology has a potential to improve manufacturing costs and may help to achieve high-performance aerospace structures. One of the application candidates would be a wind tunnel wing model. A wing tunnel model requires sophisticated designs and precise fabrications for accurate experiments, which frequently increase manufacturing costs. A flutter wind tunnel testing, especially, requires a significant cost due to strict requirements in terms of structural and aeroelastic characteristics avoiding structural failures and producing a flutter within the wind tunnel test environment. The additive manufacturing technique may help to reduce the expensive testing cost and allows investigation of aeroelastic characteristics of new designs in aerospace structures as needed. In this paper, a metal wing model made with the additive manufacturing technique for a transonic flutter test is studied. Structural/aeroelastic characteristics of an additively manufactured wing model are evaluated numerically and experimentally. The transonic wind tunnel experiment demonstrated the feasibility of the metal AM-based wings in a transonic flutter wind tunnel testing showing the capability to provide reliable experimental data, which was consistent with numerical solutions.
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Bak, Christian, Anders S. Olsen, Andreas Fischer, Oliver Lylloff, Robert Mikkelsen, Mac Gaunaa, Jimmie Beckerlee, et al. "Wind tunnel benchmark tests of airfoils." Journal of Physics: Conference Series 2265, no. 2 (May 1, 2022): 022097. http://dx.doi.org/10.1088/1742-6596/2265/2/022097.

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Abstract This paper describes a benchmark of four airfoils in the Poul la Cour Tunnel (PLCT). The wind tunnel, the corrections used and the method of making adapters for the airfoils are also described. Very good agreement was in general observed between the measurements in PLCT and in other high quality wind tunnels. Some deviations were seen, but they were mainly attributed to the differences in separation on the airfoil. Apart from the benchmarking, this paper also highlights the challenges in testing airfoils in general such as obtaining 2D flow on thick airfoils that inherently shows separated flow and how to make adapters for airfoils tested in other wind tunnels.
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Daneshmand, Saeed, Cyrus Aghanajafi, and Hossein Shahverdi. "Investigation of rapid manufacturing technology with ABS material for wind tunnel models fabrication." Journal of Polymer Engineering 32, no. 8-9 (December 1, 2012): 575–84. http://dx.doi.org/10.1515/polyeng-2012-0089.

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Abstract Nowadays, several procedures are used for manufacturing wind tunnel models. These methods include machining, casting, molding and rapid prototyping. Raw materials such as metals, ceramics, composites and plastics are used in making these models. Dimension accuracy, surface roughness and material strength are significant parameters which are effective in wind tunnel manufacturing and testing. Wind tunnel testing may need several models. Traditional methods for constructing these models are both costly and time consuming. In this research, a study has been undertaken to determine the suitability of models constructed using rapid manufacturing (RM) methods for use in wind tunnel testing. The aim of this research is to improve the surface roughness, dimensional accuracy and material strength of rapid manufacturing models for testing in wind tunnels. Consequently, the aerodynamic characteristics of three models were investigated and compared. The first model is made of steel, the second model from FDM-M30, and the third model is a hybrid model. Results show that metal models can be replaced by hybrid models in order to measure aerodynamic characteristics, reduce model fabrication time, save fabrication cost and also to verify the accuracy of aerodynamic data obtained in aerospace industry.
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Dissertations / Theses on the topic "Wind tunnel testing"

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Abrahamsen, Ida Sinnes. "Wind tunnel model testing of offshore platforms." Thesis, Norges teknisk-naturvitenskapelige universitet, Institutt for energi- og prosessteknikk, 2012. http://urn.kb.se/resolve?urn=urn:nbn:no:ntnu:diva-18627.

