Relevant bibliographies by topics / Hypersonic boundary-layer transition

Academic literature on the topic 'Hypersonic boundary-layer transition'

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Published: 10 December 2022
Last updated: 28 January 2023

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Journal articles on the topic "Hypersonic boundary-layer transition"

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Berry, Scott A., Thomas J. Horvath, Brian R. Hollis, Rick A. Thompson, and H. Harris Hamilton. "X-33 Hypersonic Boundary-Layer Transition." Journal of Spacecraft and Rockets 38, no. 5 (September 2001): 646–57. http://dx.doi.org/10.2514/2.3750.

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MATSUYAMA, Shingo. "DNS of Hypersonic Boundary Layer Transition." Journal of the Visualization Society of Japan 41, no. 162 (2021): 13–14. http://dx.doi.org/10.3154/jvs.41.162_13.

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Zhao, Yatian, Zhiyuan Shao, and Hongkang Liu. "Aerodisk Effect on Hypersonic Boundary Layer Transition and Heat Transfer of HIFiRE-5 Vehicle." Aerospace 9, no. 12 (November 23, 2022): 742. http://dx.doi.org/10.3390/aerospace9120742.

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The substantial aerodynamic drag and severe aerothermal loads, which are closely related to boundary layer transition, challenge the design of hypersonic vehicles and could be relieved by active methods aimed at drag and heat flux reduction, such as aerodisk. However, the research of aerodisk effects on transitional flows is still not abundant. Based on the improved k-ω-γ transition model, this study investigates the influence of the aerodisk with various lengths on hypersonic boundary layer transition and surface heat flux distribution over HIFiRE-5 configuration under various angles of attack. Certain meaningful analysis and results are obtained: (i) The existence of aerodisk is found to directly trigger separation-induced transition, moving the transition onset near the centerline upstream and widening the transition region; (ii) The maximum wall heat flux could be effectively reduced by aerodisk up to 52.1% and the maximum surface pressure can even be reduced up to 80.4%. The transition shapes are identical, while the variety of growth rates of intermittency are non-monotonous with the increase in aerodisk length. The dilation of region with high heat flux boundary layer is regarded as an inevitable compromise to reducing maximum heat flux and maximum surface pressure. (iii) With the angle of attack rising, first, the transition is postponed and subsequently advanced on the windward surface, which is in contrast to the continuously extending transition region on the leeward surface. This numerical study aims to explore the effects of aerodisk on hypersonic boundary layer transition, enrich the study of hypersonic flow field characteristics and active thermal protection system considering realistic boundary layer transition, and provide references for the excogitation and utilization of hypersonic vehicle aerodisk.
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Kimmel, Roger L. "Introduction: Roughness and Hypersonic Boundary-Layer Transition." Journal of Spacecraft and Rockets 45, no. 6 (November 2008): 1089. http://dx.doi.org/10.2514/1.41332.

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Kuntz, David W., and Donald L. Potter. "Boundary-Layer Transition and Hypersonic Flight Testing." Journal of Spacecraft and Rockets 45, no. 2 (March 2008): 184–92. http://dx.doi.org/10.2514/1.29708.

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TONG, FuLin, JianQiang CHEN, GuoHua TU, GuoLiang XU, JiuFen CHEN, BingBing WAN, XianXu YUAN, and YiFeng ZHANG. "Recent progresses on hypersonic boundary-layer transition." SCIENTIA SINICA Physica, Mechanica & Astronomica 49, no. 11 (May 1, 2019): 114701. http://dx.doi.org/10.1360/sspma-2019-0071.

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Patrick, Chris. "Total temperature affects hypersonic boundary layer transition." Scilight 2019, no. 47 (November 22, 2019): 471107. http://dx.doi.org/10.1063/10.0000281.

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Dong, Hao, Shicheng Liu, Xi Geng, and Keming Cheng. "Study on Oil-Film Interferometry Measurement Technique of Hypersonic Boundary Layer Transition." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 36, no. 6 (December 2018): 1156–61. http://dx.doi.org/10.1051/jnwpu/20183661156.

