Relevant bibliographies by topics / Wind tunnel balance

Academic literature on the topic 'Wind tunnel balance'

Author: Grafiati
Published: 10 December 2022
Last updated: 28 January 2023

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Journal articles on the topic "Wind tunnel balance"

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

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During a supersonic run of a blowdown wind tunnel, temperature of air in the test section drops which can affect planned measurements. Adverse thermal effects include variations of the Mach and Reynolds numbers, variation of airspeed, condensation of moisture on the model, change of characteristics of the instrumentation in the model, et cetera. Available data on thermal effects on instrumentation are pertaining primarily to long-run-duration wind tunnel facilities. In order to characterize such influences on instrumentation in the models, in short-run-duration blowdown wind tunnels, temperature measurements were made in the wing-panel-balance and main-balance spaces of two wind tunnel models tested in the T-38 wind tunnel. The measurements showed that model-interior temperature in a run increased at the beginning of the run, followed by a slower drop and, at the end of the run, by a large temperature drop. Panel-force balance was affected much more than the main balance. Ways of reducing the unwelcome thermal effects by instrumentation design and test planning are discussed.
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Burns, Devin E., and Peter A. Parker. "Additively Manufactured Wind-Tunnel Balance." Journal of Aircraft 57, no. 5 (September 2020): 958–63. http://dx.doi.org/10.2514/1.c035889.

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

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Abstract For the definition of the acccuracy of an internal strain gauge balance no general agreement exists. So it is difficult or even impossible, to compare balances from different manufacturers or balances used at different places. Since most wind tunnel tests at least in the aeronautical field are done on a reference basis i.e. the results are compared with earlier results achieved with a more or less different configuration, repeatability is at least as important as absolute accuracy or even more important. So also repeatability, which in a physical sense is quite different from accuracy, must be defined and proven for each balance. With the examples of several balances manufactured for the DNW (Deutsch-Niederländischer Windkanal) and ETW (European transonic tunnel) accuracy and repeatability definitions are discussed. A proposal for a generally binding definition of accuracy and repeatability is given.
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EWALD, B. "WIND TUNNEL INSTRUMENTATION TECHNIQUE BALANCE DESIGN PROBLEMS." International Conference on Aerospace Sciences and Aviation Technology 1, CONFERENCE (May 1, 1985): 1–8. http://dx.doi.org/10.21608/asat.1985.26474.

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

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To apply the experimental data measured in a wind tunnel for a scaled aircraft to a free-flying model, conditions of dynamical similarity must be met or scaling procedures introduced. The scaling methods should correct the wind tunnel data regarding model support, wall interference, and lower Reynolds number. To include the necessary corrections, the current scaling techniques use computational fluid dynamics (CFD) in combination with measurements in cryogenic wind tunnels. There are a few methods that enable preliminary calculations of typical corrections considering specific measurement conditions and volume limitation of test section. The purpose of this paper is to present one possible approach to estimating corrections due to sting interference and difference in Reynolds number between the real airplane in cruise regime and its 1:100 model in the small wind tunnel AT-1. The analysis gives results for correction of axial and normal force coefficients. The results of this analysis indicate that the Reynolds number effects and the problem of installation of internal force balance are quite large. Therefore, the wind tunnel AT-1 has limited usage for aerodynamic coefficient determination of transport airplanes, like Dash 8 Q400 analyzed in this paper.
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Shi, Pengtao, Jihai Liu, Yingsong Gu, Zhichun Yang, and Pier Marzocca. "Full-Span Flying Wing Wind Tunnel Test: A Body Freedom Flutter Study." Fluids 5, no. 1 (March 16, 2020): 34. http://dx.doi.org/10.3390/fluids5010034.

