Relevant bibliographies by topics / Wind tunnel tests

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Wind tunnel tests'

Author: Grafiati
Published: 4 June 2021
Last updated: 31 July 2024

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Journal articles on the topic "Wind tunnel tests"

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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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Hasan, Mohammed Munif, and Shabudin Mat. "Data Reduction Analysis on UTM-LST External Balance." International Journal for Research in Applied Science and Engineering Technology 10, no. 10 (October 31, 2022): 952–59. http://dx.doi.org/10.22214/ijraset.2022.47097.

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Abstract: The effective use of wind-tunnel testing in determining aerodynamic properties of a body is very much dependent upon the reliability and speed with which wind-tunnel data can be reduced. The operating efficiency of the wind tunnels is substantially improved by the capability of providing lower aerodynamic coefficients in real time, or online, which decreases the expensive wind-tunnel time necessary for each test. This paper describes a system for presenting reduced wind-tunnel data in real time for UTM-LST. The requirements for data-handling equipment and data reduction procedures for wind tunnels are quite diverse, and depend upon the wind tunnel design and the type of tests for which they are used. The supersonic wind tunnels mentioned in this description have a variety of force-balance systems and are used for force tests, pressure tests, and other research projects. Consequently, the problems associated with in order to solve this diversity we build a computerized program where we can find the transformation of axis and aerodynamic characteristics at ease. This program can find the values of different aerodynamic coefficients with certain angle of attacks.
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Zhou, Qi, Yuxiang Zhu, Yu Wang, and Jiceng Han. "CFD-Based Wind Field Correction Method for Terrain Wind Tunnel Tests." Journal of Physics: Conference Series 2083, no. 3 (November 1, 2021): 032083. http://dx.doi.org/10.1088/1742-6596/2083/3/032083.

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Abstract At present, the wind tunnel test results will have certain deviation and distortion when the wind tunnel test is conducted on certain mountainous terrain with complex local terrain and large variation of wind field characteristics due to the accuracy range of the measuring instruments used in wind tunnel test. In order to correct and obtain correct wind tunnel test results, the wind tunnel tests and numerical simulations were conducted on a super-large bridge in the mountainous area of Southwest China, and the wind parameters of the wind field at the bridge site were obtained. The CFD results were compared with the wind tunnel test results to confirm the credibility of the CFD results; a method was proposed to correct the deviated wind tunnel test data based on the CFD simulation results; the deviated wind tunnel test data were corrected and predicted with the above method, and a more satisfactory correction result was obtained.
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MAEDA, Tatsuo, and Yoshihiko KONDO. "RTRI's Large-scale Low-noise Wind Tunnel and Wind Tunnel Tests." Quarterly Report of RTRI 42, no. 2 (2001): 65–70. http://dx.doi.org/10.2219/rtriqr.42.65.

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

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The aerodynamic drags of different reference car models were investigated to calibrate the performance of the Automotive Wind Tunnel in Jilin University. The two kinds of reference models--MIRA and SAE reference car models were involved in this paper, considering the actual situation of the Automotive Wind Tunnel in Jilin University. The results of the research show that the Automotive Wind Tunnel in Jilin University can meet the demand for automotive wind tunnel tests and it can get the same performances as other wind tunnels have and reliable test data can be obtained in it.
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Vuković, Đorđe, and Dijana Damljanović. "A technique for reducing supersonic transient loads on internal wind tunnel balances." Tehnika 79, no. 2 (2024): 177–84. http://dx.doi.org/10.5937/tehnika2402177v.

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Design of slender supersonic missiles requires a comprehensive experimental support in the form of wind tunnel data for a wide range of flight parameters (angle of attack and Mach number). However, in supersonic wind tunnel testing, the problem exists of transient loads at the times of the starting and stopping of the supersonic flow. In the environments of pronounced transient loads, characteristic of blowdowin wind tunnels like the T-38 of the Military technical Institute in Belgrade, it is necessary to provide control of the use of internal wind tunnel balances in the permitted design load ranges. The presented technique is related to the definition and implementation of a methodology for reducing the transient loads on wind tunnel balances in supersonic wind tunnel tests. By limiting the clearance between the model and its tail support (sting) to a magnitude which permits normal tests, but results in model-support contact during the excessive loads, part of the loads is transferred to the support sting, relieving the balance. The technique improves control over the wind tunnel test process, improves measurement accuracy and prevents damage to sensitive instrumentation (wind tunnel balances).
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Samali, B., K. C. S. Kwok, G. S. Wood, and J. N. Yang. "Wind Tunnel Tests for Wind-Excited Benchmark Building." Journal of Engineering Mechanics 130, no. 4 (April 2004): 447–50. http://dx.doi.org/10.1061/(asce)0733-9399(2004)130:4(447).

