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

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Author: Grafiati

Published: 10 December 2022

Last updated: 28 January 2023

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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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2

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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3

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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4

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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5

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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6

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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7

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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8

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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9

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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10

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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11

Chokani, Ndaona. "VITA measurements of transition in transitional hypersonic boundary layer flows." Experiments in Fluids 38, no. 4 (February 25, 2005): 440–48. http://dx.doi.org/10.1007/s00348-004-0923-y.

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12

Wartemann, Viola, Alexander Wagner, Ross Wagnild, Fabio Pinna, Fernando Miró Miró, Hideyuki Tanno, and Heath Johnson. "High-Enthalpy Effects on Hypersonic Boundary-Layer Transition." Journal of Spacecraft and Rockets 56, no. 2 (March 2019): 347–56. http://dx.doi.org/10.2514/1.a34281.

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13

Schneider, Steven P. "Hypersonic Boundary-Layer Transition with Ablation and Blowing." Journal of Spacecraft and Rockets 47, no. 2 (March 2010): 225–37. http://dx.doi.org/10.2514/1.43926.

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14

Schneider, Steven P. "Effects of Roughness on Hypersonic Boundary-Layer Transition." Journal of Spacecraft and Rockets 45, no. 2 (March 2008): 193–209. http://dx.doi.org/10.2514/1.29713.

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15

Tirtey, S. C., O. Chazot, and L. Walpot. "Characterization of hypersonic roughness-induced boundary-layer transition." Experiments in Fluids 50, no. 2 (August 1, 2010): 407–18. http://dx.doi.org/10.1007/s00348-010-0939-4.

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16

Zhang, Chuan-Hong, Qing Tang, and Cun-Biao Lee. "Hypersonic boundary-layer transition on a flared cone." Acta Mechanica Sinica 29, no. 1 (February 2013): 48–54. http://dx.doi.org/10.1007/s10409-013-0009-2.

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17

Yao, Yu Feng. "Scramjet Flow and Intake SBLI: Technical Challenges and Case Study." Applied Mechanics and Materials 315 (April 2013): 344–48. http://dx.doi.org/10.4028/www.scientific.net/amm.315.344.

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This paper reviews some basic research areas associated with Scramjet-powered hypersonic flying vehicle, particularly the forebody boundary-layer transition and intake shock-wave boundary-layer interactions (SBLI). Some technical and physical challenges in aerodynamics, aero-thermodynamics, aero-design are visited with focuses being placed on hypersonic boundary-layer transition process and its underlying physical mechanics, feasible physics-based engineering transition prediction methods, and physics-based modelling of shock-shock, shock-wave/boundary-layer interactions of Scramjet flows. Experimental, analytical and numerical studies of previously relevant studies have also been summarized with a total of twelve transition/intake configurations that can be used as benchmarks for validating physical model development and numerical simulation tools. A case study of Scramjet intake SBLI has been carried out by using computational fluid dynamics approach to understand shock induced flow separation and its consequent influences on combustion performance, along with research perspectives discussed accordingly.

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18

Qiao, Lei, Jun-Qiang Bai, Jia-Kuan Xu, Jing-Lei Xu, and Yang Zhang. "Modeling of Supersonic/Hypersonic Boundary Layer Transition Using a Single-Point Approach." International Journal of Nonlinear Sciences and Numerical Simulation 19, no. 3-4 (June 26, 2018): 263–74. http://dx.doi.org/10.1515/ijnsns-2017-0011.

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AbstractDuring the process of aerodynamic shape design of supersonic and hypersonic space planes, laminar flow design and boundary layer transition prediction play important roles in aero-thermal numerical simulations and aero-thermal protection design. Therefore, in this study, a computational fluid dynamics compatible transition closure model for high speed laminar-to-turbulent transitional flows is formulated with consideration of the analysis results from stability theory. The proposed model contains two transport equations to describe the transition mechanism using local variables. Specifically, the eddy viscosity of laminar fluctuations and intermittency factor are chosen to be the characteristic parameters and modeled by transport equations. Accounting for the dominant instability modes at supersonic/hypersonic conditions, the first- and second- modes are modeled using local variables through the analysis of laminar self-similar boundary layers. Then, the present transition model is applied with compressibility corrected $k$-$\omega$ shear stress transport turbulence model. Thus, as the main significance of the current work, the present model is enabled to capture the overshoot phenomena as well as predict the transition onset position. Finally, comparisons between the predictions using the present model and the wind tunnel experimental results of several well-documented flow cases are provided to validate the proposed transition turbulence model.