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Aiming at the experimental test of the body freedom flutter for modern high aspect ratio flexible flying wing, this paper conducts a body freedom flutter wind tunnel test on a full-span flying wing flutter model. The research content is summarized as follows: (1) The full-span finite element model and aeroelastic model of an unmanned aerial vehicle for body freedom flutter wind tunnel test are established, and the structural dynamics and flutter characteristics of this vehicle are obtained through theoretical analysis. (2) Based on the preliminary theoretical analysis results, the design and manufacturing of this vehicle are completed, and the structural dynamic characteristics of the vehicle are identified through ground vibration test. Finally, the theoretical analysis model is updated and the corresponding flutter characteristics are obtained. (3) A novel quasi-free flying suspension system capable of releasing pitch, plunge and yaw degrees of freedom is designed and implemented in the wind tunnel flutter test. The influence of the nose mass balance on the flutter results is explored. The study shows that: (1) The test vehicle can exhibit body freedom flutter at low airspeeds, and the obtained flutter speed and damping characteristics are favorable for conducting the body freedom flutter wind tunnel test. (2) The designed suspension system can effectively release the degrees of freedom of pitch, plunge, and yaw. The flutter speed measured in the wind tunnel test is 9.72 m/s, and the flutter frequency is 2.18 Hz, which agree well with the theoretical results (with flutter speed of 9.49 m/s and flutter frequency of 2.03 Hz). (3) With the increasing of the mass balance at the nose, critical speed of body freedom flutter rises up and the flutter frequency gradually decreases, which also agree well with corresponding theoretical results.
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Lynn, Keith C., Sean A. Commo, and Peter A. Parker. "Wind-Tunnel Force Balance Characterization for Hypersonic Research Applications." Journal of Aircraft 49, no. 2 (March 2012): 556–65. http://dx.doi.org/10.2514/1.c031567.

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

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Dissertations / Theses on the topic "Wind tunnel balance"

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Katirci, Argun. "Automation And Verification Of Ankara Wind Tunnel." Master's thesis, METU, 2003. http://etd.lib.metu.edu.tr/upload/12607692/index.pdf.

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All the operational and measurement systems of Ankara Wind Tunnel was modified to operate automatically under the control of a central computer system programmed using the Lab View programming language. A cruciform air-to-air missile with triangular canard control and a trapezoidal wing model was tested by a 35mm diameter internal balance at Mach 0.2 and data was compared with the test data of the same model&rsquo
s test that was performed at NASA Langley Research Center.
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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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Parker, David Huw. "Techniques for extreme attitude suspension of a wind tunnel model in a magnetic suspension and balance system." Thesis, University of Southampton, 1989. https://eprints.soton.ac.uk/52256/.

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Although small scale magnetic suspension and balance systems (MSBSs) for wind tunnel use have been in existence for many years, they have not found general application in the production testing of flight vehicles. One reason for this is thought to lie in the relatively limited range of attitudes over which a wind tunnel model may be suspended. This text reports on the modifications made to an existing small MSBS at Southampton University to permit the suspension and control of axisymmetric models over an angle of attack range from less than zero degrees to over ninety degrees. Previous work had shown that the existing arrangement of ten electromagnets was unable to generate one of the force components necessary for control at the extreme attitudes. Examination of possible solutions has resulted in a simple alteration which rectifies this deficiency. To generate the feedback signals essential to control the magnetically suspended model, an optical position sensing system using collimated beams of laser light illuminating photodiode arrays has been installed and tested. An analytical basis has been developed for distributing the demands for force and moment needed for model stabilisation amongst the electromagnets and over the full attitude range. This has been implemented by an MSBS control program able to continually adjust the distribution for the instantaneous incidence in accordance with pre-scheduled data. Results presented demonstrate rotations of models from nought to ninety degrees at rates of change up to ninety degrees per second, with pitching rates rising to several hundred degrees per second in response to step-change demands. A study of a design for a large MSBS suggests that such a system could be given the capability to control a model in six degrees of freedom over an unlimited angle of attack range.
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Edwards, Alex T. "Comparison of Strain Gage and Fiber Optic Sensors On A Sting Balance In A Supersonic Wind Tunnel." Thesis, Virginia Tech, 2000. http://hdl.handle.net/10919/30799.