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

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Parallel sidewalls are the standard bounding walls in wind tunnels when making a wind tunnel model for free-flight condition. The consequence of confinement in wind tunnel tests, known as wall-interference, is one of the main sources of uncertainty in experimental aerodynamics, limiting the realizability of free-flight conditions. Although this has been an issue when designing transonic wind tunnels and/or in cases with large blockage ratios, even subsonic wind tunnels at low-blockage-ratios might require wall corrections if a good representation of free-flight conditions is intended. In order to avoid the cumbersome streamlining methods especially for subsonic wind tunnels, a sensitivity analysis is conducted in order to investigate the effect of inclined sidewalls as a reduced-order wall insert in the airfoil plane. This problem is investigated via Reynolds-averaged Navier–Stokes (RANS) simulations, and a NACA4412 wing at the angles of attack between 0 and 11 degrees at a moderate Reynolds number (400 k) is considered. The simulations are validated with well-resolved large-eddy simulation (LES) results and experimental wind tunnel data. Firstly, the wall-interference contribution in aerodynamic forces, as well as the local pressure coefficients, are assessed. Furthermore, the isolated effect of confinement is analyzed independent of the boundary-layer growth. Secondly, wall-alignment is modified as a calibration parameter in order to reduce wall-interference based on the aforementioned assessment. In the outlined method, we propose the use of linear inserts to account for the effect of wind tunnel walls, which are experimentally simple to realize. The use of these inserts in subsonic wind tunnels with moderate blockage ratio leads to very good agreement between free-flight and wind tunnel data, while this approach benefits from simple manufacturing and experimental realization.
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Krzysiak, A. "Bottom drag measurements in experimental wind tunnel tests." Journal of Physics: Conference Series 2367, no. 1 (November 1, 2022): 012001. http://dx.doi.org/10.1088/1742-6596/2367/1/012001.

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Abstract The paper presents the results of wind tunnel tests aimed at determining the model bottom drag in the case of rocket model tests. The balance measurement technique of the rocket model fixed in the wind tunnel test section by the rear sting was discussed. The model was equipped with the two parallel boosters. Based on the wind tunnel test of the rocket twin model the values of the bottom pressure was determined for tested Mach numbers. An algorithm of wind tunnel corrections was shown, which allowed the total drag determination in a case of the rocket active or passive rocket flight. The test results showed the necessity of the bottom drag measurements in wind tunnel tests.
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WANG, Wenjun, Hiroshi KUROYANAGI, and Kazunori YOSHIDA. "1A16 6 Force Component Balance for Wind Tunnel Model Tests." Proceedings of the Symposium on the Motion and Vibration Control 2010 (2010): _1A16–1_—_1A16–7_. http://dx.doi.org/10.1299/jsmemovic.2010._1a16-1_.

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Dissertations / Theses on the topic "Wind tunnel tests"

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BACCHINI, ALESSANDRO. "Electric VTOL preliminary design and wind tunnel tests." Doctoral thesis, Politecnico di Torino, 2020. http://hdl.handle.net/11583/2847140.

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Frison, Giovanni. "Aeroelastic and aerodynamic wind tunnel tests for tall buildings." Doctoral thesis, Università degli studi di Padova, 2019. http://hdl.handle.net/11577/3423186.

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Starting from the consolidated concept of aerodynamic model, a benchmark is proposed to further asses an extend its capability of correctly identify the dynamic response of a tall building, devoting particular attention to the contribution of higher-order modes and the possible presence of aerodynamic damping. Being the extrema ratio in terms of accuracy and reliability, a full-aeroelastic model of a tall building is presented as the subject of comparison. The complexity involved in the dynamic wind-tunnel scaling led to the definition of a novel semi-automatized procedure. Based on the author’s experience, developed during the project, each step comes with practical advice, often challenging to find in the scientific literature, and food for thought on the worthiness of design-oriented aeroelastic modeling approach. The design, construction, identification, and validation of a 1:360-scale, a four-level lumped-mass aeroelastic model of the well-known Caarc standard tall building, is presented. Differently to the numerous previous research involving the Caarc building, here it is disclosed in a new guise, featuring torsional and second-order modes, enhancing the challenge for the aerodynamic model test. An extensive experimental campaign is performed at the CRIACIV boundary layer wind tunnel. Tests are performed in turbulent flow for a wide range of velocities and varying the structural damping to be able to address the results for different design criteria. Although the aerodynamic model is generally found to provide useful insight in the building response, the presence of aerodynamic damping and second-order modes are found to be relevant both in terms of base moments and acceleration. From a design perspective, even for "not exceptional" tall buildings, such as the Caarc, the aerodynamic model seems a valid option for early design stages, while the adoption of an aeroelastic model might be a valuable solution in the refinement of loads or serviceability criteria.
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Warsido, Workamaw Paulos. "Reducing Uncertainties in Estimation of Wind Effects on Tall Buildings Using Aerodynamic Wind Tunnel Tests." FIU Digital Commons, 2013. http://digitalcommons.fiu.edu/etd/939.

