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Relevant bibliographies by topics / Transonic wind tunnel

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Academic literature on the topic 'Transonic wind tunnel'

Author: Grafiati

Published: 4 June 2021

Last updated: 14 February 2022

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Journal articles on the topic "Transonic wind tunnel"

1

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 (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

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Qian, Wei, and De Guan. "The Design, Manufacture and Wind Tunnel Test of the Full Aircraft Transonic Flutter Model." Advanced Materials Research 487 (March 2012): 267–72. http://dx.doi.org/10.4028/www.scientific.net/amr.487.267.

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This paper discusses the design, manufacture and wind tunnel test of a full aircraft structure similar transonic flutter model in the wind tunnel FL-26. It introduces the mechanics hypothesis, use of materials, and design methods of this model design, in which it uses a technology of dynamic finite element model’s flexibility-mode collaborative correction. In the process of the model, it adopts glass fiber, carbon fiber reinforced plastic and foam for manufacturing of dynamics similar model. After simulation calculation of the model, transonic flutter wind tunnel test of the model is finally a

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Phillips, Pamela S., and Edgar G. Waggoner. "Transonic wind-tunnel wall interference prediction code." Journal of Aircraft 27, no. 11 (1990): 915–16. http://dx.doi.org/10.2514/3.45959.

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Chen, Dan, Xiaosong Yang, Gang Li, Shouchun Guo, and Tianyi Chen. "Relativity Research of Total Pressure and Regulating Valve in Continuous Wind Tunnel and Its Application." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 38, no. 2 (2020): 325–32. http://dx.doi.org/10.1051/jnwpu/20203820325.

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As the main adjusting means of the total pressure for the continuous transonic wind tunnel, the characteristics of regulating valve directly affect the flow field performance of the wind tunnel, therefore, it is important to analyze and establish the correlation between the regulating valve and the total pressure, and it is necessary to select the appropriate regulating valve and its combination accordingly. Firstly, in terms of the pressure regulation principle of the wind tunnel pressure regulating system, combining with the flow characteristics of the regulating valve, the correlation betwe

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Damljanović, Dijana, Đorđe Vuković, Goran Ocokoljić, and Boško Rašuo. "Convergence of transonic wind tunnel test results of the AGARD-B standard model." FME Transactions 48, no. 4 (2020): 761–69. http://dx.doi.org/10.5937/fme2004761d.

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AGARD-B is a widely-used configuration of a standard wind tunnel model. Beside its originally intended application for correlation of data from supersonic wind tunnel facilities, it was tested in a wide range of Mach numbers and, more recently, used for assessment of wall interference effects, validation of computational fluid dynamics codes and validation of new model production technologies. The researchers and wind tunnel test engineers would, naturally, like to know the "true" aerodynamic characteristics of this model, for comparison with their own work. Obviously, such data do not exist,

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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 (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

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Yu, Li, Bin Bin Lv, Hong Tao Guo, Yu Yan, Xing Hua Yang, and Jian Guo Luo. "Research on Transonic Wind Tunnel Flutter Test for a Wing Model." Advanced Materials Research 1006-1007 (August 2014): 26–29. http://dx.doi.org/10.4028/www.scientific.net/amr.1006-1007.26.

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This paper adopts self-designed wing model to conduct flutter test on subsonic and transonic, and obtains flutter characteristic of the model, and the test results are used for calibration and verification of flutter procedures. The sub-critical extrapolation is used to obtain the flutter sub-critical parameters and the direct observation method is used to obtain comparison of results. Error of results obtained by the two approaches does not exceed 5%, and validates reliability of the sub-critical prediction approach in continuous adjusted dynamic pressure flutter test.

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Mokry, M., M. Khalid, Y. Mébarki, and A. Rebaine. "Experimental and numerical Investigation of wind tunnel wall interference near Mach one." Aeronautical Journal 105, no. 1052 (2001): 589–96. http://dx.doi.org/10.1017/s0001924000012537.

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Surface pressure measurements on the CAST-10-2/DOA 2 aerofoil, conducted in the IAR l.5m wind tunnel and supported by CFD simulations, are used to validate some new theoretical analyses of transonic wall interference. Based on the transonic freeze principle, it is shown that the stream Mach number correction is indeterminate near Mach one.