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Prediction of boundary layer transition is important for the design of hypersonic aircrafts. The study of boundary layer transition of hypersonic flow around a flat plate using oil-film interferometry was investigated at Φ500mm traditional hypersonic wind tunnel. In order to measure the skin friction fast and precisely on the hypersonic wind tunnel, the traditional oil-film interferometry technique is improved. A high-speed camera is used to capture the images of fringes and the viscosity of the silicon oil is modified according to the wall temperature measured by thermocouples during the test. The skin frictions of smooth surface and the surface with single square roughness element were measured. For the smooth surface, the boundary layer is laminar. However, the boundary layer transition is promoted by wake vortices induced by the roughness element. Both the results of skin friction with and without the roughness element are in good agreement with the simulation results correspondingly, indicating high accuracy of the oil film interferometry technique.
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Liu, Meikuan, Guilai Han, Zongxian Li, and Zonglin Jiang. "Experimental study on the effects of the cone nose-tip bluntness." Physics of Fluids 34, no. 10 (October 2022): 101703. http://dx.doi.org/10.1063/5.0110928.

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In this Letter, hypersonic boundary-layer transition was investigated on a large-scale cone with a height of 3 m and a half-cone angle of 7° at a zero angle of attack in the JF-12 hypersonic flight duplicate shock tunnel. For the same freestream unit Reynolds number, with the increase in the bluntness Reynolds number, the transition Reynolds number has a trend of first increasing and then decreasing, showing a “transition reversal” phenomenon. As the bluntness increased, the high/low-frequency instability waves in the boundary-layer were modulated, which caused the boundary-layer transition to be delayed and then advanced.
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Lee, Cunbiao, and Shiyi Chen. "Recent progress in the study of transition in the hypersonic boundary layer." National Science Review 6, no. 1 (May 7, 2018): 155–70. http://dx.doi.org/10.1093/nsr/nwy052.

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Abstract Turbulence is a universal form of fluid motion. It is the key issue in fluid mechanics. Very recently, it has become a bottleneck in some key engineering research of national importance, such as aeronautics, astronautics and navigation. Developed turbulence and the onset of turbulence, i.e. transition, are two interrelated parts of turbulence. The hypersonic boundary-layer transition is a strategic focus in the fluid mechanics community. This article reviews recent developments in the study of the hypersonic boundary-layer transition, research facilities and experimental techniques. The hypersonic quiet wind tunnel is introduced as a necessary device to obtain real flight data in near space. Near-wall measurement techniques, such as temperature-sensitive paint, near-wall particle image velocimetry and Rayleigh-scattering visualization, are shown. The most important issues in the recent development of the transition in the hypersonic boundary layer are addressed. The instability and nonlinear interaction of different instability modes are discussed. The recent contributions from China, especially at Peking University, are also introduced.
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Dissertations / Theses on the topic "Hypersonic boundary-layer transition"

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Atcliffe, Phillip Arthur. "Effects of boundary layer separation and transition at hypersonic speeds." Thesis, Cranfield University, 1995. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.336458.

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Riley, Zachary Bryce Riley. "Interaction Between Aerothermally Compliant Structures and Boundary-Layer Transition in Hypersonic Flow." The Ohio State University, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=osu1471618528.

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Husmeier, Frank. "Numerical Investigations of Transition in Hypersonic Flows over Circular Cones." Diss., The University of Arizona, 2008. http://hdl.handle.net/10150/196123.

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This thesis focuses on secondary instability mechanisms of high-speed boundary layers over cones with a circular cross section. Hypersonic transition investigations at Mach 8 are performed using Direct Numerical Simulations (DNS). At wind-tunnel conditions, these simulations allow for comparison with experimental measurements to verify fundamental stability characteristics.To better understand geometrical influences, flat-plate and cylindrical geometries are studied using after-shock conditions of the conical investigations. This allows for a direct comparison with the results of the sharp cone to evaluate the influence of the spanwise curvature and the cone opening angle. The ratio of the boundary-layer thickness to the spanwise radius is used to determine the importance of spanwise curvature effects. When advancing in the downstream direction the radius increaseslinearly while the boundary-layer thickness stays almost constant. Hence, spanwise curvature effects are strongest close to the nose and decrease in downstream direction. Their influences on the secondary instability mechanisms provide some rudimentary guidance in the design of future high-speed air vehicles.In experiments, blunting of the nose tip of the circular cone results in an increase in critical Reynolds number (c.f. Stetson et al. (1984)). However, once a certain threshold of the nose radius is exceeded, the critical Reynolds number decreases even to lower values than for the sharp cone. So far, conclusive explanations for this behavior could not be derived based on the available experimental data. Therefore, here DNS is used to study the effect of nose bluntness on secondary instability mechanisms in order to shed light on the underlying flow physics. To this end, three different nose tip radii are considered-the sharp cone, a small nose radius and a large nose radius. A small nose radius moves the transition on-set downstream, while for a large nose radius the so-called transition reversal is observed. Experimentalists hold influences of the entropy layer responsible but detailed numerical studies may lead to alternateconclusions.
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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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Laible, Andreas Christian. "Numerical Investigation of Boundary-Layer Transition for Cones at Mach 3.5 and 6.0." Diss., The University of Arizona, 2011. http://hdl.handle.net/10150/205419.

