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Academic literature on the topic 'Transonic tunnel'

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Published: 10 December 2022
Last updated: 29 January 2023

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Journal articles on the topic "Transonic tunnel"

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Greenwell, D. I. "Transonic industrial wind tunnel testing in the 2020s." Aeronautical Journal 126, no. 1295 (December 2, 2021): 125–51. http://dx.doi.org/10.1017/aer.2021.107.

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AbstractWind tunnels remain an essential element in the design and development of flight vehicles. However, graduates in aerospace engineering tend to have had little exposure to the demands of industrial experimental work, particularly at high speed, a situation exacerbated by a lack of up-to-date reference material. In an attempt to fill this gap, this paper presents an overview of the current and near-term status and usage of transonic industrial wind tunnels. The review is aimed at recent entrants to the field, with the aim of helping them make the step from research projects in small university facilities to commercial projects in large industrial facilities. In addition, a picture has emerged from the review that contradicts received wisdom that the wind tunnel is in decline. Globally, the industrial transonic wind tunnel is undergoing somewhat of a renaissance. Numbers are increasing, investment levels are rising, capabilities are being enhanced, and facilities are busy.
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Tsushima, Natsuki, Kenichi Saitoh, Hitoshi Arizono, and Kazuyuki Nakakita. "Structural and Aeroelastic Studies of Wing Model with Metal Additive Manufacturing for Transonic Wind Tunnel Test by NACA 0008 Example." Aerospace 8, no. 8 (July 25, 2021): 200. http://dx.doi.org/10.3390/aerospace8080200.

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Additive manufacturing (AM) technology has a potential to improve manufacturing costs and may help to achieve high-performance aerospace structures. One of the application candidates would be a wind tunnel wing model. A wing tunnel model requires sophisticated designs and precise fabrications for accurate experiments, which frequently increase manufacturing costs. A flutter wind tunnel testing, especially, requires a significant cost due to strict requirements in terms of structural and aeroelastic characteristics avoiding structural failures and producing a flutter within the wind tunnel test environment. The additive manufacturing technique may help to reduce the expensive testing cost and allows investigation of aeroelastic characteristics of new designs in aerospace structures as needed. In this paper, a metal wing model made with the additive manufacturing technique for a transonic flutter test is studied. Structural/aeroelastic characteristics of an additively manufactured wing model are evaluated numerically and experimentally. The transonic wind tunnel experiment demonstrated the feasibility of the metal AM-based wings in a transonic flutter wind tunnel testing showing the capability to provide reliable experimental data, which was consistent with numerical solutions.
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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 accomplished in the wind tunnel FL-26.
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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 (April 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 between the position control of the regulating valve and the total pressure control of the wind tunnel is established, then the static test is conducted to verify the relationship. In order to shorten the flow field stability time under the negative pressure of 0.6m continuous transonic wind tunnel, based on the established theory, the valve system is optimized and reformed, and the blowing test is carried out. The results show that the time of optimized Mach number polar curve decreases by 40%~50%, which greatly improves the test efficiency, which further proves that the present analysis is correct and effective, and can provide reference for the design of pressure regulating system in continuous transonic wind tunnel.
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Kaczyński, P., R. Szwaba, M. Piotrowicz, P. Flaszyński, and P. Doerffer. "Wind tunnel investigations of aircraft airfoil in cruise conditions." Journal of Physics: Conference Series 2367, no. 1 (November 1, 2022): 012019. http://dx.doi.org/10.1088/1742-6596/2367/1/012019.

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Abstract Presented work is focused on analysis of the flow over the 2D model of Airbus A320 airfoil wing in cruise phase of the flight. For this purpose the measurement channel with an airfoil model was designed and assembled in a transonic wind tunnel to obtain a similar flow pattern as in the reference two-dimensional freestream flow. Experimental investigations were conducted in the IMP PAN transonic wind tunnel with a relative narrow test section which is a novel approach in terms of these type of research. The test section was designed using CFD simulations based on 2D freestream flow for the tested wing profile and in the next step the research were continued experimentally in transonic wind tunnel with a measurement chamber width of 100 mm. This paper presents the results of reference investigations on the A320 wing profile which combines experimental tests and CFD calculations. The obtained results show that the approach presented in the paper is appropriate and the obtained flow features in the tunnel do not differ much from the freestream conditions.
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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 (April 1, 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 of tunnel effects.
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BRUCE, P. J. K., D. M. F. BURTON, N. A. TITCHENER, and H. BABINSKY. "Corner effect and separation in transonic channel flows." Journal of Fluid Mechanics 679 (May 31, 2011): 247–62. http://dx.doi.org/10.1017/jfm.2011.135.