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Tall buildings are wind-sensitive structures and could experience high wind-induced effects. Aerodynamic boundary layer wind tunnel testing has been the most commonly used method for estimating wind effects on tall buildings. Design wind effects on tall buildings are estimated through analytical processing of the data obtained from aerodynamic wind tunnel tests. Even though it is widely agreed that the data obtained from wind tunnel testing is fairly reliable the post-test analytical procedures are still argued to have remarkable uncertainties. This research work attempted to assess the uncertainties occurring at different stages of the post-test analytical procedures in detail and suggest improved techniques for reducing the uncertainties. Results of the study showed that traditionally used simplifying approximations, particularly in the frequency domain approach, could cause significant uncertainties in estimating aerodynamic wind-induced responses. Based on identified shortcomings, a more accurate dual aerodynamic data analysis framework which works in the frequency and time domains was developed. The comprehensive analysis framework allows estimating modal, resultant and peak values of various wind-induced responses of a tall building more accurately. Estimating design wind effects on tall buildings also requires synthesizing the wind tunnel data with local climatological data of the study site. A novel copula based approach was developed for accurately synthesizing aerodynamic and climatological data up on investigating the causes of significant uncertainties in currently used synthesizing techniques. Improvement of the new approach over the existing techniques was also illustrated with a case study on a 50 story building. At last, a practical dynamic optimization approach was suggested for tuning structural properties of tall buildings towards attaining optimum performance against wind loads with less number of design iterations.
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Meszaros, Steven P. "Wind tunnel tests to determine effective leakage area in model grain bins." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 1998. http://www.collectionscanada.ca/obj/s4/f2/dsk2/tape17/PQDD_0001/MQ32189.pdf.

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Lehmkuehler, Kai. "A Direct Comparison of Small Aircraft Dynamics between Wind Tunnel and Flight Tests." Thesis, The University of Sydney, 2016. http://hdl.handle.net/2123/16511.

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The miniaturization of embedded electronics and sensors driven by the rapid development of mobile devices has enabled powerful avionics systems for very small aircraft. This enables a potential step forward in accurate flight data gathering for vehicles weighing 5 kg or less. Being able to flight test a small platform like this also allows the comparison of the results with reference data from ground testing in a standard sized wind tunnel of an identical airframe. With this process, the following questions can be answered: Firstly, would such a system then be able to collect accurate flight data for system identification (ID)? Is it possible at all to fly a small, remotely piloted aircraft precisely enough to record the required data, given its sensitivity to atmospheric turbulence, airframe noise, limitations of the remote piloting and so on? And secondly, if accurate data has been obtained, how well do the two experiments match? The small scale might potentially result in previously unknown or at least insignificant physical phenomena, which need to be taken into account when flight testing such a small platform. The changes in the inertial properties of the platform due to the added mass effect is one of these phenomena, which can typically be ignored for full scale aircraft. However, this has proven to be critically important for the successful analysis and comparison of the flight- and wind tunnel data obtained throughout this project. The avionics suite designed for this research was developed in house, since the weight restrictions of the small platform excluded any commercially available flight data recording packages. The suite features an lightweight airdata probe, control surface feedback sensors, a custom designed GPS receiver and many other advanced components previously not possible at this scale. A commercial reference INS was used to benchmark the system. The UAVmainframe also provides basic flight control functionality to aid the pilot in obtaining the required trim conditions and turbulence mitigation. Extensive data compatibility analysis and calibrations were performed on the recorded data using an Extended Kalman Filter (EKF) and various other methods to ensure the best possible data quality. The inertial properties of the test aircraft were determined by swing tests. The significance of the added mass contributions was discovered during these tests, which added up to 25% onto the `true' airframe inertial properties. In an effort to estimate these added mass terms, it has been found that the methods presented in literature to determine the corrections for full scale aircraft do not give the correct results for the small scale aircraft under consideration. Swing tests of a flat plate model of the test aircraft also did not capture the magnitude of the phenomenon correctly, which led to swing tests with a geometrically similar 3-d object of known inertial properties to successfully estimate the added mass corrections. Static derivatives were obtained from conventional wind tunnel testing, in conjunction with a high fidelity three dimensional inviscid solution using the PanAir code. A dynamic test rig was used in the wind tunnel to determine the dynamic derivatives. It allowed the instrumented airframe to rotate freely on a three axis gimbal, essentially 'fly' in the tunnel. The aerodynamic derivatives from these 3 DoF tests were estimated by performing system ID on the recorded data, where the model structures were modified for the reduced set of motion variables. Extensive flight testing was performed at the university's flight test centre. These tests showed the difficulty of testing such a small and light airframe due to wind and airframe noise, as well as the limitations due to lack of feedback received by the remote pilot. The pilot was aided by the flight control system to achieve a good trim condition, and pre-recorded input sequences, similar to the dynamic wind tunnel tests, were used to excite the longitudinal and lateral dynamics of the aircraft. One particular finding during the test campaign was that there is no such thing as totally calm conditions for this scale of airframe. Other findings include a high correlation between the pitch damping term and the pitching moment due to elevator, making it impossible to determine both at the same time, and that in flight the inertial properties of the test aircraft change to the values that include the added mass components, as compared to the dynamic wind tunnel tests, where the `true' inertias are used. By including these findings in the data processing, close agreement between flight and ground test data has been achieved.
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Kusmarwanto, I. "Ground effect on a rotor wake." Thesis, Cranfield University, 1985. http://dspace.lib.cranfield.ac.uk/handle/1826/4545.

