Relevant bibliographies by topics / Hypersonic wind tunnels

Contents

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

Academic literature on the topic 'Hypersonic wind tunnels'

Author: Grafiati
Published: 4 June 2021
Last updated: 6 September 2023

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Journal articles on the topic "Hypersonic wind tunnels"

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Stalker, R. J. "Modern developments in hypersonic wind tunnels." Aeronautical Journal 110, no. 1103 (January 2006): 21–39. http://dx.doi.org/10.1017/s0001924000004346.

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AbstractThe development of new methods of producing hypersonic wind-tunnel flows at increasing velocities during the last few decades is reviewed with attention to airbreathing propulsion, hypervelocity aerodynamics and superorbital aerodynamics. The role of chemical reactions in these flows leads to use of a binary scaling simulation parameter, which can be related to the Reynolds number, and which demands that smaller wind tunnels require higher reservoir pressure levels for simulation of flight phenomena. The use of combustion heated vitiated wind tunnels for propulsive research is discussed, as well as the use of reflected shock tunnels for the same purpose. A flight experiment validating shock-tunnel results is described, and relevant developments in shock tunnel instrumentation are outlined. The use of shock tunnels for hypervelocity testing is reviewed, noting the role of driver gas contamination in determining test time, and presenting examples of air dissociation effects on model flows. Extending the hypervelocity testing range into the superorbital regime with useful test times is seen to be possible by use of expansion tube/tunnels with a free piston driver.
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V. Gromyko, Yuriy, Anatoliy A. Maslov, Andrey A. Sidorenko, Pavel A. Polivanov, and Ivan S. Tsyryulnikov. "Estimation of the Flow Parametrs in Hypersonic Wind Tunnels." Siberian Journal of Physics 6, no. 2 (July 1, 2011): 10–16. http://dx.doi.org/10.54362/1818-7919-2011-6-2-10-16.

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The paper describes the algorithm of the flow parameters calculation for hypersonic wind tunnels taking into account the real gas properties using air and carbon dioxide as a working gas. The results of the experimental measurements of the flow velocity at the contoured nozzle exit in the hypersonic wind tunnel IT-302M have been carried out for verification of the algorithm
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Griffith, Wayland C., William J. Yanta, and William C. Ragsdale. "Supercooling in hypersonic nitrogen wind tunnels." Journal of Fluid Mechanics 269 (June 25, 1994): 283–99. http://dx.doi.org/10.1017/s0022112094001564.

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Recent experimental observation of supercooling in large hypersonic wind tunnels using pure nitrogen identified a broad range of non-equilibrium metastable vapour states of the flow in the test cell. To investigate this phenomenon a number of real-gas effects are analysed and compared with predictions made using the ideal-gas equation of state and equilibrium thermodynamics. The observed limit on the extent of supercooling is found to be at 60% of the temperature difference from the sublimation line to Gibbs’ absolute limit on phase stability. The mass fraction then condensing is calculated to be 12–14%. Included in the study are virial effects, quantization of rotational and vibrational energy, and the possible role of vibrational relaxation and freezing in supercooling. Results suggest that use of the supercooled region to enlarge the Mach–Reynolds number test envelope may be practical. Data from model tests in supercooled flows support this possibility.
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Kurshin, Anatolyi Petrovich. "HYPERSONIC WIND TUNNELS BASED ON PRESSURE MULTIPLIERS PART I, PRACTICAL REQUIREMENTS: SCHEMES OF HYPERSONIC WIND TUNNELS." TsAGI Science Journal 49, no. 5 (2018): 527–41. http://dx.doi.org/10.1615/tsagiscij.2018029206.

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Tegler, Eric. "The Race To Hypersonic Supremacy." Aerospace Testing International 2022, no. 3 (September 2022): 18–24. http://dx.doi.org/10.12968/s1478-2774(23)50300-8.

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McDaniel, R. D., and H. A. Hassan. "Transition Mechanisms in Conventional Hypersonic Wind Tunnels." Journal of Spacecraft and Rockets 38, no. 2 (March 2001): 180–84. http://dx.doi.org/10.2514/2.3691.

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Kurshin, Anatolyi Petrovich. "HYPERSONIC WIND TUNNELS BASED ON PRESSURE MULTIPLIERS, PART II: CAPABILITIES OF HYPERSONIC WIND TUNNELS BASED ON VARIOUS SCHEMES." TsAGI Science Journal 49, no. 6 (2018): 625–43. http://dx.doi.org/10.1615/tsagiscij.2018029457.