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An investigation into parameters affecting separation in normal shock wave/boundary layer interactions (SBLIs) has been conducted. It has been shown that the effective aspect ratio of an experimental facility (defined as δ*/tunnel width) is a critical factor in determining when shock-induced separation will occur. Experiments examining M∞ = 1.4 and 1.5 normal shock waves in a wind tunnel with a small rectangular cross-section have been performed and show that a link exists between the extent of shock-induced separation on the tunnel centre-line and the size of corner-flow separations. In tests where the corner-flows were modified ahead of the shock (through suction and vortex generators), the extent of separation around the tunnel centre-line was seen to vary significantly. These observations are attributed to the way corner flows modify the three-dimensional shock-structure and the impact this has on the magnitude of the adverse pressure gradient experienced by the tunnel wall boundary layers.
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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, but an estimate can be made of the dispersion of test results from various sources and of the probable "mean" values of the aerodynamic coefficients. To this end, comparable transonic test results for the AGARD-B model at Mach numbers 0.77, Mach 1.0 and Mach 1.17 from six wind tunnels were analyzed and average values and dispersions of the aerodynamic coefficients were computed.
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Phillips, Pamela S., and Edgar G. Waggoner. "Transonic wind-tunnel wall interference prediction code." Journal of Aircraft 27, no. 11 (November 1990): 915–16. http://dx.doi.org/10.2514/3.45959.

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Edwards, John W. "National Transonic Facility Model and Tunnel Vibrations." Journal of Aircraft 46, no. 1 (January 2009): 46–52. http://dx.doi.org/10.2514/1.30080.

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Dissertations / Theses on the topic "Transonic tunnel"

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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 temperature. Implementing thermodynamic and kinematic equations, new methods for expanding the measured velocity, density, and total temperature fluctuations to obtain additional fluctuations are investigated. The derived static pressure fluctuations are compared to the static pressure fluctuations obtained with a conventional fluctuating static pressure probe. The results of this comparison are good, which implies that the individual velocity, density, and total temperature components are time accurate. In the process of obtaining a high quality fluctuating flow field information, it was necessary to evaluate the calibration of the hot wire sensors. A direct calibration approach was compared to a conventional non-dimensional technique. These two calibration techniques should have resulted in the same hot wire sensitivities. There were significant differences in the hot wire sensitivities as obtained from the two approaches. The direct approach was determined to have less errors due to the added heat transfer information required of the indirect approach. Both calibration techniques demonstrated that the velocity and density sensitivities were in general not equal. This suggests that the velocity and density information cannot be combined to form a mass flow. A comparison of several hot wire techniques was included to highlight the errors obtained when assuming that these sensitivities are the same. An evaluation of the free stream flow quality associated with a Laminar Flow Control experiment was carried out in the Langley Research Center 8-Foot Transonic Pressure Tunnel (8' TPT). The facility was modified with turbulence manipulators and a liner that provided a flow field around a yawed super-critical airfoil that is conducive to transition research. These devices are evaluated to determine the sources of disturbances associated with the LFC experiment.
Ph. D.
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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 section. Data were also obtained in the unsteady wake shed from an airfoil oscillating at 5 Hz. The investigation revealed the presence of large stagnation pressure and temperature fluctuations in the settling chamber occurring at the blade passing frequency of the tunnel driving fan. The fluctuations in the test section are of a much more random nature and have amplitudes much lower than those in the test section. The overall results are consistent with previous tunnel disturbance measurements in the 0.3-m TCT. In the unsteady wake shed from the oscillating airfoil, stagnation temperature fluctuations as high as 42 K rms were observed. The high-frequency angle probe is a four sensor, pyramid type probe capable of simultaneously measuring time resolved stagnation and static pressures and two orthogonal flow angles. Using measurements from both probes, all flow parameters of interest can be deduced. Aerodynamic behavior of a full size model of the probe was established in an open air jet of known conditions.
M.S.
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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 aimed at extending the use of the two-dimensional Transonic Self-Streaming Wind Tunnel to the relief of wall interference effects on three-dimensional models. The compromise of using only two-wall single curvature movement avoids the problems that are inherent with the additional complexity of fully three-dimensional adaptive tunnels. A method of assessing the wall-induced interference velocity components from tunnel boundary pressure data, without reference to the model, has been developed and validated against other wall interference assessment methods. The algorithm, suitable for use in adaptive tunnels, is used with a wall movement influence coefficient method of wall contour prediction resulting in the apparent removal of wall interference effects along a streamlining target line. The residual wall interference velocity components calculated to be present after streamlining on two half-wing models are significantly lower than their straight test section values. Providing the model span is not too large in comparison with the breadth of the test section, the spanwise interference velocity component is negligible. A calibrated force-balance wing-body model has been used to demonstrate the first successful streamlining around a three-dimensional model in the Transonic Self-Streamlining Wind Tunnel. The measured model force data obtained with streamlined walls compares favourably with that derived using a standard post-test model data correction method.
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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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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 chamber to the test section. In the test section, the maximum rms value of the normalized fluctuating velocity is 0.7 percent. Correlation coefficients l failed to show vortlcity, entropy, or sound as the dominant mode of turbulence in the tunnel.