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The effect of the ground on a rotor wake in forward flight has been investigated experimentally in the working section of an 8ft x Oft straight-through wind tunnel. A three bladed fully articulated rotor with a solidity ratio of 0.07 and diameter of 1.06m, powered by a hydraulic motor, has been tested at a height of 0.47 rotor diameter above a solid ground board which has an elliptical leading edge. Tests have been run at various low advance ratios (<0.1) with two collective pitch settings. A three-element hot wire anemometer probe has been used to measure the average value of the three components of velocity simultaneously in the forward half (advancing side) of the rotor wake and in the main stream surrounding it. The rotor wake and the ground vortices have been visualized by smoke. Surface flow patterns on the ground board have located the interaction region between the rotor wake and the oncoming flow on the ground board. Theoretical estimates of the flowfield based on Heyson's vortex cylinder model (Ref. 2) are compared with the experimental results. Both experimental results and theoretical estimates show that the ground-induced interference is an upwash and a decrease in forward velocity. The upwash interference' opposes the vertical flow through the rotor, and have large effects on the rotor performance in producing thrust. The streamwise interference decelerates the mainstream and becomes more noticeable as the wake boundary is approached.
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Breton, Simon-Philippe. "Study of the stall delay phenomenon and of wind turbine blade dynamics using numerical approaches and NREL’s wind tunnel tests." Doctoral thesis, Norwegian University of Science and Technology, Department of Civil and Transport Engineering, 2008. http://urn.kb.se/resolve?urn=urn:nbn:no:ntnu:diva-2275.

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Mesrobian, Chris Eden. "Concept Study of a High-Speed, Vertical Take-Off and Landing Aircraft." Thesis, Virginia Tech, 2009. http://hdl.handle.net/10919/35574.

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The purpose of the study was to evaluate the merits of the DiscRotor concept that combine the features of a retractable rotor system for vertical take-off and landing (VTOL) with an integral, circular wing for high-speed flight. Tests were conducted to generate basic aerodynamic characteristics of the DiscRotor in hover and in fixed-wing flight.

To assess the DiscRotor during hover, small scale tests were conducted on a 3ft diameter rotor without the presence of a fuselage. A â hover rigâ was constructed capable of rotating the model rotor at speeds up to 3,500 RPM to reach tip speeds of 500fps. Thrust and torque generated by the rotating model were measured via a two-component load cell, and time averaged values were obtained for various speeds and pitch angles. It has been shown that the DiscRotor will perform well in hover. Ground Effects in hover were examined by simulating the ground with a movable, solid wall. The thrust was found to increase by 50% compared to the ground-independent case. Pressure distributions were measured on the ground and disc surfaces. Velocity measurements examined the flow field downstream of the rotor by traversing a seven hole velocity probe. A wake behind the rotor was shown to contract due to a low pressure region that develops downstream of the disc.

Wind tunnel experimentation was also performed to examine the fixed wing flight of the DiscRotor. These experiments were performed in the VA Tech 6â X6â Stability Tunnel. A model of the fuselage and a circular wing was fabricated based upon an initial sizing study completed by our partners at Boeing. Forces were directly measured via a six degree of freedom load cell, or balance, for free stream velocities up to 200fps. Reynolds numbers of 2 and 0.5 million have been investigated for multiple angles of attack. Low lift-to-drag ratios were found placing high power requirements for the DiscRotor during fixed-wing flight. By traversing a seven-hole velocity probe, velocities in a 2-D grid perpendicular to the flow were measured on the model. The strengths of shed vortices from the model were calculated. A method to improve fixed-wing performance was considered where two blades were extended from the disc. An increase of 0.17 in the CL was measured due to the interaction between the disc and blades.

This research utilized a wide range of experiments, with the aim of generating basic aerodynamic characteristics of the DiscRotor. A substantial amount of quantitative data was collected that could not be included in this document. Results aided in the initial designs of this aircraft for the purpose of evaluating the merit of the DiscRotor concept.
Master of Science

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de, Laval Jonathan. "Simulation of thermal tests in the climatic wind tunnel CD7 at Scania Master thesis project in fluid mechanics." Thesis, KTH, Mekanik, 2016. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-195726.