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19

Stilla, J. "Engineering transition prediction for a hypersonic axisymmetric boundary layer." Journal of Aircraft 31, no. 6 (November 1994): 1358–64. http://dx.doi.org/10.2514/3.46659.

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20

Guo, Peixu, Zhenxun Gao, Zhichao Zhang, Chongwen Jiang, and Chun-Hian Lee. "Local-Variable-Based Model for Hypersonic Boundary Layer Transition." AIAA Journal 57, no. 6 (June 2019): 2372–83. http://dx.doi.org/10.2514/1.j056828.

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21

Miró Miró, Fernando, Pieter Dehairs, Fabio Pinna, Maria Gkolia, Davide Masutti, Tamas Regert, and Olivier Chazot. "Effect of Wall Blowing on Hypersonic Boundary-Layer Transition." AIAA Journal 57, no. 4 (April 2019): 1567–78. http://dx.doi.org/10.2514/1.j057604.

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22

Tu, Guohua, Jianqiang Chen, Xianxu Yuan, Qingtao Yang, Maochang Duan, Qiang Yang, Yi Duan, Xi Chen, Bingbing Wan, and Xinghao Xiang. "Progress in flight tests of hypersonic boundary layer transition." Acta Mechanica Sinica 37, no. 11 (November 2021): 1589–609. http://dx.doi.org/10.1007/s10409-021-01153-4.

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23

Riley, Zachary B., Rohit Deshmukh, Brent A. Miller, Jack J. McNamara, and Katya M. Casper. "Characterization of Structural Response to Hypersonic Boundary-Layer Transition." AIAA Journal 54, no. 8 (August 2016): 2418–31. http://dx.doi.org/10.2514/1.j054607.

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24

Murakami, Akira, Egon Stanewsky, and Paul Krogmann. "Boundary-layer transition on swept cylinders at hypersonic speeds." AIAA Journal 34, no. 4 (April 1996): 649–54. http://dx.doi.org/10.2514/3.13123.

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25

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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26

Sandham, N. D., E. Schülein, A. Wagner, S. Willems, and J. Steelant. "Transitional shock-wave/boundary-layer interactions in hypersonic flow." Journal of Fluid Mechanics 752 (July 4, 2014): 349–82. http://dx.doi.org/10.1017/jfm.2014.333.

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AbstractStrong interactions of shock waves with boundary layers lead to flow separations and enhanced heat transfer rates. When the approaching boundary layer is hypersonic and transitional the problem is particularly challenging and more reliable data is required in order to assess changes in the flow and the surface heat transfer, and to develop simplified models. The present contribution compares results for transitional interactions on a flat plate at Mach 6 from three different experimental facilities using the same instrumented plate insert. The facilities consist of a Ludwieg tube (RWG), an open-jet wind tunnel (H2K) and a high-enthalpy free-piston-driven reflected shock tunnel (HEG). The experimental measurements include shadowgraph and infrared thermography as well as heat transfer and pressure sensors. Direct numerical simulations (DNS) are carried out to compare with selected experimental flow conditions. The combined approach allows an assessment of the effects of unit Reynolds number, disturbance amplitude, shock impingement location and wall cooling. Measures of intermittency are proposed based on wall heat flux, allowing the peak Stanton number in the reattachment regime to be mapped over a range of intermittency states of the approaching boundary layer, with higher overshoots found for transitional interactions compared with fully turbulent interactions. The transition process is found to develop from second (Mack) mode instabilities superimposed on streamwise streaks.

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27

Orlik, Evgeniy, Ivan Fedioun, and Dmitry Davidenko. "Boundary-Layer Transition on a Hypersonic Forebody: Experiments and Calculations." Journal of Spacecraft and Rockets 48, no. 4 (July 2011): 545–55. http://dx.doi.org/10.2514/1.51570.

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28

Lau, Kei Y. "Hypersonic Boundary-Layer Transition: Application to High-Speed Vehicle Design." Journal of Spacecraft and Rockets 45, no. 2 (March 2008): 176–83. http://dx.doi.org/10.2514/1.31134.