At certain tunnel operating conditions, periodic disturbances are seen in the data taken in the test section. A possible cause for the disturbances is found to be acoustic coupling of the test section and plenum chamber via the perforated side walls in the tunnel. The experimental data agree well with the acoustic coupling theory.


Master of Science
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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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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, and pitching moment coefficient predictions were compared for a range of lift production and Mach conditions to determine the uncertainty in the corrections process and the expected domain of applicability. Exploiting a previously designed statistical validation method, this effort accomplishes the extension of a calibration and validation for a boundary pressure wall interference corrections method. The foundational calibration and validation work was based on blockage interference only, while this present work extends the assessment of the method to encompass blockage and lift interference production. The validation method involves the establishment of independent cases that are then compared to rigorously determine the degree to which the correction method can converge free-air solutions for differing interference fields. The process involved first establishing an empty-tunnel calibration to gain both a centerline Mach profile of the facility at various ventilation settings, and to gain a baseline wall pressure signature undisturbed by a test article. The wall boundary condition parameters were then calibrated with a blockage and lift interference producing test article, and final corrected performance coefficients were compared for varying test section ventilated configurations to validate the corrections process and assess its domain of applicability. During the validation process discrimination between homogeneous and discrete implementations of the boundary condition was accomplished and final results indicated comparative strength in the discrete implementation's ability to capture experimental flow physics. Final results indicate that a discrete implementation of the General Slotted Wall boundary condition is effective in significantly reducing variations caused by differing interference fields. Corrections performed with the discrete implementation of the boundary condition collapse differing measurements of lift coefficient to within 0.0027, drag coefficient to within 0.0002, and pitching moment coefficient to within 0.0020.
Doctor of Philosophy
The purpose of conducting experimental tests in wind tunnels is often to acquire a quantitative measure of test article aerodynamic characteristics in such a way that those specific characteristics can be accurately translated into performance characteristics of the real vehicle that the test article intends to simulate. The difficulty in accurately simulating the real flow problem may not be readily apparent, but scientists and engineers have been working to improve this desired equivalence for the better part of the last half-century. The primary aspects of experimental aerodynamics simulation that present difficulty in attaining equivalence are: geometric fidelity, accurate scaling, and accounting for the presence of walls. The problem of scaling has been largely addressed by adequately matching conditions of similarity like compressibility (Mach number), and viscous effects (Reynolds number). However, accounting for the presence of walls in the experimental setup has presented ongoing challenges for ventilated boundaries; these challenges include difficulties in the correction process, but also extend into the determination of correction uncertainties. Exploiting a previously designed statistical validation method, this effort accomplishes the extension of a calibration and validation effort for a boundary pressure wall interference corrections method. The foundational calibration and validation work was based on blockage interference only, while this present work extends the assessment of the method to encompass blockage and lift interference production. The validation method involves the establishment of independent cases that are then compared to rigorously determine the degree to with the correction method can converge free-air solutions for differing interference scenarios. The process involved first establishing an empty-tunnel calibration to gain both a centerline Mach profile of the facility at various ventilation settings, and to gain a baseline wall pressure signature undisturbed by a test article. The wall boundary condition parameters were then calibrated with a blockage and lift interference producing test article, and final corrected performance coefficients were compared for varying test section ventilated configurations to validate the corrections process and assess its domain of applicability. During the validation process discrimination between homogeneous and discrete implementations of the boundary condition was accomplished and final results indicated comparative strength in the discrete implementation's ability to capture experimental flow physics. Final results indicate that a discrete implementation of the General Slotted Wall boundary condition is effective in significantly reducing variations caused by differing interference fields. Corrections performed with the discrete implementation of the boundary condition collapse differing measurements of lift coefficient to within 0.0027, drag coefficient to within 0.0002, and pitching moment coefficient to within 0.0020.