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The Swedish truck and bus manufacturer Scania has a number of test facilities to support the R&D department and for verification of vehicle properties. The latest addition is the climatic wind tunnel Chassis Dynamometer 7 (CD7) which can fit trucks and buses for full scale testing and maintain temperatures in the range from -35 to 50 degree Celsius in the flow circuit, furthermore it can generate both rain and snow conditions. This means that vehicles can be tested in a controlled and repeatable manner at many critical driving conditions. However, since CD7 is a new facility there is a need to tune and interpret the results generated in the tunnel and translate them to true, on road conditions. In this project the airflow and temperature distribution in the climatic wind tunnel were studied by means of the CFD solver PowerFLOW based on the Lattice Boltzmann method. As a first step the wind tunnel was simulated empty to check the case set up and to understand the basic flow features in the empty tunnel. In the second step a Scania truck was added to the wind tunnel set up, a truck that also exists as a physical test vehicle at Scania R&D. Thirdly, the same vehicle model was simulated in road like conditions to give a reference for comparison. Lastly, a measurement campaign was performed in the climatic wind tunnel in order to get data for comparison and validation of the simulation results. Simulation results show that CD7 displays an overestimate of wind tunnel airspeed. To match heat exchanger mass flow and recirculation temperatures at 30 km/h it is shown that CD7 should indicate closer to 35 km/h. At this low speed range 5 km/h has a strong effect on recirculation of hot air into the cooling package which translates to 1 C increase of air temperature into the charge-air cooler. It also corresponds to an increase of 2 C of the cooling capacity of the vehicle at 30 km/h. Also the temperature in the front air intake system increases by 3 C which is also a significant change that could affect the tuning of the engine. One degree Celsius is within the measurement accuracy of a thermal test at Scania. The simulations at 85 km/h give a corresponding correction of the tunnel velocity around 10 km/h, which means that it is consistently about 10 % off. The experimental results show conformity with the simulations and also support the claim that CD7 indicates an overestimate of the actual airspeed.
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Schouten, Shane Michael. "Complete CFD analysis of a Velocity XL-5 RG with flight-test verification." Texas A&M University, 2008. http://hdl.handle.net/1969.1/85894.

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The Texas A&M Flight Research Laboratory (FRL) recently received delivery of its newest aircraft, the Velocity XL-5 RG. The Velocity can fly faster than the other aircraft owned by the FRL and does not have a propeller in the front of the aircraft to disrupt the air flow. These are definite advantages that make the Velocity an attractive addition to the FRL inventory to be used in boundary-layer stability and transition control. Possible mounting locations built into the aircraft for future projects include hard points in the wings and roof of the fuselage. One of the drawbacks of the aircraft is that it has a canard ahead of the main wing that could disrupt the incoming flow for a wing glove or research requiring test pieces mounted to the hard point in the wing. Therefore, it is necessary to understand the influence the canard and the impact of its wake on the wing of the aircraft before any in-depth aerodynamic research could be completed on the aircraft. A combination of in-flight measurements of the canard wake and Computational Fluid Dynamics (CFD) were used to provide a clear picture of the flowfield around the aircraft. The first step of the project consisted of making a 3-D CAD model of the aircraft. This model was then used for the CFD simulations in Fluent. 2-D, 3-D, inviscid, and viscous simulations were preformed on the aircraft. A pressure rake was designed to house a 5-hole probe and 18 Pitot probes that extended forward of the main wing to measure the location and strength of the canard wake at various flight conditions. There were five primary test points that were recorded at multiple times over the course of three flights. Once all of the data were collected from the flights, the freestream conditions became the inputs into the final, 3-D CFD simulations on the aircraft. The good agreement between the CFD results and the in-flight measurements provided the necessary verification of the CFD model of the aircraft. These results can be used in the future planning and execution of experiments involving the Velocity XL-5 RG.
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Books on the topic "Wind tunnel tests"

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Ajay, Kumar, Kegelman Jerome T, and United States. National Aeronautics and Space Administration., eds. The Langley wind tunnel enterprise. [Washington, DC: National Aeronautics and Space Administration, 1998.

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Ajay, Kumar, Kegelman Jerome T, and United States. National Aeronautics and Space Administration., eds. The Langley wind tunnel enterprise. [Washington, DC: National Aeronautics and Space Administration, 1998.

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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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MacKinnon, A. Wind tunnel tests on a variable camber wing. Cranfield, Bedford, England: College of Aeronautics, Cranfield University, 1993.

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Galway, R. D. The IAR High Reynolds Number Two-Dimensional Test Facility - a description of equipment and procedures common to most 2-D airfoil tests. Ottawa, Ont: National Research Council Canada, Institute for Aerospace Research, 1990.

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Galway, R. D. The IAR high Reynolds number two-dimensional test facility - a description of equipment and procedures common to most 2-D airfoil tests. Ottawa: National Research Council of Canada, Institute for Aerospace Research, 1990.

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Center, Lewis Research, and United States. National Aeronautics and Space Administration., eds. Flow field surveys of the NASA Lewis Research Center 8- by 6-foot supersonic wind tunnel (1993 test). [Cleveland, Ohio]: National Aeronautics and Space Administration, Lewis Research Center, 1998.

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Kelly, Abeyounis William, and Langley Research Center, eds. 16-foot transonic tunnel test section flowfield survey. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1994.