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Force and moment balances have proved to be essential in the measurement and calculation of aerodynamic properties during wind tunnel testing. With the recent advancements of technology, new fiber optic sensors have been designed to replace the conventional foil strain gage sensors commonly found on balances, thereby offering several distinct advantages. The use of fiber optic sensors on a balance brings with it some potential advantages over conventional strain gage balances including increased resolution and accuracy, insensitivity to electromagnetic interference, and the capability of use at high temperatures. By using the fiber optic sensors, some of the limitations of the conventional balance can be overcome, leading to a better overall balance design.

This thesis considers an initial trial application of new fiber optic sensors on a conventional, six-component sting balance while retaining the original foil strain gage sensors for comparison. Tests were conducted with a blunt, 10º half-angle cone model in the Virginia Tech 9x9 inch Supersonic Wind Tunnel at Mach 2.4 with a total pressure of 48 psia and ambient total temperature of 25.3ºC. Results showed a close comparison between the foil strain gages and the fiber optic sensor measurements, which were set up to measure the normal force and pitching moment on the blunt cone model. A Finite Element Model (FEM) of the sting balance was produced in order to determine the best locations for the fiber optic sensors on the sting balance. Computational Fluid Dynamics (CFD) was also used in order to predict and compare the results acquired from all of the sensors.
Master of Science

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Lines, Philipp A. "Upgrade of a LabVIEW based data acquisition system for wind tunnel test of a 1/10 scale OH-6A helicopter fuselage." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2003. http://library.nps.navy.mil/uhtbin/hyperion-image/03Jun%5FLines.pdf.

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Thesis (M.S. in Aeronautical Engineering)--Naval Postgraduate School, June 2003.
Thesis advisor(s): E. Roberts Wood, Richard M. Howard. Includes bibliographical references (p. 53-54). Also available online.
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Nacakli, Yavuz. "Detailed Measurements Of Dynamic Stability Derivatives Under Roll Oscillations For Standard Dynamic Model In Ankara Wind Tunnel." Master's thesis, METU, 2003. http://etd.lib.metu.edu.tr/upload/4/1206846/index.pdf.

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The subject of this experimental investigation is to measure the dynamic stability derivatives in roll plane for an oscillating combat aircraft model by using forced oscillation technique. In forced oscillation technique the model is forced to oscillate around the center of gravity according to a harmonic motion of small amplitude and low frequency. The aerodynamic reactions are measured by an internal balance placed inside the model. The thesis presents a brief description of the test rig and the measurement system. The theory of dynamic stability derivatives and forced oscillation technique are also explained. The data is collected and analyzed by using a data acquisition system written with under the Labview programming language. Systematic analysis of the static and dynamic tests results and effect of various parameters (angle of attack, sideslip angle, oscillation frequency and amplitude, wind velocity) on these results are presented. Comparison of the present results with previous results obtained in other test facilities is also given. Design and manufacture process of a new angle of attack mechanism is also given in this thesis.
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Fryšták, Lukáš. "Aerodynamická optimalizace monopostu formule SAE." Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2016. http://www.nusl.cz/ntk/nusl-254335.

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Tato práce se zabývá měřením aerodynamických charakteristik modelu závodního vozu Formula SAE v aerodynamickém tunelu, v měřítku 1:4. V první části je představen projekt Formula SAE a popsána role aerodynamiky v rámci této soutěže. Následuje přehled teoretického pozadí, které je relevantní k provedenému experimentu. Ve druhé části práce je popsán samotný experiment a prezentovány jeho výsledky. Součástí je návrh, výroba a kalibrace šestikomponentní tenzometrické váhy pro měření aerodynamického zatížení. Testy v aerodynamickém tunelu byly provedeny ve čtyřech konfiguracích, aby bylo možné určit vliv přítlačných křídel a podlahy s difuzorem na výsledné aerodynamické charakteristiky vozu.
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Broughton, Benjamin Albert. "Low speed wind tunnel testing and data correction methods for aircraft models in ground effect." Diss., University of Pretoria, 1999. http://hdl.handle.net/2263/24292.