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Nagai, Shinji, Shoichi Tsuda, Tadao Koyama, Noriaki Hirabayashi, Hideo Sekine, and Koichi Hozumi. "Uncertainty of Aerodynamic Coefficients at Hypersonic Wind Tunnels." JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 51, no. 591 (2003): 151–57. http://dx.doi.org/10.2322/jjsass.51.151.

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Topchiyan, M. E., and A. M. Kharitonov. "Wind tunnels for hypersonic research (progress, problems, prospects)." Journal of Applied Mechanics and Technical Physics 35, no. 3 (May 1994): 383–95. http://dx.doi.org/10.1007/bf02369878.

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Duan, Lian, Meelan M. Choudhari, Amanda Chou, Federico Munoz, Rolf Radespiel, Thomas Schilden, Wolfgang Schröder, et al. "Characterization of Freestream Disturbances in Conventional Hypersonic Wind Tunnels." Journal of Spacecraft and Rockets 56, no. 2 (March 2019): 357–68. http://dx.doi.org/10.2514/1.a34290.

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Dissertations / Theses on the topic "Hypersonic wind tunnels"

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Ajmani, Kumud. "Turbulence modeling in hypersonic inlets." Thesis, Virginia Polytechnic Institute and State University, 1987. http://hdl.handle.net/10919/101365.

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A study is conducted to analyze the performance of different turbulence models when applied to flow through a Mach 7.4 hypersonic inlet. The analysis, which is two-dimensional, is done by comparing computational results from a Parabolized Navier Stokes code, with experimental data. The McDonald Camarata (MC) and Baldwin Lomax (BL) models were the two zero-equation models used in the study. The Turbulent Kinetic Energy (TKE) model was chosen as a representative higher order model. The MC model, when run with transition of flow, provides a solution which compares excellently with the data. Transition has a first order effect on the overall solution provided by the code. The BL model predicts separation of flow in the inlet, which contradicts experimental findings. The TKE model does not perform any better than the MC and BL models, despite the fact that it is a higher order turbulence model. The BL and TKE models predict transition in the inlet at a location which is much earlier than observed in the experiment. This may be attributed to the empirical constants used to determine the point of transition.
M.S.
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Goozee, Richard J. "Simulation of a complete shock tunnel using parallel computer codes /." St. Lucia, Qld, 2003. http://www.library.uq.edu.au/pdfserve.php?image=thesisabs/absthe17470.pdf.

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Tirtey, Sandy C. "Characterization of a transitional hypersonic boundary layer in wind tunnel and flight conditions." Doctoral thesis, Universite Libre de Bruxelles, 2009. http://hdl.handle.net/2013/ULB-DIPOT:oai:dipot.ulb.ac.be:2013/210367.

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Laminar turbulent transition is known for a long time as a critical phenomenon influencing the thermal load encountered by hypersonic vehicle during their planetary re-entry trajectory. Despite the efforts made by several research laboratories all over the world, the prediction of transition remains inaccurate, leading to oversized thermal protection system and dramatic limitations of hypersonic vehicles performances. One of the reasons explaining the difficulties encountered in predicting transition is the wide variety of parameters playing a role in the phenomenon. Among these parameters, surface roughness is known to play a major role and has been investigated in the present thesis.

A wide bibliographic review describing the main parameters affecting transition and their coupling is proposed. The most popular roughness-induced transition predictions correlations are presented, insisting on the lack of physics included in these methods and the difficulties encountered in performing ground hypersonic transition experiments representative of real flight characteristics. This bibliographic review shows the importance of a better understanding of the physical phenomenon and of a wider experimental database, including real flight data, for the development of accurate prediction methods.

Based on the above conclusions, a hypersonic experimental test campaign is realized for the characterization of the flow field structure in the vicinity and in the wake of 3D roughness elements. This fundamental flat plate study is associated with numerical simulations for supporting the interpretation of experimental results and thus a better understanding of transition physics. Finally, a model is proposed in agreement with the wind tunnel observations and the bibliographic survey.