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The purpose of this thesis is to highlight some of the areas of interest when it comes to wind tunnel experimenting of offshore platforms regarding stability concerns such as critical angles and wind overturning moment. Some important factors include design of tower geometry, the effect of surface roughness on drag, methods of calculating blockage corrections of wall interference and the generation of an atmospheric boundary layer to resemble full-scale conditions. Data obtained from wind tunnel experiments with two different models have been compared and discussed according to the areas of interest as mentioned above. Testing of platforms was done at NTNU with a six-component balance, measuring forces of drag, side and lift and moment of pitch, roll and yaw with increments of 10° the whole 360° to account for wind coming from all directions. Two geometries were tested for the tower members, one with a circular cross-section which was smaller than scale and another with a square cross-section in correct scale. There was noticeable change in both global forces and moments. Blockage corrections caused by wall interference were researched from different sources and reviewed, and it was apparent that it is still an area with lots of uncertainty. Consensus was that and area ratio of maximum 0.10 should be abided in any case and that the simplified method of Pope is widely used. An atmospheric boundary layer was simulated at NTNU using trial-and-error and the validity of this was confirmed by comparing experimental data with theoretical data regarding the velocity profile, turbulence intensity and energy spectrum. For the experiments of surface roughness on an individual circular cylinder and the corresponding change in drag, a simple three-component balance was used. The cylinder represents the platform legs. Two types of surface roughness were tested, first a plain wooden surface and then with a layer of coarse sand applied to the whole surface. It was seen that the rougher surface provoked an earlier transition to a turbulent boundary layer, causing an earlier drop in drag which is a better fit to estimated full-scale characteristics.Finally, the element that contributes most to the inaccuracy of the experiments is shown to be the difficulty of geometric similarity. Further investigation is needed.
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Danis, Reed. "Investigating Forward Flight Multirotor Wind Tunnel Testing in a 3-by 4-foot Wind Tunnel." DigitalCommons@CalPoly, 2018. https://digitalcommons.calpoly.edu/theses/1909.

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Investigation of complex multirotor aerodynamic phenomena via wind tunnel experimentation is becoming extremely important with the rapid progress in advanced distributed propulsion VTOL concepts. Much of this experimentation is being performed in large, highly advanced tunnels. However, the proliferation of this class of vehicles extends to small aircraft used by small businesses, universities, and hobbyists without ready access to this level of test facility. Therefore, there is a need to investigate whether multirotor vehicles can be adequately tested in smaller wind tunnel facilities. A test rig for a 2.82-pound quadcopter was developed to perform powered testing in the Cal Poly Aerospace Department’s Low Speed Wind Tunnel, equipped with a 3-foot tall by 4-foot wide test section. The results were compared to data from similar tests performed in the U.S. Army 7-by 10-ft Wind Tunnel at NASA Ames. The two data sets did not show close agreement in absolute terms but demonstrated similar trends. Due to measurement uncertainties, the contribution of wind tunnel interference effects to this discrepancy in measurements was not able to be properly quantified, but is likely a major contributor. Flow visualization results demonstrated that tunnel interference effects can likely be minimized by testing at high tunnel speeds with the vehicle pitched 10-degrees or more downward. Suggestions towards avoiding the pitfalls inherent to multirotor wind tunnel testing are provided. Additionally, a modified form of the conventional lift-to-drag ratio is presented as a metric of electric multirotor aerodynamic efficiency.
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Kayisoglu, Bengi. "Investigation Of Wind Effects On Tall Buildings Through Wind Tunnel Testing." Master's thesis, METU, 2011. http://etd.lib.metu.edu.tr/upload/12613324/index.pdf.

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In recent years, especially in the crowded city-centers where land prizes have become extremely high, tall buildings with more than 30 floors have started to be designed and constructed in Turkey. On the other hand, the technical improvements have provided the opportunity of design and construction of more slender structures which are influenced by the wind actions more. If the building is flexible, wind can interact with it so the wind induced oscillations can be significantly magnified. In order to analyze the response of such buildings under wind effects, wind tunnel tests are accepted to be the most powerful tool all over the world. In this study, a series of tests were performed in Ankara Wind Tunnel on a model building in the shape of a rectangular prism. For the similitude of flow conditions, passive devices were designed. The response of the model building was measured through a high frequency base balance which was designed specifically for this case study. Through the tests, the effects of turbulence intensity, vortex shedding and wind angle of attack on the response of the building were questioned. Finally, the results were compared with the results of various technical specifications about wind.
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Sheng, Wanan. "CFD simulations in support of wind tunnel testing." Thesis, University of Glasgow, 2003. http://theses.gla.ac.uk/5393/.