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Chen, Jiming, Shenghao Wu, Zhenhua Chen, Jinlei Lyu, and Haitao Pei. "Experimental Research on Noise Reduction for Continuous Transonic Wind Tunnel Loop." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 38, no. 4 (2020): 855–61. http://dx.doi.org/10.1051/jnwpu/20203840855.

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The noise level of wind tunnel test section is respected as one of the most important performance specifications to represent the flow field quality, especially for large scale wind tunnel. According to the acoustic experimental research conducted in the 0.6 m continuous transonic wind tunnel of CARDC, main noise sources in the tunnel loop included the compressor, the high-speed diffuser and the test section. To reduce the noise in the test section, it is necessary to prevent the test section from the compressor noise propagated both forward and backward. In 0.6 m wind tunnel loop, acoustic tr

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Kiock, R., F. Lehthaus, N. C. Baines, and C. H. Sieverding. "The Transonic Flow Through a Plane Turbine Cascade as Measured in Four European Wind Tunnels." Journal of Engineering for Gas Turbines and Power 108, no. 2 (1986): 277–84. http://dx.doi.org/10.1115/1.3239900.

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Reliable cascade data are esssential to the development of high-speed turbomachinery, but it has long been suspected that the tunnel environment influences the test results. This has now been investigated by testing one plane gas turbine rotor blade section in four European wind tunnels of different test sections and instrumentation. The Reynolds number of the transonic flow tests was Re2 = 8 × 105 based on exit flow conditions. The turbulence was not increased artificially. A comparison of results from blade pressure distributions and wake traverse measurements reveals the order of magnitude

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Dissertations / Theses on the topic "Transonic wind tunnel"

1

Jones, Gregory Stephen. "The measurement of wind tunnel flow quality at transonic speeds." Diss., Virginia Tech, 1991. http://hdl.handle.net/10919/39109.

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The measurement of wind tunnel flow quality for the transonic flow regime has been plagued by the inability to interpret complex unsteady flow field information obtained in the free stream. Traditionally hot wire anemometry and fluctuating pressure techniques have been used to quantify the unsteady characteristics of a wind tunnel. This research focuses on the application of these devices to the transonic flow regime. Utilizing hot wire anemometry, one can decompose the unsteady flow field with a three sensor technique, to obtain fluctuations associated with the velocity, density, and total t

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Rosson, Joel Christopher. "Dynamic flow quality measurements in a transonic cryogenic wind tunnel." Thesis, Virginia Polytechnic Institute and State University, 1985. http://hdl.handle.net/10919/101463.

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Two instruments mounted in a piggyback arrangement were developed for time-resolved measurements of dynamic flow quality in a transonic cryogenic wind tunnel. The first one is a dual hot-wire aspirating probe for measurement of stagnation pressure and temperature. The second is a miniature high-frequency response angle probe consisting of surface mounted pressure sensors. The aspirating probe was tested in the 0.3-m Transonic Cryogenic Tunnel (TCT) at NASA-Langley Research Center. Stagnation pressure and temperature measurements were taken in the free-stream of the settling chamber and test

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Griffith, Dwaine O. "Turbulence measurements and noise generation in a transonic cryogenic wind tunnel." Thesis, Virginia Tech, 1989. http://hdl.handle.net/10919/45979.

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<p>A high-frequency combination probe was used to measure dynamic flow quality in the test section of the NASA Langley 0.3-m Transonic Cryogenic Tunnel. The probe measures fluctuating stagnation (total) temperature and pressure, static pressure, and flow angles in two orthogonal planes. Simultaneous unsteady temperature and pressure measurements were also made in the settling chamber of the tunnel. The data show that the stagnation temperature fluctuations remain constant, and the stagnation pressure fluctuations increase by a factor of two, as the flow accelerates from the settling cha

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Neal, Graeme. "Three-dimensional model testing in the transonic self-streamlining wind tunnel." Thesis, University of Southampton, 1988. https://eprints.soton.ac.uk/52257/.