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Transition in high-speed boundary layers is investigated using direct numerical simulation (DNS). A compressible Navier-Stokes code that is specifically tailored towards accurate and efficient simulations of boundary layer stability and boundary layer transition was developed and thoroughly validated. Particular emphasis was put into the adoption of a high-order accurate spatial discretization including a boundary closure with the same stencil width as the interior scheme. Oblique breakdown has been shown, using both temporal and spatial DNS, to be a viable route to transition for the boundary layer of the sharp 7° cone at Mach 3.5 investigated by Corke 2002. A 'wedge-shaped' transitional regime was observed to be characteristic for this type of breakdown on the cone geometry. Furthermore, it was shown that the dominance of the longitudinal mode in the nonlinear transition regime of oblique breakdown is due to a continuously nonlinear forced transient growth. That is the primary pair of oblique waves permanently 'seeds' disturbances into the longitudinal mode, where these disturbances exhibit non-modal unstable behavior. In addition to the simulations of controlled transition via oblique breakdown, six simulations have been conducted and analyzed where transition is initiated by multiple primary waves. Despite the broader spectrum of primary waves, typical features of oblique breakdown are still apparent in these simulations and therefore, it may be conjectured, that oblique breakdown initiated by one primary pair of waves is a good model for the nonlinear processes in natural transition. Furthermore, hypersonic boundary layer stability and transition for a flared and a straight cone at Mach 6 was investigated. In particular, a comparative investigation between both geometries regarding the K-type breakdown was performed in order to give some indications towards the open question how strong the nonlinear transition processis altered by the cone flare.
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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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Sivasubramanian, Jayahar. "Numerical Investigation of Laminar-Turbulent Transition in a Cone Boundary Layer at Mach 6." Diss., The University of Arizona, 2012. http://hdl.handle.net/10150/228514.

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Direct Numerical Simulations (DNS) are performed to investigate laminar-turbulent transition in a boundary layer on a sharp cone at Mach 6. The main objective of this dissertation research is to explore which nonlinear breakdown mechanisms may be dominant in a broad--band "natural" disturbance environment and then use this knowledge to perform controlled transition simulations to investigate these mechanisms in great detail. Towards this end, a "natural" transition scenario was modeled and investigated by generating wave packet disturbances. The evolution of a three-dimensional wave packet in a boundary layer has typically been used as an idealized model for "natural" transition to turbulence, since it represents the impulse response of the boundary layer and, thus, includes the interactions between all frequencies and wave numbers. These wave packet simulations provided strong evidence for a possible presence of fundamental and subharmonic resonance mechanisms in the nonlinear transition regime. However, the fundamental resonance was much stronger than the subharmonic. In addition to these two resonance mechanisms, the wave packet simulations also indicated the possible presence of oblique breakdown mechanism. To gain more insight into the nonlinear mechanisms, controlled transition simulations were performed of these mechanisms. Several small and medium scale simulations were performed to scan the parameter space for fundamental and subharmonic resonance. These simulations confirmed the findings of the wave packet simulations, namely that, fundamental resonance is much stronger compared to the subharmonic resonance. Subsequently a set of highly resolved fundamental and oblique breakdown simulations were performed. In these DNS, remarkable streamwise arranged "hot'' streaks were observed for both fundamental and oblique breakdown. The streaks were a consequence of the large amplitude steady longitudinal vortex modes in the nonlinear régime. These simulations demonstrated that both second--mode fundamental breakdown and oblique breakdown may indeed be viable paths to complete breakdown to turbulence in hypersonic boundary layers at Mach 6.
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Yentsch, Robert J. "Three-Dimensional Shock-Boundary Layer Interactions in Simulations of HIFiRE-1 and HIFiRE-2." The Ohio State University, 2013. http://rave.ohiolink.edu/etdc/view?acc_num=osu1384195671.

