Relevant bibliographies by topics / Hypersonic boundary layer

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
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Academic literature on the topic 'Hypersonic boundary layer'

Author: Grafiati
Published: 4 June 2021
Last updated: 6 February 2022

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Journal articles on the topic "Hypersonic boundary layer"

1

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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Shi, Mingfang, Lidan Xu, Zhenqing Wang, and Hongqing Lv. "Effect of a Roughness Element on the Hypersonic Boundary Layer Receptivity Due to Different Types of Free-Stream Disturbance with a Single Frequency." Entropy 21, no. 3 (March 6, 2019): 255. http://dx.doi.org/10.3390/e21030255.

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The hypersonic flow field around a blunt cone was simulated using a high-order finite difference method. Fast acoustic waves, slow acoustic waves, entropy waves, and vortical waves were introduced into the free-stream to determine the influence of a free-stream with disturbances on the hypersonic flow field and boundary layer. The effect of disturbance type on the evolution of perturbations in the hypersonic boundary layer was analyzed. Fast Fourier Transform was adopted to analyze the effect of the disturbance type on the evolution of different modes in the boundary layer. A roughness element was introduced into the flow field to reveal the impact of the roughness element on hypersonic boundary layer receptivity. The results showed that a free-stream with disturbances affected the hypersonic flow field and boundary layer; acoustic waves had the greatest influence. The impact of slow acoustic waves on the flow field was mainly concentrated in the region between the shock and the boundary layer, whereas the influence of fast acoustic waves was mainly concentrated in the boundary layer. Multi-mode perturbations formed in the boundary layer were caused by the free-stream with disturbances, wherein the fundamental mode was the dominant mode of the perturbations in the boundary layer caused by fast acoustic waves, entropy waves, and vortical waves. The dominant modes of the perturbations in the boundary layer caused by slow acoustic waves were both the fundamental mode and the second harmonic mode. The roughness element changed the propagation process of different modes of perturbations in the boundary layer. In the downstream region of the roughness element, perturbations in the boundary layer caused by the slow acoustic waves had the greatest influence. The second harmonic mode in the boundary layer was significantly suppressed, and the fundamental mode became the dominant mode. The effects of fast acoustic waves and entropy waves on the boundary layer receptivity were similar, except the amplitude of the perturbations in the boundary layer caused by the fast acoustic waves was larger.
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Fan, Y., J. Chang, W. Bao, and D. Yu. "Effects of boundary-layer bleeding on unstart oscillatory flow of hypersonic inlets." Aeronautical Journal 114, no. 1157 (July 2010): 445–50. http://dx.doi.org/10.1017/s0001924000003924.

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Abstract The unsteady flowfield of a series of mixed-compression hypersonic inlets with different bleeding rates were numerically simulated. Firstly unstart oscillatory flow of hypersonic inlets caused by downstream massflow choking was discussed. Then the effects of boundary layer bleeding on the averaged performance parameter of hypersonic inlets, and on the dominant amplitude and frequency of unstart oscillatory flow of hypersonic inlets were presented. The reasons why the boundary-layer bleeding can suppress unstart oscillatory flow of hypersonic inlets were analysed. In conclusion, the averaged performance parameter of hypersonic inlets during a big buzz is improved greatly, and the dominant frequency of unstart oscillatory flow of hypersonic inlets is reduced in contrast with no bleeding, and all these are benefit to the design and operation of hypersonic inlets.
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Chang, J., D. Yu, W. Bao, Y. Fan, and Y. Shen. "Effects of boundary-layers bleeding on unstart/restart characteristics of hypersonic inlets." Aeronautical Journal 113, no. 1143 (May 2009): 319–27. http://dx.doi.org/10.1017/s0001924000002992.

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Abstract A series of mixed-compression hypersonic inlets at different bleeding rates were simulated at different freestream conditions in this paper. The unstart/restart characteristics of hypersonic inlets were analysed and the reasons why the unstart/restart phenomenon is in existence is presented. The unstart/restart characteristics of hypersonic inlets at different bleeding rates were given. The effects of boundary-layer bleeding on the performance parameter (mass-captured coefficient, total-pressure recovery coefficient), starting and restarting Mach number of hypersonic inlets were discussed. In conclusion, boundary-layer bleeding can improve the performance parameter of hypersonic inlets, and can reduce the starting and restarting Mach number, and can broad the operation range of the hypersonic inlet.
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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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Moghadam, Ramin Kamali, and Seyed Amir Hosseini. "Assessment of Real Gas Effects on Approximate and Boundary Layer Equations for Hypersonic Laminar Flow over Axisymmetric Bodies." Advanced Materials Research 1016 (August 2014): 534–39. http://dx.doi.org/10.4028/www.scientific.net/amr.1016.534.