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CFD and wind tunnel simulations are complementary due to their inherent limitations. Wind tunnel tests apply to any hypothesis, but are limited by the tunnel wall interference/blockage, the model details, and even the distortion of the model. CFD are not limited in any of these ways, but limited in speed and memory and the lack of determinate set of equations. Theoretically, CFD can provide an assessment of any problem in fluid dynamics (Direct Numerical Simulation), but the requirements of speed and memory are far from being met presently, or even in the foreseeable future. Of necessity, present CFD applications, however, employ a turbulence model, which limits its application due to the problems in accuracy and reliability. Given the power of CFD however, the work contained herein makes use of the advantages of CFD and also the wind tunnel, to form a powerful facility for aerodynamic test, i.e., CFD was used to complement and enhance the wind tunnel test, so producing an integrated test facility. A very important aspect in this work is that CFD was used to investigate the blockage correction for wind tunnel tests. By using CFD, the blockage correction could be made directly, in terms of representing the test model and tunnel walls in high fidelity. Meanwhile, the effect of support system on the test model was also investigated by CFD. The numerical results showed significant effect of the strut on the test model in the Argyll Wind Tunnel (Glasgow University), and an interesting result showed that different positions of support system had different effects. This research aimed to utilise CFD to support wind tunnel testing, and its ultimate purpose is to form a powerful facility for aerodynamic test by combining CFD and wind tunnel. The contributions are summarised as follows: The calibrations of wind tunnel by CFD simulations; A proposed improvement for moving belt system by CFD tools; Blockage correction of wind tunnel by CFD method; and The confirmation of CFD results by wind tunnel model test.
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Abudaram, Yaakov Jack. "Wind tunnel testing of load-alleviating membrane wings." [Gainesville, Fla.] : University of Florida, 2009. http://purl.fcla.edu/fcla/etd/UFE0041340.

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Hameury, Michel. "Development of the tolerant wind tunnel for bluff body testing." Thesis, University of British Columbia, 1987. http://hdl.handle.net/2429/27311.

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In conventional wind tunnels the solid-wall or open-jet test section imposes on the flow field around the test model new boundary conditions absent in free air. Unless a small model is used, the solid-wall test section generally increases the loadings on the model while the open-jet boundary decreases the loadings compared to the unconfined case. However, the development of a low wall-interference test section and its successful demonstration would allow the testing of relatively large models without the application of often uncertain correction formulae. The Tolerant wind tunnel, which makes use of the opposite effects of solid and open boundaries, is a transversely slatted-wall test section designed to produce at an optimal wall open-area ratio (OAR) low-correction data for a wide variety of model shapes and sizes. Initially intended for low-speed airfoil testing, its use is theoretically and experimentally investigated here in connection with bluff body testing. A simple mathematical model based on two-dimensional potential flow theory and solved with the help of a vortex surface-singularity technique is used to estimate the best wall configuration. The theory predicts an optimum OAR of about 0.45 at which pressure distributions on flat plate and circular cylinder models of blockage ratios up to 33.3 % would differ from the free-air values by not more than 1 %. On the other hand, experiments performed with flat plate, circular cylinder and circular-cylinder-with-splitter-plate models indicate the existence of an optimum configuration around OAR = 0.6. The experiments also show a maximum allowable blockage in the Tolerant wind tunnel to be equivalent to the blockage created by a 33.3 %-blockage-ratio flat plate model.
Applied Science, Faculty of
Mechanical Engineering, Department of
Graduate
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Kong, Lingzhe. "Experimental investigation of the tolerant wind tunnel for unsteady airfoil motion testing." Thesis, University of British Columbia, 1991. http://hdl.handle.net/2429/29992.

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Previously, the concept of the tolerant wind tunnel, developed in the Department of Mechanical Engineering, U. B. C., was tested only for stationary models. In the present study, the concept is investigated for unsteady airfoil motion. The new wind tunnel test section, using the opposite effects of solid and open boundaries, is a new approach to reduce wall blockage effects. Consisting of vertical airfoil slats uniformly spaced on both side walls in the test section, it is designed to produce a nearly free-air test environment for the test model, which leads to negligible or small corrections to the experimental results. The performance of this wind tunnel for unsteady model testing is examined experimentally with a two-dimensional NACA 0015 airfoil in a simple plunging sinusoidal motion. The airfoil is mounted vertically in the center plane of the test section between solid ceiling and floor. An oscillating table is designed to give the airfoil an accurate plunging sinusoidal motion. A full range of open area ratio is tested by varying the number of slats mounted inside the side walls. Pressure distribution along the airfoil surface and displacement of the airfoil are measured as functions of time by a data acquisition system designed for this research. Lift and moment are obtained by integration of the pressure distribution at every time increment. Using a numerical model based on the singularity distribution method, the free air case results for a NACA 0015 airfoil in the same unsteady motion are obtained. Comparison with the linear theory results by Sears¹ are discussed. Comparing with the numerical and the linear theory results, the experimental investigation shows that the new test section produces low-correction data.
Applied Science, Faculty of
Mechanical Engineering, Department of
Graduate
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Hetherington, Ben. "Interference of supports used for ground vehicle wind tunnel testing." Thesis, Durham University, 2006. http://etheses.dur.ac.uk/2671/.