The second principal axis of the present study is the development of a hypersonic in-flight roughness-induced transition experiment in the frame of the European EXPERT program. These flight data, together with various wind tunnel measurements are very important for the development of a wide experimental database supporting the elaboration of future transition prediction methods.
Doctorat en Sciences de l'ingénieur
info:eu-repo/semantics/nonPublished

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Grossir, Guillaume. "Longshot hypersonic wind tunnel flow characterization and boundary layer stability investigations." Doctoral thesis, Universite Libre de Bruxelles, 2015. http://hdl.handle.net/2013/ULB-DIPOT:oai:dipot.ulb.ac.be:2013/209044.

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The hypersonic laminar to turbulent transition problem above Mach 10 is addressed experimentally in the short duration VKI Longshot gun tunnel. Reentry conditions are partially duplicated in terms of Mach and Reynolds numbers. Pure nitrogen is used as a test gas with flow enthalpies sufficiently low to avoid its dissociation, thus approaching a perfect gas behavior. The stabilizing effects of Mach number and nosetip bluntness on the development of natural boundary layer disturbances are evaluated over a 7 degrees half-angle conical geometry without angle of attack.

Emphasis is initially placed on the flow characterization of the Longshot wind tunnel where these experiments are performed. Free-stream static pressure diagnostics are implemented in order to complete existing stagnation point pressure and heat flux measurements on a hemispherical probe. An alternative method used to determine accurate free-stream flow conditions is then derived following a rigorous theoretical approach coupled to the VKI Mutation thermo-chemical library. Resulting sensitivities of free-stream quantities to the experimental inputs are determined and the corresponding uncertainties are quantified and discussed. The benefits of this different approach are underlined, revealing the severe weaknesses of traditional methods based on the measurement of reservoir conditions and the following assumptions of an isentropic and adiabatic flow through the nozzle. The operational map of the Longshot wind tunnel is redefined accordingly. The practical limits associated with the onset of nitrogen flow condensation under non-equilibrium conditions are also accounted for.

Boundary layer transition experiments are then performed in this environment with free-stream Mach numbers ranging between 10-12. Instrumentation along the 800mm long conical model includes flush-mounted thermocouples and fast-response pressure sensors. Transition locations on sharp cones compare favorably with engineering correlations. A strong stabilizing effect of nosetip bluntness is reported and no transition reversal regime is observed for Re_RN<120000. Wavelet analysis of wall pressure traces denote the presence of inviscid instabilities belonging to Mack's second mode. An excellent agreement with Linear Stability Theory results is obtained from which the N-factor of the Longshot wind tunnel in these conditions is inferred. A novel Schlieren technique using a short duration laser light source is developed, allowing for high-quality flow visualization of the boundary layer disturbances. Comparisons of these measurement techniques between each other are finally reported, providing a detailed view of the transition process above Mach 10.
Doctorat en Sciences de l'ingénieur
info:eu-repo/semantics/nonPublished

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Edy, Jean-Luc. "Application de la photoluminescence pour la mesure des flux thermiques en soufflerie hypersonique à rafales." Valenciennes, 1995. https://ged.uphf.fr/nuxeo/site/esupversions/b8f44f3d-2475-494b-9670-b3b708b9c821.

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Une étude a été entreprise à la direction de l'aérodynamique de l'onera concernant l'application en soufflerie hypersonique d'une nouvelle méthode thermographique utilisant les propriétés de la photoluminescence. Après avoir étudie la faisabilité de la technique en mesure ponctuelle, il a été décidé de développer un système cartographique basé sur l'utilisation d'une camera video 3-ccd et d'un système de traitement d'images et de vérifier son adéquation aux mesures des transferts de chaleur pariétaux dans les souffleries hypersoniques à rafales. Le système a été étalonné en laboratoire, puis évalué dans le cadre d'essais dans les installations de l'onera à Chalais-Meudon. Il apparait que la thermographie par photoluminescence (tph) fournit des résultats satisfaisants sur des maquettes en matériau isolant thermiquement. Quant aux corps d'étude en matériau conducteur, la comparaison soit avec une évaluation théorique, soit avec données acquises au moyen de capteurs ponctuels montre que l'accord est moins bon. Cette méthode, avec la configuration expérimentale choisie, ne peut concurrencer directement la thermographie infrarouge. Elle est plutôt d'une technique complémentaire applicable quand la thermographie infrarouge ne peut être mise en œuvre
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Jeyaratnam, Jonathan Jehan. "On the low speed longitudinal stability of hypersonic waveriders." Thesis, The University of Sydney, 2020. https://hdl.handle.net/2123/22456.