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Two efficient computational procedures based on the boundary layer equations and approximate relations areassessedin prediction of the laminar hypersonic flowfield for both the perfect gas and equilibrium air around the axisymmetric blunt body configurations. For the boundary layer procedure, the boundary layer equationsutilize the integral matrix solution algorithm for the blunt nose and after body region by using a space marching technique. The integral matrix procedure able us to create accurate and smooth results using the minimum grid in the boundary layer and minimize the computational costs. Applying the approximate method creates a robust and efficient code for heating calculations over the blunt bodies which flies in hypersonic regimes. These algorithms are highly appropriate to design of hypersonic reentry vehicles. The effects of real gas on the flowfield characteristics are also studied in two procedures.
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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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Ruban, Alex, Viren Menezes, and Sridhar Balasubramanian. "Boundary-Layer Control for Effective Hypersonic Intake." Journal of Propulsion and Power 34, no. 6 (November 2018): 1612–14. http://dx.doi.org/10.2514/1.b37066.

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Craig, Stuart A., and William S. Saric. "Crossflow instability in a hypersonic boundary layer." Journal of Fluid Mechanics 808 (October 27, 2016): 224–44. http://dx.doi.org/10.1017/jfm.2016.643.

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The crossflow instability in a hypersonic, laminar boundary layer is investigated using point measurements inside the boundary layer for the first time. Experiments are performed on a 7° right, circular cone with an adiabatic wall condition at 5.6° angle of incidence in the low-disturbance Mach 6 Quiet Tunnel at Texas A&M University. Measurements are made with a constant-temperature hot-wire anemometer system with a frequency response up to 180 kHz. Stationary crossflow waves are observed to grow and saturate. A travelling wave coexists with the stationary wave and occurs in a frequency band centred around 35 kHz. A type-I secondary instability is also observed in a frequency band centred around 110 kHz. The behaviour of all three modes is largely consistent with their low-speed counterparts prior to saturation of the stationary wave. Afterward, the behaviour remains in partial agreement with the low-speed case. Neither type-II secondary instability nor transition to turbulence are observed in this study.
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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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Dissertations / Theses on the topic "Hypersonic boundary layer"

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Williams, Simon. "Three-dimensional separation of a hypersonic boundary layer." Thesis, Imperial College London, 2005. http://hdl.handle.net/10044/1/11450.

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Wang, Xiaowen. "Numerical simulations of hypersonic boundary-layer stability and receptivity." Diss., Restricted to subscribing institutions, 2007. http://proquest.umi.com/pqdweb?did=1464122601&sid=1&Fmt=2&clientId=1564&RQT=309&VName=PQD.

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Manning, Melissa Lynn. "COMPUTATIONAL EVALUATION OF QUIET TUNNEL HYPERSONIC BOUNDARY LAYER STABILITY EXPERIMENTS." NCSU, 2001. http://www.lib.ncsu.edu/theses/available/etd-20010112-081130.

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Manning, Melissa Lynn. Computational Evaluation of Quiet Tunnel Hypersonic Boundary Layer Stability Experiments. (Under the direction of Dr. Ndaona Chokani.) A computational evaluation of two stability experiments conducted in the NASA Langley Mach 6 axisymmetric quiet nozzle test chamber facility is conducted. Navier-Stokes analysis of the mean flow and linear stability theory analysis of boundary layer disturbances is performed in the computations. The effects of adverse pressure gradient and wall cooling are examined. Calculated pressure, temperature and boundary layer thickness distributions show very good overall agreement with experimental measurements. Computed mass flux and total temperature profiles show very good quantitative agreement with uncalibrated hot-wire measurements obtained with the hot-wire operated in high and low overheat modes respectively. Comparisons between calibrated hot-wire data and mean flow computations show excellent agreement in the early stages of the transitional flow. However, examination of the wire Reynolds number and mass flux and total temperature eigenfunction profiles suggest that when operated in high overheat mode the sensitivity of the hot-wire to total temperature is significant. Thus, while uncalibrated hot-wire measurements are useful to characterize the overall features of the flow, calibrated hot-wire measurements are necessary for quantitative comparison with stability theory. Computations show that adverse pressure gradient and wall cooling decrease the boundary layer thickness and increase the frequency and amplification rate of the unstable second mode disturbances; these findings are consistent with the experimental observations.