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In this thesis, techniques for testing aircraft models in ground effect in a low speed wind tunnel are investigated. Although these types of tests have been done before, the current study is unique in that forces are measured with an overhead balance instead of an internal balance. This has the advantage that the types of models that are difficult to mount on a sting with an internal balance, can often be mounted with a strut protruding from the top of the model. Positioning a sting-mounted model close to the ground at a high angle-of-attack is also usually difficult if not impossible. Finally, drag measurements are often more accurate when measured with an overhead balance rather than with an internal sting-type balance. The disadvantages associated with this method of testing are identified and solutions suggested. These include accurate moment transfers and correcting for support tares and interference. The thesis also investigates general procedures associated with ground effect testing such as proper boundary corrections and the necessity of a rolling floor. A simplified preliminary test series was performed in order to identify shortcomings in the existing equipment and procedures. This series is explained in Chapter 2. Chapter 4 and 5 describe changes made to the existing equipment following this test series. These include a novel telescopic fairing to shroud the mounting strut and an internal pitching mechanism. The correction techniques and general theory are summarised in Chapter 3. The author concludes in Chapter 6 that with the application of the techniques described in this thesis, the test engineer should be able to obtain accurate and reliable data from most aircraft configurations. Additional suggestions for testing models in ground effect are also given in this chapter. Finally, a few shortcomings that still need to be investigated are mentioned at the end of Chapter 6. AFRIKAANS : Hierdie verhandeling ondersoek tegnieke om vliegtuigmodelle in grondeffek in 'n laespoed-windtonnel te toets. Alhoewel hierdie tipe van toetse al voorheen gedoen is, is die huidige studie uniek deurdat 'n oorhoofse balans eerder as 'n interne balans gebruik word. Die voordeel hiervan is dat modelle wat moeilik op 'n naald- of "sting"-balans monteer kan word, baie keer makliker monteer kan word met 'n stang wat deur die bokant van die model steek. Posisioneering van 'n naald-gemonteerde model naby aan die vloer van die tonnel by hoe invalshoeke is gewoonlik ook baie moeilik indien nie onmoontlik nie. Laastens is sleurkrag-metings wat met 'n oorhoofse balans gemeet is gewoonlik meer akkuraat as sleurkrag-metings wat met 'n interne naald-tipe balans gedoen is. Die nadele wat met hierdie toetsmetode geassosieer kan word, word geïdentifiseer en moontlike oplossing word voorgestel. Hierdie sluit die berekening in van akkurate moment-transformasies en monteersleureffekte en -steurings. Die verhandeling ondersoek ook algemene prosedures wat met grondeffektoetse geassosieer kan word, byvoorbeeld akkurate wandkorreksies en die nodigheid van die rolvloer. 'n Vereenvoudigde vooraf-toetsreeks was uitgevoer om moontlike tekortkominge in die bestaande toerusting en prosedures te identifiseer. Hierdie toetsreeks word in Hoofstuk 2 bespreek. Hoofstuk 4 en 5 verduidelik die veranderinge wat aan die bestaande toerusting gemaak is na aanleidng van hierdie toetsreeks. Hierdie veranderinge sluit 'n teleskopiese windskerm in om die monteerstang te isoleer van die wind, sowel as 'n interne heimeganisme om die invalshoek van die model te verstel. Die korreksieprosedures en algemene teorie word in Hoofstuk 3 opgesom. Die outeur se gevolgtekking in Hoofstuk 6 stel dat die toetsingenieur, met behulp van die gebruik van die tegnieke in hierdie verhandeling beskryf, in staat behoort te wees om betroubare metings te kan neem van meeste vliegtuigkonfigurasies. Verdere voorstelle vir die toets van modelle in grondeffek word ook in hierdie hoofstuk gemaak. Uiteindelik word 'n paar tekortkominge genoem wat moontlik in 'n toekomstige studie ondersoek kan word.
Dissertation (MEng)--University of Pretoria, 1999.
Mechanical and Aeronautical Engineering
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Sevier, Abigail. "Feasibility Study for Testing the Dynamic Stability of Blunt Bodies with a Magnetic Suspension System in a Supersonic Wind Tunnel." Case Western Reserve University School of Graduate Studies / OhioLINK, 2017. http://rave.ohiolink.edu/etdc/view?acc_num=case1493207020743959.