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Padilla, Montero Ivan. "Analysis of the stability of a flat-plate high-speed boundary layer with discrete roughness." Doctoral thesis, Universite Libre de Bruxelles, 2021. https://dipot.ulb.ac.be/dspace/bitstream/2013/324490/5/contratPM.pdf.

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Boundary-layer transition from a laminar to a turbulent regime is a critical driver in the design of high-speed vehicles. The aerothermodynamic loads associated with transitional or fully turbulent hypersonic boundary layers are several times higher than those associated with laminar flow. The presence of isolated roughness elements on the surface of a body can accelerate the growth of incoming disturbances and introduce additional instability mechanisms in the flow field, eventually leading to a premature occurrence of transition. This dissertation studies the instabilities induced by three-dimensional discrete roughness elements located inside a high-speed boundary layer developing on a flat plate. Two-dimensional local linear stability theory (2D-LST) is employed to identify the instabilities evolving in the three-dimensional flow field that characterizes the wake induced by the roughness elements and to investigate their evolution downstream. A formulation of the disturbance energy evolution equation available for base flows depending on a single spatial direction is generalized for the first time to base flows featuring two inhomogeneous directions and perturbations depending on three spatial directions. This generalization allows to obtain a decomposition of the temporal growth rate of 2D-LST instabilities into the different contributions that lead to the production and dissipation of the total disturbance energy. This novel extension of the formulation provides an additional layer of information for understanding the energy exchange mechanisms between a three-dimensional base flow and the perturbations resulting from 2D-LST. Stability computations for a calorically perfect gas illustrate that the wake induced by the roughness elements supports the growth of different sinuous and varicose instabilities which coexist together with the Mack-mode perturbations that evolve in the flat-plate boundary layer, and which become modulated by the roughness-element wake. A single pair of sinuous and varicose disturbances is found to dominate the wake instability in the vicinity of the obstacles. The application of the newly developed decomposition of the temporal growth rate reveals that the roughness-induced wake modes extract most of their potential energy from the transport of entropy fluctuations across the base-flow temperature gradients and most of their kinetic energy from the work of the disturbance Reynolds stresses against the base-flow velocity gradients. Further downstream, the growth rate of the wake instabilities is found to be influenced by the presence of Mack-mode disturbances developing on the flat plate. Strong evidence is observed of a continuous synchronization mechanism between the wake instabilities and the Mack-mode perturbations. This phenomenon leads to an enhancement of the amplification rate of the wake modes far downstream of the roughness element, ultimately increasing the associated integrated amplification factors for some of the investigated conditions. The effects of vibrational molecular excitation and chemical non-equilibrium on the instabilities induced by a roughness element are studied for the case of a high-temperature boundary layer developing on a sharp wedge configuration. For this purpose, a 2D-LST solver for chemical non-equilibrium flows is developed for the first time, featuring a fully consistent implementation of the thermal and transport models employed for the base flow and the perturbation fields. This is achieved thanks to the automatic derivation and implementation tool (ADIT) available within the von Karman Institute extensible stability and transition analysis (VESTA) tool-kit, which enables an automatic derivation and implementation of the 2D-LST governing equations for different thermodynamic flow assumptions and models. The stability computations for this configuration show that sinuous and varicose disturbances also dominate the wake instability in the presence of vibrational molecular energy mode excitation and chemical reactions. The resulting base-flow cooling associated with the modeling of such high-temperature phenomena is found to have opposite stabilizing and destabilizing effects on the streamwise evolution of the sinuous and varicose instabilities. The modeling of vibrational excitation and chemical non-equilibrium acting exclusively on the perturbations is found to have a stabilizing influence in all cases.
Doctorat en Sciences de l'ingénieur et technologie
info:eu-repo/semantics/nonPublished
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Di, Giovanni Antonio [Verfasser], Christian [Akademischer Betreuer] Stemmer, Wolfgang [Gutachter] Schröder, and Christian [Gutachter] Stemmer. "Roughness-Induced Transition in a Hypersonic Capsule Boundary Layer under Wind-Tunnel and Reentry Conditions / Antonio Di Giovanni ; Gutachter: Wolfgang Schröder, Christian Stemmer ; Betreuer: Christian Stemmer." München : Universitätsbibliothek der TU München, 2020. http://d-nb.info/1211725227/34.

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Books on the topic "Hypersonic boundary-layer transition"

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Wendt, Volker. Experimentelle Untersuchung der Instabilitat von ebenen und konischen laminaren Hyperschallgrenzschichten. Koln, Germany: DLR, 1993.