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Surah, Davinder. "Investigation of attachment line boundary layer characteristics in hypersonic flows." Thesis, Cranfield University, 2000. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.323921.

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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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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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Bura, Romie Oktovianus. "Laminar/transitional shock-wave/boundary-layer interactions (SWBLIs) in hypersonic flows." Thesis, University of Southampton, 2004. https://eprints.soton.ac.uk/47605/.

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Numerical investigations of laminar shock-wave/boundary-layer interactions (SWBLIs) in hypersonic flow have been carried out at M∞ = 6.85 and M∞ ≈ 8, with unit Reynolds numbers ranging from 2.0 x 106 m- l to 7.60 x 106 m- l. This thesis deals with a simplified 2-D geometric configuration to simulate SWBLIs on vehicle surfaces or engine intakes, i.e. the interaction of an oblique shock (produced by a wedge) impinging on an incoming laminar boundary-layer on an isothermal flat plate. The numerical simulations were performed with weak/moderate to strong shock. The results were compared with available theoretical and experimental results. Limited experimental work at M∞ = 6.85 for obtaining qualitative data were performed to provide the location of separation and re-attachment points using surface oil flow. Schlieren photographs were taken to provide the general flow features. A comprehensive analysis was performed on the 2-D numerical results with various Mach numbers, Reynolds numbers and shock strengths, to verify whether numerical solutions were able to confirm the established trends for the laminar free-interaction concept. An analysis was also performed using a well-established power-law relationship of pressure and heat flux in the region of interactions. An unstable first oblique mode disturbance was imposed with the strongest wedge angle, 9°, at M∞ = 6.85 and unit Reynolds number 2.45 x 106 m- l to determine the boundary-layer stability and its propensity to undergo transition in the linear regime. Several unsteady 3-D simulations were performed with varied parameters. Streamwise vortices were generated in all cases especially downstream of maximum separation bubble height. However, as the amplifications of the disturbance were quite small, transition was found to be unlikely at these conditions
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Murray, Neil Paul. "Three-dimensional turbulent shock-wave : boundary-layer interactions in hypersonic flows." Thesis, Imperial College London, 2007. http://hdl.handle.net/10044/1/7963.

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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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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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Books on the topic "Hypersonic boundary layer"

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Marvin, J. G. Turbulence modeling for hypersonic flows. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1989.

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Goldstein, M. F. Spatial evolution of nonlinear acoustic mode instabilities on hypersonic boundary layers. [Washington, DC]: National Aeronautics and Space Administration, 1990.

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Townend, L. H. Intakes and boundary layer crossflows for hypersonic vehicles. New York: American Institute of Aeronautics and Astronautics, 1991.

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Wilmoth, Richard G. Interference effects on the hypersonic, rarefied flow about a flat plate. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1989.

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

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Hamed, A. Flow separation in shock wave boundary layer interactions at hypersonic speeds. Washington, D.C: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

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Moraes, Augusto C. M. Compressible laminar boundary layers for perfect and real gases in equilibrium at Mach numbers to 30. Washington, D. C: American Institute of Aeronautics and Astronautics, 1992.

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Fu, Yibin B. Crossflow effects on the growth rate of inviscid Gortler vortices in a hypersonic boundary layer. Hampton Va: Institute for Computer Applications in Science and Engineering, 1992.

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Lee, Jong-Hun. Hypersonic three-dimensional nonequilibrium boundary-layer equations in generalized curvilinear coordinates. [Washington, DC]: National Aeronautics and Space Administration, 1993.

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Lee, Jong-Hun. Hypersonic three-dimensional nonequilibrium boundary-layer equations in generalized curvilinear coordinates. [Washington, DC]: National Aeronautics and Space Administration, 1993.

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Book chapters on the topic "Hypersonic boundary layer"

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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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Stemmer, Christian, and Nikolaus A. Adams. "Supersonic and Hypersonic Boundary-Layer Flows." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 77–91. Berlin, Heidelberg: Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-642-00262-5_4.