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Kelly, Abeyounis William, and Langley Research Center, eds. 16-foot transonic tunnel test section flowfield survey. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1994.

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Book chapters on the topic "Wind tunnel tests"

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Fujino, Yozo, Kichiro Kimura, and Hiroshi Tanaka. "Wind Tunnel Tests." In Wind Resistant Design of Bridges in Japan, 89–118. Tokyo: Springer Japan, 2012. http://dx.doi.org/10.1007/978-4-431-54046-5_6.

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Gibertini, G., D. Grassi, N. Scarpellini, D. Spreafico, and D. Trovato. "Wind Tunnel Tests of Speed-Skier." In IFMBE Proceedings, 224–27. Berlin, Heidelberg: Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/978-3-642-14515-5_58.

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Nicolosi, F., V. Cusati, D. Ciliberti, Pierluigi Della Vecchia, and S. Corcione. "Aeroelastic Wind Tunnel Tests of the RIBES Wing Model." In Flexible Engineering Toward Green Aircraft, 9–28. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-36514-1_2.

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Starossek, U., H. Ziems, and T. Ferenczi. "Eccentric-wing flutter stabilizer: Analysis and wind tunnel tests." In Insights and Innovations in Structural Engineering, Mechanics and Computation, 53–58. Taylor & Francis Group, 6000 Broken Sound Parkway NW, Suite 300, Boca Raton, FL 33487-2742: CRC Press, 2016. http://dx.doi.org/10.1201/9781315641645-9.

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Zhu, Weijun, and Dichen Li. "Overview of Wind Tunnel Test Models." In Models for Wind Tunnel Tests Based on Additive Manufacturing Technology, 1–20. Singapore: Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-99-5877-1_1.

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Zhu, Weijun, and Dichen Li. "Inspection Techniques of Wind Tunnel Test Models Based on Additive Manufacturing Wind Tunnel Test Models." In Models for Wind Tunnel Tests Based on Additive Manufacturing Technology, 69–90. Singapore: Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-99-5877-1_4.

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Matejka, Milan. "Experimental Results of Synthetic Jet Wind Tunnel Tests." In Recent Progress in Flow Control for Practical Flows, 233–60. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-50568-8_13.

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Kirchheck, Daniel, Dominik Saile, and Ali Gülhan. "Rocket Wake Flow Interaction Testing in the Hot Plume Testing Facility (HPTF) Cologne." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 145–62. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_9.

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Abstract Rocket wake flows were under investigation within the Collaborative Research Centre SFB/TRR40 since the year 2009. The current paper summarizes the work conducted during its third and final funding period from 2017 to 2020. During that phase, focus was laid on establishing a new test environment at the German Aerospace Center (DLR) Cologne in order to improve the similarity of experimental rocket wake flow–jet interaction testing by utilizing hydrogen–oxygen combustion implemented into the wind tunnel model. The new facility was characterized during tests with the rocket combustor model HOC1 in static environment. The tests were conducted under relevant operating conditions to demonstrate the design’s suitability. During the first wind tunnel tests, interaction of subsonic ambient flow at Mach 0.8 with a hot exhaust jet of approx. 920 K was compared to previously investigated cold plume interaction tests using pressurized air at ambient temperature. The comparison revealed significant differences in the dynamic response of the wake flow field on the different types of exhaust plume simulation.
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Schito, P., I. Bayati, M. Belloli, L. Bernini, V. Dossena, and A. Zasso. "Numerical Wind Tunnel Tests of an Open Data IPC-VAWT." In Wind Energy Exploitation in Urban Environment, 113–22. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-74944-0_8.

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Sergei, Solovev, and Khrapunov Evgenii. "Improving the Aerodynamic Stability of Bridges. Wind Tunnel Tests." In Structural Integrity, 509–15. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-29227-0_54.

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Conference papers on the topic "Wind tunnel tests"

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Coetzee, Etienne, Mark H. Lowenberg, and Simon A. Neild. "Flexible High Aspect Ratio Wing Wind Tunnel Tests." In AIAA SCITECH 2023 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2023. http://dx.doi.org/10.2514/6.2023-1311.

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Schottler, Jannik, Agnieszka Hölling, Joachim Peinke, and Michael Hölling. "Wind tunnel tests on controllable model wind turbines in yaw." In 34th Wind Energy Symposium. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-1523.

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Oerlemans, Stefan, and Paul Migliore. "Aeroacoustic Wind Tunnel Tests of Wind Turbine Airfoils." In 10th AIAA/CEAS Aeroacoustics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-3042.

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Plourde, B. D., J. P. Abraham, G. S. Mowry, and W. J. Minkowycz. "Wind-Tunnel Tests of Vertical-Axis Wind Turbine Blades." In ASME 2011 5th International Conference on Energy Sustainability. ASMEDC, 2011. http://dx.doi.org/10.1115/es2011-54604.