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The development of hypersonic civilian transport aircraft requires solutions to a number of challenging problems in the areas of aerothermodynamics, control, aeroelasticity, propulsion and others encountered at high Mach number flight. The desire for good aerodynamic performance at high Mach numbers results in slender vehicle designs called waveriders. The stability and handling of waverider shapes at the low speeds at the take-off and landing phases of flight is not well studied. This thesis covers static and dynamic CFD simulations of the Hexafly-Int glider which have been used to obtain longitudinal stability derivatives at low speeds. Complementary static and free-to-pitch dynamic wind tunnel testing, are used to validate the CFD computations. A final chapter on the optimisation of waverider designs including low speed longitudinal stability is presented to show the impacts of this additional requirement on the hypersonic design space. The static wind tunnel testing has identified stability issues relating to the location of the centre of gravity. The design centre of gravity which is suitable for the Hexafly-Int vehicle at Mach 7.2 is found to be too far aft which results in instability at low speeds. In addition, the dynamic testing in the wind tunnel shows that the pitch damping is inadequate at low speeds. The CFD simulations agree well with the wind tunnel test results validating the use of CFD tools for determining dynamic stability derivatives of this class of slender vehicle in the design process. To alleviate the low speed stability issue of hypersonic vehicles, a waverider shape optimisation study has been carried out to understand what shapes will produce better low speed stability behaviour. These shapes are found to produce lower aerodynamic efficiency at high speeds which suggests that a design compromise between low speed stability and high speed performance is required at the outset of hypersonic waverider design.
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Bensassi, Khalil. "Contribution to the Numerical Modeling of the VKI Longshot Hypersonic Wind Tunnel." Doctoral thesis, Universite Libre de Bruxelles, 2014. http://hdl.handle.net/2013/ULB-DIPOT:oai:dipot.ulb.ac.be:2013/229727.

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The numerical modelling of the VKI-Longshot facility remains a challeng-ing task as it requires multi-physical numerical methods in order to simulate all the components. In the current dissertation, numerical tools were developed in order to study each component of the facility separately and a deep investigations of each stage of the shot were performed. This helped to better understand the different processes involved in the flow development inside this hypersonic wind tunnel. However the numerical computation of different regions of the facility treated as independent from each others remains an approximation at best.The accuracy of the rebuilding code for determining the free stream conditions and the total enthalpy in the VKI-Longshot facility was investigated by using a series of unsteady numerical computations of axisymmetric hypersonic flow over a heat flux probe. Good agreement was obtained between the numerical results and the measured data for both the stagnation pressure and the heat flux dur- ing the useful test time.The driver-driven part of the Longshot facility was modelled using the quasi one-dimensional Lagrangian solver L1d2. The three main conditions used for the experiments —low, medium and high Reynolds number —were considered.The chambrage effect due to the junction between the driver and the driven tubes in the VKI-Longshot facility was investigated. The computation showed great ben- efit of the chambrage in increasing the speed of the piston and thus the final compression ratio of the test gas.Two dimensional simulations of the flow in the driver and the driven tube were performed using Arbitrary Lagrangian Eulerian (ALE) solver in COOLFLuiD. A parallel multi-domain strategy was developed in order to integrate the moving piston within the computational domain.The computed pressure in the reservoir is compared to the one provided by the experiment and good agreement was obtained for both con- editions.Finally, an attempt was made to compute the starting process of the flow in the contoured nozzle. The transient computation of the flow showed how the primary shock initiates the flow in the nozzle before reaching the exit plan at time of 1.5 [ms] after the diaphragm rupture. The complex interactions of the reflected shocks in the throat raise the temperature above 9500 [K] which was not expected. Chemical dissociation of Nitrogen was not taken into account during this transient investigation which may play a key role considering the range of temperature reached near the throat.
Doctorat en Sciences de l'ingénieur
info:eu-repo/semantics/nonPublished
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Bykerk, Tamas. "Low Speed Aerodynamics, Performance and Handling Qualities of a Hypersonic Waverider." Thesis, University of Sydney, 2020. https://hdl.handle.net/2123/23111.