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Schulte, D., A. Henckels, and I. Schell. "Boundary Layer Bleed in Hypersonic Inlets." In Notes on Numerical Fluid Mechanics (NNFM), 296–303. Wiesbaden: Vieweg+Teubner Verlag, 1997. http://dx.doi.org/10.1007/978-3-322-86573-1_38.

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Ren, Jie. "Stabilization of the Hypersonic Boundary Layer." In Secondary Instabilities of Görtler Vortices in High-Speed Boundary Layers, 73–86. Singapore: Springer Singapore, 2017. http://dx.doi.org/10.1007/978-981-10-6832-4_5.

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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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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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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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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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Monnoyer, F. "Cases VI.1 and VI.8: ELLIPSOID Eüler-boundary layer calculation." In Hypersonic Flows for Reentry Problems, 647–63. Berlin, Heidelberg: Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-642-77922-0_54.

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Monnoyer, F. "Case VII.4: Blunt nose delta wing Euler-boundary layer calculation." In Hypersonic Flows for Reentry Problems, 902–17. Berlin, Heidelberg: Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-642-77922-0_69.

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Conference papers on the topic "Hypersonic boundary layer"

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STETSON, KENNETH, and ROGER KIMMEL. "On hypersonic boundary-layer stability." In 30th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-737.

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SETTLES, G., and L. DODSON. "Hypersonic shock/boundary-layer interaction database." In 22nd Fluid Dynamics, Plasma Dynamics and Lasers Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1991. http://dx.doi.org/10.2514/6.1991-1763.

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KIM, S., and G. HARLOFF. "Hypersonic turbulent wall boundary layer computations." In 24th Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-2829.

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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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Baumgardner, M., A. Smits, T. Nau, and C. Rowley. "A new hypersonic boundary layer facility." In 33rd Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-787.

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NAGAMATSU, H., and R. SHEER, JR. "Critical layer concept relative to hypersonic boundary layer stability." In 23rd Aerospace Sciences Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1985. http://dx.doi.org/10.2514/6.1985-303.

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Hamed, A., and Ajay Kumar. "Hypersonic Flow Separation in Shock Wave Boundary Layer Interactions." In ASME 1992 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1992. http://dx.doi.org/10.1115/92-gt-205.

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This work presents an assessment of the experimental data on separated flow in shock wave turbulent boundary layer interactions at hypersonic and supersonic speeds. The data base consist of selected configurations where the only characteristic length in the interation is the incoming boundary layer thickness. It consists of two dimensional and axisymmetric interactions in compression corners or cylinder-flares, and externally generated oblique shock interactions with boundary layers over flat plates or cylindrical surfaces. The conditions leading to flow separation and the empirical correlations for incipient separation are reviewed. The effects of Mach number, Reynolds number, surface cooling and the methods of detecting separation are discussed.
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Chokani, N., and J. Norris. "Nonlinear interactions in a hypersonic boundary layer." In 40th AIAA Aerospace Sciences Meeting & Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/6.2002-154.

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Berry, Scott, Robert Nowak, and Thomas Horvath. "Boundary Layer Control for Hypersonic Airbreathing Vehicles." In 34th AIAA Fluid Dynamics Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-2246.

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Reports on the topic "Hypersonic boundary layer"

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Reed, Helen L. Stability of Hypersonic Boundary-Layer Flows. Fort Belvoir, VA: Defense Technical Information Center, September 1997. http://dx.doi.org/10.21236/ada329724.

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2

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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3

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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4

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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Knight, Doyle. Assessment of CFD Modeling Capability for Hypersonic Shock Wave Boundary Layer Interactions. Fort Belvoir, VA: Defense Technical Information Center, November 2015. http://dx.doi.org/10.21236/ada627597.

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6

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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7

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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8

Wagnild, Ross Martin, Neal Bitter, Jeffrey A. Fike, and Micah Howard. Direct Numerical Simulation of Hypersonic Turbulent Boundary Layer Flow using SPARC: Initial Evaluation. Office of Scientific and Technical Information (OSTI), September 2019. http://dx.doi.org/10.2172/1569350.

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9

Zhong, Xiaolin. Direct Numerical Simulation and Experimental Validation of Hypersonic Boundary-Layer Receptivity and Instability. Fort Belvoir, VA: Defense Technical Information Center, March 2007. http://dx.doi.org/10.21236/ada467163.

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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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