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Chen, Ru-Ching. "Development of a Supersonic Nozzle and Test Section for use with a Magnetic Suspension System for Re-Entry Aeroshell Models." Case Western Reserve University School of Graduate Studies / OhioLINK, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=case1544179612537658.

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Books on the topic "Wind tunnel balance"

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Britcher, Colin P. Application of magnetic suspension and balance systems to ultra-high Reynolds number facilities. [Washington, D.C: National Aeronautics and Space Administration, 1996.

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Britcher, Colin P. Applications of magnetic suspension technology to large scale facilities: Progress, problems and promises. [Washington, DC: National Aeronautics and Space Administration, 1997.

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Johnson, William G. The 13-inch magnetic suspension and balance system wind tunnel. Hampton, Va: Langley Research Center, 1989.

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Johnson, William G. The 13-inch magnetic suspension and balance system wind tunnel. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Division, 1989.

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Johnson, William G. The 13-inch magnetic suspension and balance system wind tunnel. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Division, 1989.

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Johnson, William G. The 13-inch magnetic suspension and balance system wind tunnel. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Division, 1989.

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Johnson, William G. The 13-inch magnetic suspension and balance system wind tunnel. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Division, 1989.

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Baljeu, J. F. Development of a multi-component internal strain-gauge balance for model tests in a cryogenic wind tunnel. Amsterdam: National Aerospace Laboratory, 1988.

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Welsh, B. L. A dynamic balance for the measurement of time-dependent aerodynamic forces on wind-tunnel models. London: HMSO, 1990.

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Huebner, Lawrence D. Assessment of a flow-through balance for hypersonic wind tunnel models with scramjet exhaust flow simulation. Hampton, Va: Langley Research Center, 1993.

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Book chapters on the topic "Wind tunnel balance"

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Oyama, Tomokazu, T. Ichige, A. Inoue, and J. Bredenbeck. "Electrical wind tunnel external balance system." In Proceedings, 1177–91. Wiesbaden: Springer Fachmedien Wiesbaden, 2014. http://dx.doi.org/10.1007/978-3-658-05130-3_84.

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Hufnagel, Klaus. "Utilization of Balances in the Wind Tunnel." In Experimental Fluid Mechanics, 273–76. Cham: Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-030-97766-5_10.

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Ştefănescu, Dan Mihai. "Strain Gauge Balances for Testing Car and Flight Models in Wind Tunnel Applications." In Handbook of Force Transducers, 177–88. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-35322-3_17.

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Gonzalez, Miguel, Jose Miguel Ezquerro, Victoria Lapuerta, Ana Laveron, and Jacobo Rodriguez. "Components of a Wind Tunnel Balance: Design and Calibration." In Wind Tunnels and Experimental Fluid Dynamics Research. InTech, 2011. http://dx.doi.org/10.5772/21095.

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"Calibration and Use of Internal Strain-Gage Balances with Application to Wind Tunnel Testing (AIAA R-091A-2020)." In Calibration and Use of Internal Strain-Gage Balances with Application to Wind Tunnel Testing (AIAA R-091A-2020). 12700 Sunrise Valley Drive, Suite 200, Reston, VA 20191: American Institute of Aeronautics and Astronautics, Inc., 2020. http://dx.doi.org/10.2514/4.106019.001.