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Richards, W. Lance. Finite-element analysis of a Mach-8 flight test article using nonlinear contact elements. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1997.

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Three-Dimensional Hypersonic Boundary Layer Stability and Transition. Storming Media, 1997.

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A, Thompson R., and United States. National Aeronautics and Space Administration., eds. Hypersonic boundary-layer transition for X-33 phase II vehicle. Reston, Va: American Institute of Aeronautics and Astronautics, 1998.

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A, Thompson R., and United States. National Aeronautics and Space Administration., eds. Hypersonic boundary-layer transition for X-33 phase II vehicle. Reston, Va: American Institute of Aeronautics and Astronautics, 1998.

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A, Thompson R., and United States. National Aeronautics and Space Administration., eds. Hypersonic boundary-layer transition for X-33 phase II vehicle. Reston, Va: American Institute of Aeronautics and Astronautics, 1998.

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A, Thompson R., and United States. National Aeronautics and Space Administration., eds. Hypersonic boundary-layer transition for X-33 phase II vehicle. Reston, Va: American Institute of Aeronautics and Astronautics, 1998.

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Thermal analysis of a metallic wing glove for a Mach-8 boundary-layer experiment. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1998.

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Thermal analysis of a metallic wing glove for a Mach-8 boundary-layer experiment. Edwards, Calif: National Aeronautics and Space Administration, Dryden Flight Research Center, 1998.

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A quiet tunnel investigation of hypersonic boundary-layer stability over a cooled, flared cone: Final report. Norfolk, Va: Dept. of Mechanical Engineering, College of Engineering & Technology, Old Dominion University, 1996.

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Book chapters on the topic "Hypersonic boundary-layer transition"

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Stetson, Kenneth F. "Hypersonic Boundary-Layer Transition." In Advances in Hypersonics, 324–417. Boston, MA: Birkhäuser Boston, 1992. http://dx.doi.org/10.1007/978-1-4612-0379-7_7.

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Malik, M. R. "Hypersonic Boundary-Layer Receptivity and Stability." In Laminar-Turbulent Transition, 409–14. Berlin, Heidelberg: Springer Berlin Heidelberg, 2000. http://dx.doi.org/10.1007/978-3-662-03997-7_61.

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Maslov, A. A., T. Poplavskaya, and D. A. Bountin. "Hypersonic boundary layer transition and control." In Seventh IUTAM Symposium on Laminar-Turbulent Transition, 19–26. Dordrecht: Springer Netherlands, 2009. http://dx.doi.org/10.1007/978-90-481-3723-7_3.

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Maslov, A. A., and S. G. Mironov. "Experimental Investigations of the Hypersonic Boundary Layer Stability." In Laminar-Turbulent Transition, 421–26. Berlin, Heidelberg: Springer Berlin Heidelberg, 2000. http://dx.doi.org/10.1007/978-3-662-03997-7_63.

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Fu, S., and L. Wang. "Modeling Flow Transition in Hypersonic Boundary Layer." In New Trends in Fluid Mechanics Research, 53–56. Berlin, Heidelberg: Springer Berlin Heidelberg, 2007. http://dx.doi.org/10.1007/978-3-540-75995-9_9.

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Morozov, S. O., S. V. Lukashevich, and A. N. Shiplyuk. "Hypersonic Boundary Layer Instability and Control by Passive Porous Coatings." In IUTAM Laminar-Turbulent Transition, 613–19. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-67902-6_53.

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Sidharth, G. S., A. Dwivedi, J. W. Nichols, M. Jovanović, and G. V. Candler. "Global Linear Stability and Sensitivity of Hypersonic Shock-Boundary Layer Interactions." In IUTAM Laminar-Turbulent Transition, 489–98. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-67902-6_42.

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Groskopf, Gordon, and Markus J. Kloker. "Effects of an Oblique Roughness on Hypersonic Boundary-Layer Transition." In High Performance Computing in Science and Engineering ‘12, 255–76. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-33374-3_20.

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Yu, Min, Wu-bing Yang, and Xiang-jiang Yuan. "Numerical Study of Görtler Vortices on Hypersonic Boundary-Layer Transition." In Lecture Notes in Electrical Engineering, 416–22. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-3305-7_33.