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In order to provide a correct aerodynamic simulation of a vehicle travelling along the ground, models are tested using rotating wheels in a wind tunnel with a moving ground. In the most common of moving ground configurations the model is supported by an overhead strut, usually designed as an aerofoil profile to minimise interference, with the wheels supported by lateral stings hinged to mounts outside the span of the moving ground plane. ๒ using this type of configuration it is assumed that the presence of the intruding supports do not markedly affect the aerodynamic behaviour of the model, but this assumption is not always valid. In order to quantify interference effects from model supports, a range of models were tested over a stationary ground plane mounted to an under floor balance. Each model was tested with and without mock struts and stings, which do not actually support the model. Comparisons were made between configurations with and without the mock supports in order to quantify their aerodynamic effects and investigate any changes in flow structure. Force and moment measurements show significant effects on both drag (up to 25 counts / 7% of total drag) and lift (up to 170 counts) due to a vertical strut for all vehicle types. Motor Sport models, whose performance relies greatly on the underside flow, are largely affected (26 counts / 3% on drag and up to 250 counts on lift) by the presence of lateral stings. Passenger vehicle models with larger ride heights were not as sensitive to the use of stings. Further investigation into the flow mechanisms that create these effects were carried out in the form of pressure and velocity measurements in the model and support wakes, surface oil flow visualisations, and surface static pressure readings. Results showed that the strut wake impinged on the rear wings of the motor sport vehicle models and the backlight of the passenger vehicle models as expected, but its influence was more wide ranging than this, extending to the model under floor. To explore changes in flow structure local to the strut-model junction, the junction is simplified as an aerofoil intersecting a flat plate and modelled in Fluent. Comparisons were made between configurations with and without the presence of six different aerofoil profiles for four different boundary layer thicknesses. Results found a noticeable interference on the plate from the union of the aerofoil, but showed that when the magnitude of the interference effect was recalculated using model frontal area the portion of the interference local to the junction affecting the model was small and in some cases insignificant. It was determined that deficiencies in the wake of the supports and their complex interference flow fields were creating a much greater amount of the overall effect by interfering with vehicle features downstream. Due to the complexity of interactions between struts, stings, and the model, the effect of combining them for a common moving ground configuration was highly vehicle dependent, precluding the possibility of developing a reliable correction for interference effects. The results do, however, lead to suggestions for support-model coupling methods that minimise the magnitude of the effect and offer guidelines for the expected magnitudes of effects for the different vehicle types and struts tested.
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Lewis, Mark Charles. "Aerofoil testing in a self-streamlining flexible walled wind tunnel." Thesis, University of Southampton, 1987. https://eprints.soton.ac.uk/52285/.

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Ratliff, Card. "Revitalization and initial testing of a blowdown supersonic wind tunnel." Master's thesis, Mississippi State : Mississippi State University, 2008. http://library.msstate.edu/etd/show.asp?etd=etd-07312008-093307.

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Books on the topic "Wind tunnel testing"

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Quality assessment for wind tunnel testing. Neuilly-sur-Seine, France: AGARD, 1994.

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North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Quality assessment for wind tunnel testing. Neuilly-sur-Seine: AGARD, 1994.

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American Institute of Aeronautics and Astronautics., ed. Recommended practice: Wind tunnel testing. Reston, VA: American Institute of Aeronautics and Astronautics, 2003.

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Barlow, Jewel B. Low-speed wind tunnel testing. 3rd ed. New York: Wiley, 1999.

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United States. National Aeronautics and Space Administration., ed. Wind tunnel testing and research. [Washington, DC: National Aeronautics and Space Administration, 1994.