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"Recommended Practice: Calibration and Use of Internal Strain-Gage Balances with Application to Wind Tunnel Testing (AIAA R-091-2003)." In Recommended Practice: Calibration and Use of Internal Strain-Gage Balances with Application to Wind Tunnel Testing (AIAA R-091-2003). Washington, DC: American Institute of Aeronautics and Astronautics, Inc., 2003. http://dx.doi.org/10.2514/4.476464.001.

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Conference papers on the topic "Wind tunnel balance"

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Alves, Leonardo Boa Sorte, Marco Gabaldo, Luiz Severiano Dutra, and Jose Eduardo Mautone Barros. "Wind Tunnel Balance." In 26th SAE BRASIL Inernational Congress and Display. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2017. http://dx.doi.org/10.4271/2017-36-0237.

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Hufnagel, Klaus, Bernd Ewald, Ruediger Rebstock, and Junnai Zhai. "Advanced half model wind tunnel balance developments." In 21st Aerodynamic Measurement Technology and Ground Testing Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-2385.

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Karkehabadi, Reza, and Ray Rhew. "Structural Integrity of a Wind Tunnel Balance." In 42nd AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-1293.

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Landman, Drew, and Jim Simpson. "A Wind Tunnel External Balance Calibration Using Design of Experiments." In 2007 U.S. Air Force T&E Days. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-1604.

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Polansky, L., W. Matich, and J. T. Kutney. "A New Multi-Component-Wind-Tunnel-Balance for Automotive Windtunnels." In International Congress & Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1995. http://dx.doi.org/10.4271/950995.

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Reis, Maria Luísa, Olympio Mello, and Sadahaki Uyeno. "Calibration Uncertainty of an External Six-Component Wind Tunnel Balance." In 33rd AIAA Fluid Dynamics Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-3884.

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Reis, Maria Luísa, Wilson Vieira, Itamar Barbosa, Olympio Achilles Mello, and Luciano Santos. "Validation of an External Six-Component Wind Tunnel Balance Calibration." In 24th AIAA Aerodynamic Measurement Technology and Ground Testing Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-2300.

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Choi, Simon, and J. Stewart. "Force Balance Measurement Sensor in Wind Tunnel Aerodynamic Testing Environments." In USAF Developmental Test and Evaluation Summit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-6812.

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Ulbrich, Norbert. "Combined Load Diagram for a Wind Tunnel Strain-Gage Balance." In 27th AIAA Aerodynamic Measurement Technology and Ground Testing Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-4203.

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Britcher, Colin P., and David E. Cox. "Electromagnetic Modeling of Wind Tunnel Magnetic Suspension and Balance Systems." In AIAA SCITECH 2023 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2023. http://dx.doi.org/10.2514/6.2023-1819.

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Reports on the topic "Wind tunnel balance"

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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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Fuchs, Marcel, Jerry Hatfield, Amos Hadas, and Rami Keren. Reducing Evaporation from Cultivated Soils by Mulching with Crop Residues and Stabilized Soil Aggregates. United States Department of Agriculture, 1993. http://dx.doi.org/10.32747/1993.7568086.bard.

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Abstract:
Field and laboratory studies of insulating properties of mulches show that the changes they produce on the heat balance and the evaporation depend not only on the intrinsic characteristics of the material but also on the structure of air flow in boundary layer. Field measurements of the radiation balance of corn residue showed a decrease of reflectivity from 0.2 to 0.17 from fall to spring. The aerodynamic properties of the atmospheric surface layer were turbulent, with typical roughness length of 12 to 24 mm. Evaporation from corn residue covered soils in climate chambers simulating the diurnal course of temperature in the field were up to 60% less than bare soil. Wind tunnel studies showed that turbulence in the atmospheric boundary layer added a convective component to the transport of water vapor and heat through the mulches. The decreasing the porosity of the mulch diminished this effect. Factors increasing the resistance to vapor flow lowering the effect of wind. The behavior of wheat straw and stabilized soil aggregates mulches were similar, but the resistance to water of soil aggregate layer with diameter less than 2 mm were very large, close to the values expected from molecular diffusion.
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