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Interest in the development of high speed commercial aircraft capable of travelling in excess of Mach 5 is on the increase. This is mainly driven by the potential of these vehicles to significantly reduce long haul flight times, connecting antipodal city pairs such as Brussels and Sydney in less than three hours. The hypersonic waverider concept has received particular attention because of its ability to achieve comparatively high aerodynamic efficiency at hypersonic cruise, as the body shock is contained by the wing leading edges. As research into the extreme conditions at high Mach numbers takes priority, no full subsonic handling quality analysis of a waverider has ever been completed, nor has an understanding of the mechanisms behind both static and dynamic stability been developed. This gap in literature is addressed by this thesis, which presents a combination of results from computational fluid dynamics simulations and wind tunnel experiments, completing the first full subsonic handling quality analysis of a waverider.
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Comstock, Robert. "Hypersonic Heat Transfer Load Analysis in STAR-CCM+." DigitalCommons@CalPoly, 2020. https://digitalcommons.calpoly.edu/theses/2226.

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This thesis investigates the capabilities of STAR-CCM+, a Computational Fluid Dynamics (CFD) software owned by Siemens, in predicting hypersonic heat transfer loads on forward-facing surfaces. Results show that STAR-CCM+ predicted peak heat transfer loads within +/- 20% of experimental data on the leading edge of a delta wing design from the X-20 Dyna-Soar program with 73o of sweep. Steady-state laminar simulations were run as replications of wind tunnel tests documented in NASA CR-535, a NASA technical report that measured and studied the hypersonic pressure and heat transfer loads on preliminary X- 20 wing designs across a wide range of Reynolds numbers and Mach numbers in different wind tunnel and shock tunnel facilities. One of the Mach 8.08 test cases that was run at NASA Arnold Engineering Development Center Wind Tunnel B was selected as the case of comparison for this thesis, which was designated as test AD462M-1 in the original report. The CFD simulations assumed an ideal gas in laminar flow with temperature-dependent viscosity, thermal conductivity, and isobaric specific heat across an angle of attack range from 0o to 30o. A separate CFD study of heat transfer loads of a hemisphere-cylinder at Mach 6.74 was used as a simpler and less computationally-expensive validation case compared against wind tunnel data from NASA Langley Research Center to help select the appropriate CFD solver and mesh settings for this thesis. For the hemisphere-cylinder, the heat transfer load at the stagnation point was overpredicted in STAR-CCM+ by 21.8%. Peak heat transfer loads on the delta wing leading edge were all within +/- 20% of the wind tunnel data, which was published for angles of attack between 15o to 30o. A more adverse heat transfer gradient along the leading edge of the delta wing was also observed in the direction from the front of the wing to the outer wing tip when compared to wind tunnel data. The pressure loads on the delta wing leading edge in CFD were within +/-10% of wind tunnel measurements.
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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 "Hypersonic wind tunnels"

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Jacobi, L. Y. I.A.I. hypersonic wind tunnel. Ben Gurion Airport, Israel: Israel Aircraft Industries Ltd, 1987.

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Lederer, Melissa A. Condensation in hypersonic nitrogen wind tunnels. Washington: American Institute of Aeronautics and Astronautics, 1990.

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Lee, J. Lawrence. Into the wind: The wind tunnels of NASA and its predecessors. Washington, DC: National Aeronautics and Space Administration, Office of Communications, History Program Office, 2012.

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Lu, Frank K. Survey of short duration, hypersonic and hypervelocity facilities. Washington, D. C: American Institute of Aeronautics and Astronautics, 1994.

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Norris, R. B. The flying wind tunnel. New York: AIAA, 1989.

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K, Lu Frank, and Marren Dan E, eds. Advanced hypersonic test facilities. Reston, Va: American Institute of Aeronautics and Astronautics, 2002.

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Midden, Raymond E. Description and calibration of the Langley hypersonic CF: A facility for simulating low ©. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1987.

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Midden, Raymond E. Description and calibration of the Langley hypersonic CF: A facility for simulating low. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1987.

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F, Akyurtlu Ates, and United States. National Aeronautics and Space Administration., eds. Evaluation of candidate working fluid formulations for the electrothermal-chemical wind tunnel: Final report for NAG-1-767. [Hampton, Va.]: Hampton University, Dept. of Engineering, 1993.

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Haas, Jeffrey E. Reactivation study for NASA Lewis Research Center's Hypersonic Tunnel Facility. [Washington, DC: National Aeronautics and Space Administration, 1987.