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An ongoing research project is investigating the potential of locating vertical-axis wind turbines (WT) on remote, off-grid cellular communication towers. The goal of the WT is to provide local power generation to meet the electrical needs of the tower. While vertical-axis devices are less efficient than their more traditional horizontal-axis counterparts, they provide a number of practical advantages which make them a suitable choice for the present situation. First, the direction of their axis is aligned with the existing tower and its rotation does not interfere with the tower structure. Second, vertical-axis devices are much less susceptible to the direction of wind and they do not require control-systems to ensure they are oriented correctly. Third, vertical-axis turbines have very low start-up wind speeds so that they generate power over a wide range of speeds. Fourth, since vertical-axis turbines rotate at a slower speed compared with horizontal counterparts, they impart a lessened vibration load to the tower. These facts, collectively, make the vertical-axis turbine suitable for the proposed application. The design process involved a detailed initial design of the turbine blade using computational methods. Next, a trio of designs was evaluated experimentally in a large, low-speed wind tunnel. The wind tunnel is operated by the University of Minnesota’s St. Anthony Falls Fluid Laboratory. The tunnel possesses two testing sections. The larger section was sufficient to test a full-size turbine blade. Accounting was taken of the blockage effect following the tests. The experiments were completed on (1) a solid-wing design (unvented), (2) a slotted-wing design (vented), and (3) a capped-and-slotted design (capped). Conditions spanned a wide range of wind speeds (4.5–11.5 m/s). The turbines were connected to electronics which simulated a range of electrical loads. The tested range was selected to span the expected range of resistances which will be found in practice. It was discovered that over a range of these wind speeds and electrical resistances, slots located on the wings result in a slight improvement in power generation. On the other hand, the slotted-and-capped design provided very large increases in performance (approximately 200–300% compared with the unvented version). This large improvement has justified commercialization of the product for use in powering remote, off-grid cellular communication towers.
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"MORPHING WING REAL TIME OPTIMIZATION IN WIND TUNNEL TESTS." In 7th International Conference on Informatics in Control, Automation and Robotics. SciTePress - Science and and Technology Publications, 2010. http://dx.doi.org/10.5220/0002885701140124.

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Corneille, Jennifer, and M. Franke. "Wind tunnel tests of a joined wing missile model." In 38th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-938.

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Vnuchkov, D. A., V. I. Zvegintsev, D. G. Nalivaychenko, V. I. Smoljaga, and A. V. Stepanov. "Solid fuel ramjet tests in wind tunnel." In INTERNATIONAL CONFERENCE ON THE METHODS OF AEROPHYSICAL RESEARCH (ICMAR 2018). Author(s), 2018. http://dx.doi.org/10.1063/1.5065090.

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Eberhardt, Scott. "Preliminary Wind Tunnel Tests of WWI Fighters." In 44th AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-333.

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TEWELL, J., and D. BUELL. "Shuttle derived launch vehicle wind tunnel tests." In 3rd Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1985. http://dx.doi.org/10.2514/6.1985-5021.

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Etter, Robert J., Jewel B. Barlow, Ahmad Kassaee, and Hareen Aparakakankanange. "Wind Tunnel Tests of a Trimaran Hull." In SNAME 29th American Towing Tank Conference. SNAME, 2010. http://dx.doi.org/10.5957/attc-2010-034.

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The U.S. Navy is developing technologies to produce surface warships with higher speeds and varying mission capabilities. An enhanced understanding of the hydrodynamics of high speed multi-hull ships is one of the key technologies. The experimental set-up and very limited sample data reported in this paper were developed for tests of a trimaran hull in a large cross-section, Mach 0.3 capable, closed circuit wind tunnel. The purpose of the paper is principally to describe the technique used to design and execute the test program. The hull model is of the “reflex” type in which a mirror image of the hull below the waterline is used to create a symmetric model representing the ship at zero pitch and yaw and with no waves at the plane of the “free-surface” To evaluate the influence of the hulls, main hull and side hulls, on the frictional and form drag resistance of each other, the model was configured with two longitudinal and three transverse side hull (outrigger) spacings relative to the main hull. The paper discusses the model design, mounting technique and drag and pressure distribution measurements. The wind tunnel model hull geometry is a nominally 1/30 scale model of a preliminary version of the Royal Navy Technology Demonstrator R.V. TRITON (2001- 2005). This geometry was chosen since it closely represented an actual trimaran ship that had been designed and built and for which technical information existed in the unclassified literature. This preliminary hull geometry had been previously tow tank model tested (Gale, et al, 1996) with a main hull waterline length of 6.0 meters. The wind tunnel model had a main hull length of 3.0 meters and side hulls 1.2 meters long at the waterline. Non-dimensional maximum side hull spacing corresponded to the towing tank transverse location. The minimum sidehull transverse spacing was as close to the mainhull at the waterline as felt reasonable. An intermediate spacing was selected midway between the maximum and minimum. The minimum sidehull spacing was actually so small as to negate the roll stability improvement which might lead one to choose a trimaran configuration over a monohull in the first place, but was selected to insure that at least some influence of the hulls on each other could be measured in the current tests. The longitudinal locations of the sidehulls relative to the mainhull matched two of the five non-dimensional locations used in the towing tank tests. A third intermediate longitudinal location was provided for in the wind tunnel model, but was not used due to budget and schedule constraints. The wind tunnel speed was varied from 27.5 to 95.7 m/s or 62 to 215 mph to provide a range of Reynolds numbers on the model and the mounting system. Mounting the model in the wind tunnel test section provided a challenge. The model needed to be mounted in a rigid configuration that could accommodate alignment and utilize the wind tunnel external balance six-component force measuring system (Barlow, et al, 1999, 2009). Supplementary drags of the sidehulls and the sidehull mounting system were measured by a force gage mounted inside the mainhull. Pressures at 91 locations on the mainhull were measured by pressure transducers inside the mainhull. Signals from the internal instrumentation were transferred out of the transom of the model mainhull and into the aft sting mount on the on the wind tunnel external balance system. To support the model forward of the sting mount, faired cables or “flying wires” were utilized from the main hull to the external balance system. Removable duplicate cables and struts were used to allow dummy drag values to be determined for tares to correct for mounting system drags.
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Reports on the topic "Wind tunnel tests"