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Advisory Group for Aerospace Research and Development. Fluid Dynamics Panel., ed. Quality assessment for wind tunnel testing. Neuilly sur Seine: Agard, 1994.

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United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., ed. The status of two-dimensional testing at high transonic speeds in the University of Southampton transonic self-streamlining wind tunnel. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1985.

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United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., ed. The status of two-dimensional testing at high transonic speeds in the University of Southampton transonic self-streamlining wind tunnel. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1985.

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American Society of Civil Engineers. Wind tunnel testing for buildings and other structures. Reston, VA: American Society of Civil Engineers, 2012.

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J, Jeracki Robert, and United States. National Aeronautics and Space Administration., eds. Porous wind tunnel corrections for counterrotation propeller testing. [Washington, DC]: National Aeronautics and Space Administration, 1988.

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Book chapters on the topic "Wind tunnel testing"

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Matthews, R. K. "Hypersonic Wind Tunnel Testing." In Advances in Hypersonics, 72–108. Boston, MA: Birkhäuser Boston, 1992. http://dx.doi.org/10.1007/978-1-4612-0379-7_3.

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Mora, R. Bardera. "Unmanned Aircraft Wind Tunnel Testing." In Advanced UAV Aerodynamics, Flight Stability and Control, 181–99. Chichester, UK: John Wiley & Sons, Ltd, 2017. http://dx.doi.org/10.1002/9781118928691.ch5.

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Brownlie, Len W. "Wind Tunnels: Design Considerations in Wind Tunnel Testing of Cyclists." In Biomechanical Principles and Applications in Sports, 57–86. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-13467-9_4.

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Bottasso, Carlo L., and Filippo Campagnolo. "Wind Tunnel Testing of Wind Turbines and Farms." In Handbook of Wind Energy Aerodynamics, 1077–126. Cham: Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-030-31307-4_54.

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Bottasso, Carlo L., and Filippo Campagnolo. "Wind Tunnel Testing of Wind Turbines and Farms." In Handbook of Wind Energy Aerodynamics, 1–57. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-05455-7_54-1.

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Gibertini, G., G. Campanardi, L. Guercilena, and C. Macchi. "Cycling Aerodynamics: Wind Tunnel Testing versus Track Testing." In IFMBE Proceedings, 10–13. Berlin, Heidelberg: Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/978-3-642-14515-5_3.

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Yinzhi, He, Zhigang Yang, and Yigang Wang. "Wind Noise Testing at Shanghai Automotive Wind Tunnel Center." In Lecture Notes in Electrical Engineering, 571–78. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-33832-8_44.

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He, Yinzhi, Z. Yang, and Y. Wang. "Wind noise testing at the full scale aeroacoustic wind tunnel of Shanghai Automotive Wind Tunnel Center." In Proceedings, 1369–78. Wiesbaden: Springer Fachmedien Wiesbaden, 2014. http://dx.doi.org/10.1007/978-3-658-05130-3_97.

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Sears, W. R. "A Wind-Tunnel Method for V/STOL Testing." In Recent Advances in Aerodynamics, 525–45. New York, NY: Springer New York, 1986. http://dx.doi.org/10.1007/978-1-4612-4972-6_14.

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Huang, Min, Huiguo Lu, Baoqiang Wang, and Yong Lu. "Research on Testing the Ultrasonic Wind Sensors in Circuit Wind Tunnel." In Proceedings of the 2015 International Conference on Communications, Signal Processing, and Systems, 859–68. Berlin, Heidelberg: Springer Berlin Heidelberg, 2016. http://dx.doi.org/10.1007/978-3-662-49831-6_89.

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Conference papers on the topic "Wind tunnel testing"

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BARNWELL, R., C. EDWARDS, R. KILGORE, and D. DRESS. "Optimum transonic wind tunnel." In 14th Aerodynamic Testing Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-755.

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BUSHNELL, D., and R. TRIPI. "Supersonic wind tunnel optimization." In 14th Aerodynamic Testing Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-773.

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Schoenfeld, William, and Francis Priolo. "Automated wind tunnel testing." In 36th AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-709.

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TRIMMER, L., A. CARY, JR., and R. VOISINET. "The optimum hypersonic wind tunnel." In 14th Aerodynamic Testing Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-739.