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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 compared with the subsonic data published to confirm this test procedure. For the angled slot, at the supersonic freestream Mach number, the current experiment shows that at the same x/Ms, the film cooling effectiveness increases by as much as 25% as compared to the subsonic case. The results of the experiment also show that at the same x/Ms, the film cooling effectiveness of the angled slot is considerably higher than that of the normal slot, at both subsonic and supersonic Mach numbers. The flow physics for the slot tests considered here are also described with computational fluid dynamic (CFD) simulations in the subsonic and supersonic regimes.
Master of Science
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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, multiple bodies were examined within the confines of their own specific flow regimes. These were: an inverted T026 wing in the low-to-medium subsonic regime, a lifting RAE 2822 aerofoil and ONERA M6 wing in the transonic regime, and a NATO military projectile at supersonic Mach numbers. Two primary aims were pursued. Firstly, experimental issues surrounding compressible ground effect flows were addressed. Potential problems were found in the practice of matching incompressible Computational Fluid Dynamics (CFD) simulations to wind tunnel experiments for the inverted wing at low freestream Mach numbers (<0.3), where the inverted wing was found to experience significant compressible effects even at Mach 0.15. The approach of matching full-scale CFD simulations to scale model testing at an identical Reynolds number but higher Mach number was analysed and found to be prone to significant error. An exploration was also conducted of appropriate ways to conduct experimental tests at transonic and supersonic Mach numbers, resulting in the recommendation of a symmetry (image) method as an effective means of approximating a moving ground boundary in a small-scale blowdown wind tunnel. Issues of scale with regards to Reynolds number persisted in the transonic regime, but with careful use of CFD as a complement to experiments, discrepancies were quantified with confidence. The second primary aim was to use CFD to gain a broader understanding of the ways in which density changes in the flowfield affect the aerodynamic performance of the bodies in question, in particular when a shock wave reflects from the ground plane to interact again with the body or its wake. The numerical approach was extensively verified and validated against existing and new experimental data. The lifting aerofoil and wing were investigated over a range of mid-to-high subsonic Mach numbers (1>M???>0.5), ground clearances and angles of incidence. The presence of the ground was found to affect the critical Mach number, and the aerodynamic characteristics of the bodies across all Mach numbers and clearances proved to be highly sensitive to ground proximity, with a step change in any variable often causing a considerable change to the lift, moment and drag coefficients. At the lowest ground clearances in both two and three dimensional studies, the aerodynamic efficiency was generally found to be less than that of unbounded (no ground) flight for shock-dominated flowfields at freestream Mach numbers greater than 0.7. In the fully-supersonic regime, where shocks tend to be steady and oblique, a supersonic spinning NATO projectile travelling at Mach 2.4 was simulated at several ground clearances. The shocks produced by the body reflected from the ground plane and interacted with the far wake, the near wake, and/or the body itself depending on the ground clearance. The influence of these wave reflections on the three-dimensional flowfield, and their resultant effects on the aerodynamic coefficients, was determined. The normal and drag forces acting on the projectile increased in exponential fashion once the reflections impinged on the projectile body again one or more times (at a height/diameter ground clearance h/d<1). The pitching moment of the projectile changed sign as ground clearance was reduced, adding to the complexity of the trajectory which would ensue.
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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 tunnel"

1

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

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

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

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

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

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Bruce, Robert A. A vapor generator for transonic flow visualization. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1989.