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Book chapters on the topic "Hypersonic wind tunnels"

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Chanetz, Bruno, Jean Délery, Patrick Gilliéron, Patrick Gnemmi, Erwin R. Gowree, and Philippe Perrier. "Hypersonic Wind Tunnels." In Springer Tracts in Mechanical Engineering, 135–64. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-35562-3_6.

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Stetson, Kenneth F. "Hypersonic Transition Testing in Wind Tunnels." In Advances in Soil Science, 91–100. New York, NY: Springer New York, 1990. http://dx.doi.org/10.1007/978-1-4612-3430-2_13.

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Gundlach, G., and C. Dankert. "Nonintrusive Temperature Determination by LIF in Hypersonic Wind Tunnels." In New Trends in Instrumentation for Hypersonic Research, 255–64. Dordrecht: Springer Netherlands, 1993. http://dx.doi.org/10.1007/978-94-011-1828-6_23.

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Chazot, Olivier, and Francesco Panerai. "High-Enthalpy Facilities and Plasma Wind Tunnels for Aerothermodynamics Ground Testing." In Hypersonic Nonequilibrium Flows: Fundamentals and Recent Advances, 329–42. Reston, VA: American Institute of Aeronautics and Astronautics, Inc., 2015. http://dx.doi.org/10.2514/5.9781624103292.0329.0342.

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

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Chazot, Olivier. "Aerospace Flight Modeling and Experimental Testing." In Uncertainty in Engineering, 131–47. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-83640-5_9.

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AbstractValidation processes for aerospace flight modeling require to articulate uncertainty quantification methods with the experimental approach. On this note, the specific strategies for the reproduction of re-entry flow conditions in ground-based facilities are reviewed. It shows how it combines high-speed flow physics with the hypersonic wind tunnel capabilities.
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Miller, Charles G., and W. L. Wells. "Wind-Tunnel Based Definition of the AFE Aerothermodynamic Environment." In Advances in Hypersonics, 109–81. Boston, MA: Birkhäuser Boston, 1992. http://dx.doi.org/10.1007/978-1-4612-0379-7_4.

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Spekreijse, S. P. "Nonequilibrium Flow in a Hypersonic Wind Tunnel Nozzle." In Hypersonic Flows for Reentry Problems, 1159–73. Berlin, Heidelberg: Springer Berlin Heidelberg, 1991. http://dx.doi.org/10.1007/978-3-642-76527-8_76.

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Barbé, S., D. Boscher, J. Deschamps, G. Gauffre, and A. Girard. "Infrared Thermography for Hot-Shot Wind Tunnel." In New Trends in Instrumentation for Hypersonic Research, 513–16. Dordrecht: Springer Netherlands, 1993. http://dx.doi.org/10.1007/978-94-011-1828-6_46.

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Sleziona, P. C., M. Auweter-Kurtz, B. Glocker, T. Gogel, T. Gölz, E. Messerschmid, and H. O. Schrade. "Non-equilibrium Flow in an Arc Heated Wind Tunnel." In Hypersonic Flows for Reentry Problems, 1116–30. Berlin, Heidelberg: Springer Berlin Heidelberg, 1991. http://dx.doi.org/10.1007/978-3-642-76527-8_73.

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Conference papers on the topic "Hypersonic wind tunnels"

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LEDERER, MELISSA, SUSAN HUDSON, WAYLAND GRIFFITH, WILLIAM YANTA, and WILLIAM RAGSDALE. "Condensation in hypersonic nitrogen wind tunnels." In 16th Aerodynamic Ground Testing Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-1392.

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Tirres, Carlos. "The future of hypersonic wind tunnels." In 37th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-819.

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Dicks, John B. "The Use of MHD in Hypersonic Wind Tunnels." In 22nd Intersociety Energy Conversion Engineering Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-9298.

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Duan, Lian, Meelan M. Choudhari, Amanda Chou, Federico Munoz, S. R. C. Ail, Rolf Radespiel, Thomas Schilden, et al. "Characterization of Freestream Disturbances in Conventional Hypersonic Wind Tunnels." In 2018 AIAA Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-0347.

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Kennell, Chris, Andrew J. Neely, Sean B. O'Byrne, and David Buttsworth. "Measurement of Vehicle Stability Coefficients in Hypersonic Wind Tunnels." In 20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-3690.