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The wall interference effects present on three-dimensional models during wind tunnel testing are difficult to correct using post-test model data correction methods. Further, at transonic speeds, with the use of ventilated test sections these corrections become complex to apply and inaccurate. The high quality of wind tunnel testing that is required today means that such methods are no longer satisfactory. The flexible walled wind tunnel has in recent years shown its ability to obtain two-dimensional aerofoil data free from the effects of wall boundary restraint. This work at Southampton was ai

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Suratanakavikul, Varangrat. "Computational study of compressible flow in an S-shaped duct." Thesis, Imperial College London, 1999. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.313370.

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Jeffries, Michael. "Initial investigations of transonic turbine aerodynamics using the Carleton University high-speed wind tunnel." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 2001. http://www.collectionscanada.ca/obj/s4/f2/dsk3/ftp04/NQ60956.pdf.

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Hatchett, John Henry. "An Investigation of Effectiveness of Normal and Angled Slot Film Cooling in a Transonic Wind Tunnel." Thesis, Virginia Tech, 2008. http://hdl.handle.net/10919/31324.

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An experimental and numerical investigation was conducted to determine the film cooling effectiveness of a normal slot and angled slot under realistic engine Mach number conditions. Freestream Mach numbers of 0.65 and 1.3 were tested. For the normal slot, hot gas ingestion into the slot was observed at low blowing ratios (M < 0.25). At high blowing ratios (M > 0.6) the cooling film was observed to â lift offâ from the surface. For the 30o angled slot, the data was found to collapse using the blowing ratio as a scaling parameter (x/Ms). Results from the current experiment were comp

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Doig, Graham Mechanical &amp Manufacturing Engineering Faculty of Engineering UNSW. "Compressible ground effect aerodynamics." Awarded by:University of New South Wales. Mechanical & Manufacturing Engineering, 2009. http://handle.unsw.edu.au/1959.4/44696.

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The aerodynamics of bodies in compressible ground effect flowfields from low-subsonic to supersonic Mach numbers have been investigated numerically and experimentally. A study of existing literature indicated that compressible ground effect has been addressed sporadically in various contexts, without being researched in any comprehensive detail. One of the reasons for this is the difficulty involved in performing experiments which accurately simulate the flows in question with regards to ground boundary conditions. To maximise the relevance of the research to appropriate real-world scenarios,

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Bailey, Matthew Marlando. "An Extended Calibration and Validation of a Slotted-Wall Transonic Wall-Interference Correction Method for the National Transonic Facility." Diss., Virginia Tech, 2019. http://hdl.handle.net/10919/95882.

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Correcting wind tunnel data for wall interference is a critical part of relating the acquired data to a free-air condition. Accurately determining and correcting for the interference caused by the presence of boundaries in wind tunnels can be difficult especially for facilities employing ventilated boundaries. In this work, three varying levels of ventilation at the National Transonic Facility (NTF) were modeled and calibrated with a general slotted wall (GSW) linear boundary condition to validate the computational model used to determine wall interference corrections. Free-air lift, drag, an

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Boyd, Robert Raymond. "An Experimental and Computational Investigation on the Effect of Transonic Flow in Hypersonic Wind Tunnel Nozzles, Including Filtered Rayleigh Scattering Measurements /." The Ohio State University, 1996. http://rave.ohiolink.edu/etdc/view?acc_num=osu148793364864785.

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Books on the topic "Transonic wind tunnel"

1

Everhart, Joel L. Slotted-wall flow-field measurements in a transonic wind tunnel. Langley Research Center, 1991.

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2

Brooks, Cuyler W. The NASA Langley 8-Foot Transonic Pressure Tunnel calibration. Langley Research Center, 1994.

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3

Brooks, Cuyler W. The NASA Langley 8-foot transonic pressure tunnel calibration. National Aeronautics and Space Administration, Langley Research Center, 1994.

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4

Capone, Francis J. The NASA Langley 16-Foot Transonic Tunnel: Historical overview, facility description, calibration, flow characteristics, and test capabilities. Langley Research Center, 1995.