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Bruce, Robert A. A vapor generator for transonic flow visualization. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1989.

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

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

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

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Book chapters on the topic "Transonic tunnel"

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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, 115–27. Cham: 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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Bobbitt, Percy J., William D. Harvey, Charles D. Harris, and Cuyler W. Brooks. "The Langley 8-ft Transonic Pressure Tunnel Laminar-Flow-Control Experiment." In ICASE/NASA LaRC Series, 247–411. New York, NY: Springer New York, 1992. http://dx.doi.org/10.1007/978-1-4612-2872-1_8.

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Rasuo, Bosko. "On Boundary Layer Control in Two-Dimensional Transonic Wind Tunnel Testing." In Solid mechanics and its applications, 473–82. Dordrecht: Springer Netherlands, 2006. http://dx.doi.org/10.1007/978-1-4020-4150-1_46.

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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, 71–78. Boston, MA: Springer US, 1994. http://dx.doi.org/10.1007/978-1-4615-2522-6_8.

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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, 71–78. Dordrecht: Springer Netherlands, 2003. http://dx.doi.org/10.1007/978-94-010-0017-8_12.

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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, 417–27. Berlin, Heidelberg: 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, 475–82. Berlin, Heidelberg: 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, 525–32. Berlin, Heidelberg: 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, 97–113. Cham: 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, 103–10. Berlin, Heidelberg: Springer Berlin Heidelberg, 2002. http://dx.doi.org/10.1007/978-3-540-45466-3_13.

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Conference papers on the topic "Transonic tunnel"

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

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Helland, Stephen, and Courtney Henson. "Transonic Tunnel Comparison Test." In 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-402.

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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. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-452.

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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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Abstract:
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 variable porosity distribution as the third generation of porous wind tunnels. In order to improve knowledge about effects of the porosity distribution on the wall interference in subsonic/transonic conditions, an experimental investigation was carried out in the PT-1 CIRA transonic wind tunnel in the Mach range between 0.3 and 0.9 (over 400 test points were measured on different models and wall porosity configurations). At this aim, a dedicated experimental setup consisting in five plates positioned on the top and bottom walls of the PT-1 porous test section, has been designed and realized. Setting independently each plate, it is possible to obtain practically unlimited combinations of porosity distributions along the streamwise direction. The final purpose of the present activity was to evaluate the optimal porosity distribution able to minimize wind tunnel wall interferences in the considered Mach range. The huge number of factors (Mach number and the positions of the five plates setting the porosity distribution) made practically impossible to study the porosity distribution effects by using a traditional One Factor At a Time (OFAT) approach. Therefore, the optimum porosity distribution has been achieved through an experiment designed with a Modern Design of Experiment (MDOE) approach. Within the MDOE approach, the RSM (Response Surface Modeling) has been selected. The objective of the experiment, designed with the RSM approach, is to acquire a sufficient number of data to create one or more response surface models to be used to predict the response variable of interest (within a specified uncertainty) as function of the factors which can affect the selected response variables. The best porosity distribution able to improve the quality of wind tunnel data has been found for the PT-1 Wind Tunnel (but results and/or the procedure are applicable to all similar Wind Tunnels). In the present paper, to contextualize the activity, after a short summary of the historical wind tunnel development, the stat of art of the variable streamwise porosity distribution is discussed. Then, the experimental setup to simulate in wind tunnel several streamwise variable porosity distribution and the design of Experiment are described. Finally, the main experimental results are reported and critically analyzed.
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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. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-1716.

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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. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/6.2002-2782.

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Edwards, John, and John Edwards. "National Transonic Facility model and tunnel vibrations." In 35th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-345.

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Chung, K., J. Miau, and J. Yieh. "Initial operation of ASTRC/NCKU transonic wind tunnel." In 25th Plasmadynamics and Lasers Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1994. http://dx.doi.org/10.2514/6.1994-2515.

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

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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. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1998. http://dx.doi.org/10.2514/6.1998-2872.

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Reports on the topic "Transonic tunnel"

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

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Wong, J. K., G. N. Banks, and H. Whaley. Combustion evaluation of BP TRANSOIL emulsion in CCRL pilot-scale flame tunnel furnace. Natural Resources Canada/ESS/Scientific and Technical Publishing Services, 1989. http://dx.doi.org/10.4095/304426.

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