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Xie, S. F., F. Ji, D. Yao, and Q. Shen. "Experimental Study of Hypersonic Shock Wave/Transition Boundary Layer Interaction." In 31st International Symposium on Shock Waves 1, 1015–24. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-319-91020-8_122.

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Conference papers on the topic "Hypersonic boundary-layer transition"

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Berry, Scott, Thomas Horvath, Brian Hollis, H. Hamilton, II, and Richard Thompson. "X-33 hypersonic boundary layer transition." In 33rd Thermophysics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-3560.

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MALIK, M., T. ZANG, and D. BUSHNELL. "Boundary layer transition in hypersonic flows." In 2nd International Aerospace Planes Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-5232.

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Kuntz, David, and Donald Potter. "Boundary Layer Transition and Hypersonic Flight Testing." In 45th AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-308.

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Kimmel, Roger. "Aspects of Hypersonic Boundary Layer Transition Control." In 41st Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-772.

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Shrestha, Prakash, Joseph W. Nichols, Mihailo R. Jovanovic, and Graham V. Candler. "Study of Trip-Induced Hypersonic Boundary Layer Transition." In 47th AIAA Fluid Dynamics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-4513.

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Schneider, Steven. "Effects of Roughness on Hypersonic Boundary-Layer Transition." In 45th AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-305.

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Johnson, Heath, and Graham Candler. "PSE analysis of reacting hypersonic boundary layer transition." In 30th Fluid Dynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-3793.

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Schneider, Steven. "Hypersonic Boundary-Layer Transition with Ablation and Blowing." In 38th Fluid Dynamics Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2008. http://dx.doi.org/10.2514/6.2008-3730.

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Berry, Scott, Roger Kimmel, and Eli Reshotko. "Recommendations for Hypersonic Boundary Layer Transition Flight Testing." In 41st AIAA Fluid Dynamics Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-3415.

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Riley, Zachary, Rohit Deshmukh, Brent A. Miller, and Jack J. McNamara. "Characterization of Structural Response to Hypersonic Boundary Layer Transition." In 56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2015. http://dx.doi.org/10.2514/6.2015-0688.

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Reports on the topic "Hypersonic boundary-layer transition"

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Stetson, Kenneth F. Comments on Hypersonic Boundary-Layer Transition. Fort Belvoir, VA: Defense Technical Information Center, September 1990. http://dx.doi.org/10.21236/ada227242.

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Kimmel, Roger L., and J. Poggie. Three-Dimensional Hypersonic Boundary Layer Stability and Transition. Fort Belvoir, VA: Defense Technical Information Center, December 1997. http://dx.doi.org/10.21236/ada417303.

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Maslov, Anatoly A. Experimental Study of Stability and Transition of Hypersonic Boundary Layer Around Blunted Cone. Fort Belvoir, VA: Defense Technical Information Center, December 2001. http://dx.doi.org/10.21236/ada408241.

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Schneider, Steven P. Hypersonic Boundary-Layer Transition Research in the Boeing/AFOSR Mach-6 Quiet Tunnel. Fort Belvoir, VA: Defense Technical Information Center, March 2006. http://dx.doi.org/10.21236/ada448081.

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Zhong, Xiaolin. Numerical Simulation of Hypersonic Boundary Layer Receptivity, Transient Growth and Transition With Surface Roughness. Fort Belvoir, VA: Defense Technical Information Center, December 2009. http://dx.doi.org/10.21236/ada517055.

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Aeschliman, D. P., R. H. Croll, and D. W. Kuntz. Use of shear-stress-sensitive, temperature-insensitive liquid crystals for hypersonic boundary-layer transition detection. Office of Scientific and Technical Information (OSTI), April 1997. http://dx.doi.org/10.2172/469193.

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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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Abstract:
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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Kimmel, Roger, David Adamczak, Ryan Gosse, Karen Berger, and Shann Rufer. Ground Test and Computation of Boundary Layer Transition on the Hypersonic International Flight Research and Experimentation (HIFiRE)-5 Vehicle. Fort Belvoir, VA: Defense Technical Information Center, February 2011. http://dx.doi.org/10.21236/ada548272.

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Stetson, Kenneth F. Hypersonic Laminar Boundary Layer Transition. Part 1. Nosetip Bluntness Effects on Cone Frustum Transition. Part 2. Mach 6 Experiments of Transition on a Cone at Angle of Attack. Fort Belvoir, VA: Defense Technical Information Center, December 1986. http://dx.doi.org/10.21236/ada178877.

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