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5

Al-Saadi, Jassim A. Wall interference and boundary simulation in a transonic wind tunnel with a discretely slotted test section. Langley Research Center, 1993.

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6

Kuczka, Detlef. Hybridverfahren fur instationare Messungen in trassonischen Windkanalen am Beispiel der harmonischen Nickschwingung. DFVLR, 1988.

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7

Green, Lawrence L. Wall-interference assessment and corrections for transonic NACA 0012 airfoil data from various wind tunnels. Langley Research Center, 1991.

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8

Ohman, L. H. New transonic test sections for the NAE 5ftx5ft trisonic wind tunnel. National Aeronautical Establishment, 1990.

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9

Mabey, Dennis G. Further buffeting tests in a cryogenic wind tunnel. National Aeronautics and Space Administration, Langley Research Center, 1992.

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10

Schairer, Edward T. A two-dimensional adaptive-wall test section with ventilated walls in the Ames 2- by 2-foot transonic wind tunnel. National Aeronautics and Space Administration, Ames Research Center, 1989.

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Book chapters on the topic "Transonic wind tunnel"

1

Mignosi, André, J. P. Archambaund, A. Seraudie, and J. B. Dor. "The T2 Cryogenic Transonic Wind Tunnel of Onera-Cert Toulouse France." In Advances in Cryogenic Engineering. Springer US, 1994. http://dx.doi.org/10.1007/978-1-4615-2522-6_8.

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2

Rasuo, Bosko. "On Boundary Layer Control in Two-Dimensional Transonic Wind Tunnel Testing." In Solid mechanics and its applications. Springer Netherlands, 2006. http://dx.doi.org/10.1007/978-1-4020-4150-1_46.

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Castro, Breno M., Kevin D. Jones, Max F. Platzer, Stefan Weber, and John A. Ekaterinaris. "Numerical Investigation of Transonic Flutter and Modeling of Wind Tunnel Interference Effects." In IUTAM Symposium Transsonicum IV. Springer Netherlands, 2003. http://dx.doi.org/10.1007/978-94-010-0017-8_12.

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Bolgar, Istvan, Sven Scharnowski, and Christian J. Kähler. "Effects of a Launcher’s External Flow on a Dual-Bell Nozzle Flow." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_7.

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Abstract Previous research on Dual-Bell nozzle flow always neglected the influence of the outer flow on the nozzle flow and its transition from sea level to altitude mode. Therefore, experimental measurements on a Dual-Bell nozzle with trans- and supersonic external flows about a launcher-like forebody were carried out in the Trisonic Wind Tunnel Munich with particle image velocimetry, static pressure measurements and the schlieren technique. A strongly correlated interaction exists between a transonic external flow with the nozzle flow in its sea level mode. At supersonic external flow conditions, a Prandtl–Meyer expansion about the nozzle’s lip decreases the pressure in the vicinity of the nozzle exit by about 55%. Therefore a new definition for the important design criterion of the nozzle pressure ratio was suggested, which considers this drastic pressure drop. Experiments during transitioning of the nozzle from sea level to altitude mode show that an interaction about the nozzle’s lip causes an inherently unstable nozzle state at supersonic free-stream conditions. This instability causes the nozzle to transition and retransition, or flip-flop, between its two modes. This instability can be eliminated by designing a Dual-Bell nozzle to transition during sub-/transonic external flow conditions.

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Dor, J. B., A. Mignosi, A. Seraudie, and B. Benoit. "Wind Tunnel Studies of Natural Shock Wave — Separation Instabilities for Transonic Airfoil Tests." In Symposium Transsonicum III. Springer Berlin Heidelberg, 1989. http://dx.doi.org/10.1007/978-3-642-83584-1_34.

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von Geyr, H. Frhr, C. C. Rossow, and H. Hoheisel. "Influence of transonic Flow on the Thrust Determination of TPS during Wind Tunnel measurements." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer Berlin Heidelberg, 2004. http://dx.doi.org/10.1007/978-3-540-39604-8_59.

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Richter, K., and H. Rosemann. "Numerical Simulation of Wind Tunnel Wall Effects on the Transonic Flow around an Airfoil Model." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-35680-3_62.