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Burdett, Timothy A., and Kenneth W. Van Treuren. "Scaling Small-Scale Wind Turbines for Wind Tunnel Testing." In ASME Turbo Expo 2012: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/gt2012-68359.

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Abstract:
Wind tunnel testing of wind turbines can provide valuable insights into wind turbine performance and provides a simple process to test and improve existing designs. However, the scale of most wind turbines is significantly larger than most existing wind tunnels, thus, the scaling required for testing in a typical wind tunnel presents multiple challenges. When wind turbines are scaled, often only geometric similarity and tip speed ratio matching are employed. Scaling in this manner can result in impractical rotational velocities. For wind tunnel tests that involve Reynolds numbers less than approximately 500,000, Reynolds number matching is necessary. When including Reynolds number matching in the scaling process, keeping rotational velocities realistic becomes even more challenging and preventing impractical freestream velocities becomes difficult. Turbine models of 0.5, 0.4, and 0.3 m diameter, resulting in wind tunnel blockages up to 52.8%, were tested in order to demonstrate scaling using Reynolds number matching and to validate blockage corrections found in the literature. Reynolds numbers over the blades ranged from 20,000 to 150,000 and the tip speed ratio ranged from 3 to 4 at the maximum power point for each wind speed tested.
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Marks, Christopher R., Lauren Zientarski, Adam J. Culler, Benjamin Hagen, Brian M. Smyers, and James J. Joo. "Variable Camber Compliant Wing - Wind Tunnel Testing." In 23rd AIAA/AHS Adaptive Structures Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-1051.

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SCAGGS, NORMAN, RICHARD NEUMANN, and ANTHONY LAGANELLI. "Hypersonic wind tunnel nozzle study." In 17th Aerospace Ground Testing Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-4012.

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MORT, K., P. SODERMAN, and L. MEYN. "OPTIMUM FULL-SCALE SUBSONIC WIND TUNNEL." In 14th Aerodynamic Testing Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-732.

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Agrawal, Devansh, Faisal Asad, Blake M. Berk, Trevor Long, Jackson Lubin, Christopher Courtin, Mark Drela, R. John Hansman, and Jacqueline L. Thomas. "Wind Tunnel Testing of a Blown Flap Wing." In AIAA Aviation 2019 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2019. http://dx.doi.org/10.2514/6.2019-3170.

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Darida, Mauro, and Ladislav Smrcek. "RPV wing glove configuration - Wind tunnel testing results." In 16th AIAA Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-2532.

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Reports on the topic "Wind tunnel testing"

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Alexander, Michael G. Subsonic Wind Tunnel Testing Handbook. Fort Belvoir, VA: Defense Technical Information Center, May 1991. http://dx.doi.org/10.21236/ada240263.

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Butterfield, C. P., W. P. Musial, and D. A. Simms. Combined Experiment Phase 1. [Horizontal axis wind turbines: wind tunnel testing versus field testing]. Office of Scientific and Technical Information (OSTI), October 1992. http://dx.doi.org/10.2172/6882369.

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Ruyten, Wim. Toward an Integrated Optical Data System for Wind Tunnel Testing. Fort Belvoir, VA: Defense Technical Information Center, January 1999. http://dx.doi.org/10.21236/ada370964.

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Simms, D., S. Schreck, M. Hand, L. Fingersh, J. Cotrell, K. Pierce, and M. Robinson. Plans for Testing the NREL Unsteady Aerodynamics Experiment 10m Diameter HAWT in the NASA Ames Wind Tunnel: Minutes, Conclusions, and Revised Text Matrix from the 1st Science Panel Meeting. Office of Scientific and Technical Information (OSTI), August 2000. http://dx.doi.org/10.2172/763620.

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Wagner, Matthew J., and Gary A. Dale. The Design and Testing of Pneumatic Systems for Measuring Low Pressures in Hypersonic Wind Tunnels. Fort Belvoir, VA: Defense Technical Information Center, November 1985. http://dx.doi.org/10.21236/ada379715.

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Hill, David W., Carman Jr., and Jr Jack B. User Requirements and Information for Captive Trajectory and Grid Testing in the PWT Aerodynamic Wind Tunnels (4T/16T/16S). Fort Belvoir, VA: Defense Technical Information Center, July 1985. http://dx.doi.org/10.21236/ada334792.

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