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29

Johnson, Heath B., Trevor G. Seipp, and Graham V. Candler. "Numerical study of hypersonic reacting boundary layer transition on cones." Physics of Fluids 10, no. 10 (October 1998): 2676–85. http://dx.doi.org/10.1063/1.869781.

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30

Yu, Min, and Xiang-Jiang Yuan. "The effect of Görtler instability on hypersonic boundary layer transition." Theoretical and Applied Mechanics Letters 6, no. 2 (March 2016): 97–99. http://dx.doi.org/10.1016/j.taml.2016.02.003.

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31

Zhang, Yunchi, and Chi Li. "Transition control of Mach 6.5 hypersonic flat plate boundary layer." Applied Mathematics and Mechanics 40, no. 2 (January 23, 2019): 283–92. http://dx.doi.org/10.1007/s10483-019-2423-8.

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32

Simeonides, G., and W. Haase. "Experimental and computational investigations of hypersonic flow about compression ramps." Journal of Fluid Mechanics 283 (January 25, 1995): 17–42. http://dx.doi.org/10.1017/s0022112095002229.

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Comprehensive results of a joint experimental and computational study of the two-dimensional flow field over flat plate/compression ramp configurations at Mach 14 are presented. These geometries are aimed to simulate, in a simplified manner, the region around deflected control surfaces of hypersonic re-entry vehicles. The test cases considered cover a range of realistic flow conditions with Reynolds numbers to the hinge line varying between 4.5 × 105 and 2.6 × 106 (with a reference length taken as the distance between the leading edge and the hinge line) and a wall-to-total-temperature ratio of 0.12. The combination of flow and geometric parameters gives rise to fully laminar strong shock wave/boundary layer interactions with extensive separation, and transitional interactions with transition occurring near the reattachment point. A fully turbulent interaction is also considered which, however, was only approximately achieved in the experiments by means of excessive tripping of the oncoming hypersonic laminar boundary layer. Emphasis has been placed upon the quality and level of confidence of both experiments and computations, including a discussion on the laminar-turbulent transition process and the associated striation phenomenon. The favourable comparison between the experimental and computational results has profided the grounds for an enhanced understanding of the relevant flow processes and their modelling. Particularly in relation to transitional shock wave/boundary layer interactions, where laminar-turbulent transition is promoted by the adverse pressure gradient and flow concavity in the reattachment region, a method is proposed to compute extreme adverse effects in the interaction region avoiding such inhibiting requirements as transition modelling or turbulence modelling over separated regions.

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33

Zhou, Ling, Chao Yan, Zi Hui Hao, and Wei Xuan Kong. "A “Laminar + Transition Criteria” Model for Hypersonic Three-Dimensional Boundary Layer Transition Prediction." Applied Mechanics and Materials 798 (October 2015): 627–31. http://dx.doi.org/10.4028/www.scientific.net/amm.798.627.

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A “laminar + transition criteria” model utilizingReθ/MeandReCFcriteria in conjunction with an intermittency functionΓis developed in this paper. With pretreated computational grid and total enthalpyh0=(h0,∞)maxcriteria the boundary layer edge and crossflow velocity can be obtained by using parallel methodology. Validation is accomplished via HIFiRE-5 and a blunt cone with small angle of attack. Results show that computedReθ/MeandReCFdistributions are similar to theN-factor for streamwise instability and crossflow instability from linear PSE methods. The shape and trend of transition regions predicted by the “laminar + transition criteria” model in HIFiRE-5 and blunt cone are in good agreement with the experiment and DNS. However, for the transition induced by inflection point on streamwise velocity profiles, using criteria related to boundary layer thickness is inappropriate and can predict transition onset prematurely.

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34

Sivasubramanian, Jayahar, and Hermann F. Fasel. "Direct numerical simulation of transition in a sharp cone boundary layer at Mach 6: fundamental breakdown." Journal of Fluid Mechanics 768 (March 10, 2015): 175–218. http://dx.doi.org/10.1017/jfm.2014.678.