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Nguyen, Nhat, Mathew Ruda, Luca Massa, Colin Adams, and Joseph Schetz. "High Frequency, Multidimensional Heat Flux Reconstruction in Hypersonic Wind Tunnels." In AIAA AVIATION 2020 FORUM. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2020. http://dx.doi.org/10.2514/6.2020-3292.

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Nagai, Shinji, Shoichi Tsuda, Tadao Koyama, Noriaki Hirabayashi, and Hideo Sekine. "Comparison of winged vehicle force data at large hypersonic wind tunnels." In 39th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-166.

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BECKWITH, I., F. J. CHEN, and M. MALIK. "Design and fabrication requirements for low-noise supersonic/hypersonic wind tunnels." In 26th Aerospace Sciences Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-143.

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Shimura, Takashi, Noboru Sakuranaka, Muneo Izumikawa, and Tohru Mitani. "Load oscillations due to unstart of engines and hypersonic wind tunnels." In 32nd Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1996. http://dx.doi.org/10.2514/6.1996-3242.

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Buck, Gregory. "Simultaneous global pressure and temperature measurement technique for hypersonic wind tunnels." In 21st Aerodynamic Measurement Technology and Ground Testing Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-2649.

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Reports on the topic "Hypersonic wind tunnels"

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Grossir, Guillaume. On the design of quiet hypersonic wind tunnels. Von Karman Institute for Fluid Dynamics, December 2020. http://dx.doi.org/10.35294/tm57.

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This document presents a thorough literature review on the development of hypersonic quiet tunnels. The concept of boundary layer transition in high-speed flows is presented first. Its consequences on the free-stream turbulence levels in ground facilities are reviewed next, demonstrating that running boundary layers along the nozzle walls must remain laminar for quiet operation. The design key points that enable laminar boundary layers and hypersonic operation with low free-stream noise levels are then identified and discussed. The few quiet facilities currently operating through the world are also presented, along with their design characteristics and performances. The expected characteristics and performances of a European quiet tunnel are also discussed, along with flow characterization methodologies and different measurement techniques. It is finally shown that the required expertise to establish the first European quiet hypersonic wind tunnel is mostly at hand.
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Schneider, Steven P. Towards High-Reynolds-Number Quiet Flow in Hypersonic Wind Tunnels. Fort Belvoir, VA: Defense Technical Information Center, April 2009. http://dx.doi.org/10.21236/ada500049.

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Duan, Lian, Meelan M. Choudhari, Amanda Chou, Federic Munoz, Rolf Radespiel, Thomas Schilden, Wolfgang Schroder, et al. Chapter 15 - Characterization of Freestream Disturbances in Conventional Hypersonic Wind Tunnels. Office of Scientific and Technical Information (OSTI), July 2018. http://dx.doi.org/10.2172/1530152.

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North, Simon W., Andrea G. Hsu, and Jonathan H. Frank. Application of advanced laser diagnostics to hypersonic wind tunnels and combustion systems. Office of Scientific and Technical Information (OSTI), September 2009. http://dx.doi.org/10.2172/993892.

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

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Miles, Richard B., and Garry L. Brown. Radiatively Driven Hypersonic Wind Tunnel. Fort Belvoir, VA: Defense Technical Information Center, May 2002. http://dx.doi.org/10.21236/ada403037.

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Simmons, Gloyd A. Radiatively Driven Hypersonic Wind Tunnel (RDHWT) Program Magnetohydrodynamic Accelerator Research Into Advanced Hypersonics (MARIAH II). Fort Belvoir, VA: Defense Technical Information Center, January 2000. http://dx.doi.org/10.21236/ada397435.

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Schneider, Larry X. Building 865 Hypersonic Wind Tunnel Power System Analysis. Office of Scientific and Technical Information (OSTI), February 2015. http://dx.doi.org/10.2172/1259561.

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Lipinski, R. J., and R. P. Kensek. Conceptual design for an electron-beam heated hypersonic wind tunnel. Office of Scientific and Technical Information (OSTI), July 1997. http://dx.doi.org/10.2172/522724.

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Elhadj, S. Materials response under hypersonic flow conditions probed by multi-modal diagnostics in a benchtop wind tunnel. Office of Scientific and Technical Information (OSTI), September 2020. http://dx.doi.org/10.2172/1669239.

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