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Chanetz, Bruno, Jean Délery, Patrick Gilliéron, Patrick Gnemmi, Erwin R. Gowree, and Philippe Perrier. "Transonic Wind Tunnels." In Springer Tracts in Mechanical Engineering. Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-35562-3_4.

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Bruse, M., K. W. Bock, S. Tusche, and M. Jacobs. "Unsteady Measurements with the Continuously Rotating DLR-PSP-Model at the Transonic Wind Tunnel Göttingen (DNW-TWG)." In New Results in Numerical and Experimental Fluid Mechanics III. Springer Berlin Heidelberg, 2002. http://dx.doi.org/10.1007/978-3-540-45466-3_13.

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Bütefisch, K. A., V. Schmidt, H. Vollmers, et al. "Density Measurements on a Delta Wing by Means of Planar Intensity Distribution of Rayleigh Scattered Laser Light (PIRS) in the 1m × 1m Transonic Wind Tunnel Göttingen (TWG)." In Notes on Numerical Fluid Mechanics (NNFM). Vieweg+Teubner Verlag, 1997. http://dx.doi.org/10.1007/978-3-322-86573-1_11.

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Conference papers on the topic "Transonic wind tunnel"

1

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

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Hergert, D., G. Smith, A. Krynytzky, and C. Jauch. "Transonic wind tunnel circuit upgrade." In 39th Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-452.

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Cahill, David, Melissa Minter, and Richard Roberts. "FAVOR - National Transonic Wind Tunnel Comparison." In U.S. Air Force T&E Days 2010. American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-1716.

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Marino, Antonello, and Aldo Bonfiglioli. "Optimization of the Porosity Distribution in Transonic Wind Tunnel." In ASME 2012 Fluids Engineering Division Summer Meeting collocated with the ASME 2012 Heat Transfer Summer Conference and the ASME 2012 10th International Conference on Nanochannels, Microchannels, and Minichannels. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/fedsm2012-72487.

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During past years, to improve the quality of wind tunnel data in transonic configurations, researchers first designed new wind tunnel geometries (as porous and/or slotted wind tunnels), then developed more accurate correction laws giving acceptable results in certain conditions but absolutely not sufficient to satisfy the increasing aeronautical requirements. Recent studies showed that the quality of wind tunnel data can be improved by using test sections provided with variable streamwise porosity distributions instead of the typical uniform ones. Some authors identified this new concept of va

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Begnini, Guilherme R., Carlos A. Bones, and Cleber Spode. "Transonic Wind Tunnel Test of Wing Oscillating in Pitch." In 2018 Applied Aerodynamics Conference. American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-3004.

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Krynytzky, Alexander, and Dennis Hergert. "Boeing Transonic Wind Tunnel Upgrade Assessment (Invited)." In 22nd AIAA Aerodynamic Measurement Technology and Ground Testing Conference. American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/6.2002-2782.

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Fauci, Roberto, Alessio Nicolì, Biagio Imperatore, and U. Cella. "Wind Tunnel Tests of a Transonic Natural Laminar Flow Wing." In 25th AIAA Aerodynamic Measurement Technology and Ground Testing Conference. American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-3638.

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Crowder, J., G. Amiryants, and V. Bounkov. "Flying strut traverser for transonic wind tunnel calibration." In 20th AIAA Advanced Measurement and Ground Testing Technology Conference. American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-2872.

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PHILLIPS, PAMELA, and EDGAR WAGGONER. "A transonic wind tunnel wall interference prediction code." In 6th Applied Aerodynamics Conference. American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-2538.

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Matsushita, Hiroshi, Kenichi Saitoh, and Peter Granasy. "Wind tunnel investigation of transonic limit cycle flutter." In 39th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference and Exhibit. American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-1728.

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Reports on the topic "Transonic wind tunnel"

1

Lowry, Heard S., Mike S. Smith, William T. Bertrand, Fred Heltsley, and Daryl W. Sinclair. Integrated Optical Diagnostics for 16-ft Transonic Wind Tunnel. Defense Technical Information Center, 2001. http://dx.doi.org/10.21236/ada387335.

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