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Ghee, Terence A., and Nigel J. Taylor. Low-Speed Wind Tunnel Tests on a Diamond Wing High Lift Configuration. Fort Belvoir, VA: Defense Technical Information Center, June 2000. http://dx.doi.org/10.21236/ada377908.

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Hosoya, N., J. A. Peterka, R. C. Gee, and D. Kearney. Wind Tunnel Tests of Parabolic Trough Solar Collectors: March 2001--August 2003. Office of Scientific and Technical Information (OSTI), May 2008. http://dx.doi.org/10.2172/929597.

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Sitek, M. A., and S. A. Lottes. CFD Simulations of Wind Tunnel Tests On Deer Isle – Sedgwick Bridge Model. Part 1. Static tests. Office of Scientific and Technical Information (OSTI), January 2018. http://dx.doi.org/10.2172/1433491.

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Gillard, William J. Innovative Control Effectors (Configuration 101) Dynamic Wind Tunnel Test Report. Rotary Balance and Forced Oscillation Tests. Fort Belvoir, VA: Defense Technical Information Center, July 1998. http://dx.doi.org/10.21236/ada362903.

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Abdel-Fattah, A. M., and Y. Y. Link. Wind Tunnel Tests on Jindivik Air Intake Duct with and Without an Auxiliary Intake. Fort Belvoir, VA: Defense Technical Information Center, March 1992. http://dx.doi.org/10.21236/ada251676.

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Ligotke, M. W., G. W. Dennis, and L. L. Bushaw. Wind tunnel tests of biodegradable fugitive dust suppressants being considered to reduce soil erosion by wind at radioactive waste construction sites. Office of Scientific and Technical Information (OSTI), October 1993. http://dx.doi.org/10.2172/10190697.

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Selig, M. S., and B. D. McGranahan. Wind Tunnel Aerodynamic Tests of Six Airfoils for Use on Small Wind Turbines; Period of Performance: October 31, 2002--January 31, 2003. Office of Scientific and Technical Information (OSTI), October 2004. http://dx.doi.org/10.2172/15007930.

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Oerlemans, S. Wind Tunnel Aeroacoustic Tests of Six Airfoils for Use on Small Wind Turbines; Period of Performance: August 23, 2002 through March 31, 2004. Office of Scientific and Technical Information (OSTI), August 2004. http://dx.doi.org/10.2172/15007773.

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Slone, Scott, Marissa Torres, Alexander Stott, Ethan Thomas, and Robert Ibey. CRREL Environmental Wind Tunnel upgrades and the Snowstorm Library. Engineer Research and Development Center (U.S.), January 2024. http://dx.doi.org/10.21079/11681/48077.

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Environmental wind tunnels are ideal for basic research and applied physical modeling of atmospheric conditions and turbulent wind flow. The Cold Regions Research and Engineering Laboratory's own Environmental Wind Tunnel (EWT)—an open-circuit suction wind tunnel—has been historically used for snowdrift modeling. Recently the EWT has gone through several upgrades, namely the three-axis chassis motors, variable frequency drive, and probe and data acquisition systems. The upgraded wind tunnel was used to simulate various snowstorm conditions to produce a library of images for training machine learning models. Various objects and backgrounds were tested in snowy test conditions and no-snow control conditions, producing a total of 1.4 million training images. This training library can lead to improved machine learning models for image-cleanup and noise-reduction purposes for Army operations in snowy environments.
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Lammert, Michael P., Kenneth J. Kelly, and Janet Yanowitz. Correlations of Platooning Track Test and Wind Tunnel Data. Office of Scientific and Technical Information (OSTI), February 2018. http://dx.doi.org/10.2172/1422885.

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