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Direct numerical simulations (DNS) were performed to investigate the laminar–turbulent transition in a boundary layer on a sharp cone with an isothermal wall at Mach 6 and at zero angle of attack. The motivation for this research is to make a contribution towards understanding the nonlinear stages of transition and the final breakdown to turbulence in hypersonic boundary layers. In particular, the role of second-mode fundamental resonance, or (K-type) breakdown, is investigated using high-resolution ‘controlled’ transition simulations. The simulations were carried out for the laboratory conditions of the hypersonic transition experiments conducted at Purdue University. First, several low-resolution simulations were carried out to explore the parameter space for fundamental resonance in order to identify the cases that result in strong nonlinear interactions. Subsequently, based on the results from this study, a set of highly resolved simulations that proceed deep into the turbulent breakdown region have been performed. The nonlinear interactions observed during the breakdown process are discussed in detail in this paper. A detailed description of the flow structures that arise due to these nonlinear interactions is provided and an analysis of the skin friction and heat transfer development during the breakdown is presented. The controlled transition simulations clearly demonstrate that fundamental breakdown may indeed be a viable path to complete breakdown to turbulence in hypersonic cone boundary layers at Mach 6.

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35

Buntin, Dmitriy, Anatoliy Maslov, Timur Chimytov, and Aleksandr Shiplyuk. "Statistical Analysis of Nonlinear Processes on a Porous Surface in a Hypersonic Boundary Layer." Siberian Journal of Physics 4, no. 3 (October 1, 2009): 43–49. http://dx.doi.org/10.54362/1818-7919-2009-4-3-43-49.

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Experimental investigation of nonlinear stage of the transition to turbulence in a hypersonic boundary layer is presented. The experiments were carried out in a hypersonic wind tunnel T-326 at the Institute of theoretical and applied mechanics SB RAS. The model was a sharp cone with porous surface. Using the statistical analysis of the signals obtained by means of hot-wire it was shown that skewness and kurtosis distribution in a boundary layer on both solid and porous surface are in a qualitative agreement. At the same time the growing of skewness and kurtosis on a porous surface was shown. Analysis of mean voltage and rms voltage pulsation profiles of the hot-wire sensors showed that there is a delay of the laminar-turbulent transition on a porous surface.

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36

Miao, Hai Feng, Lv Rong Xie, and Weng Xiao Chai. "Effects of Unforced Bounday Layer Transition on the Performance of a Two-Dimensional Hypersonic Inlet." Applied Mechanics and Materials 275-277 (January 2013): 466–71. http://dx.doi.org/10.4028/www.scientific.net/amm.275-277.466.

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Numerical investigation was conducted on a typical two-dimensional hypersonic inlet to study the influence of unforced boundary layer transition affected by compression ramp geometric parameters on the inlet performance. The numerical results show that the transition onset location on the compression ramp can be delayed by filleting the ramp intersection, and also the inlet's performance obviously improves when the transition onset location is delayed. Compared with full turbulent situation, when the boundary layer transition occurs, the unstart of the inlet is significantly mitigated, the heat transfer rate on the compression ramp decreases, both the total pressure recovery coefficient and mass flow rate increase at both design and off-design points. But the static pressure distribution along the ramp is fairly independent of the varieties of boundary layer.

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37

Yates, Harrison B., Eric H. Matlis, Thomas J. Juliano, and Matthew W. Tufts. "Plasma-Actuated Flow Control of Hypersonic Crossflow-Induced Boundary-Layer Transition." AIAA Journal 58, no. 5 (May 2020): 2093–108. http://dx.doi.org/10.2514/1.j058981.

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38

Aeschliman, D. P., R. H. Croll, and D. W. Kuntz. "Shear-stress sensitive liquid crystals for hypersonic boundary-layer transition detection." Journal of Spacecraft and Rockets 32, no. 5 (September 1995): 749–57. http://dx.doi.org/10.2514/3.26679.

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39

Kimmel, Roger L., Mark A. Klein, and Stephen N. Schwoerke. "Three-Dimensional Hypersonic Laminar Boundary-Layer Computations for Transition Experiment Design." Journal of Spacecraft and Rockets 34, no. 4 (July 1997): 409–15. http://dx.doi.org/10.2514/2.3236.

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40

Schneider, Steven P. "Flight Data for Boundary-Layer Transition at Hypersonic and Supersonic Speeds." Journal of Spacecraft and Rockets 36, no. 1 (January 1999): 8–20. http://dx.doi.org/10.2514/2.3428.

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41

Orlik, E., I. Fedioun, and N. Lardjane. "Hypersonic Boundary-Layer Transition Forced by Wall Injection: A Numerical Study." Journal of Spacecraft and Rockets 51, no. 4 (July 2014): 1306–18. http://dx.doi.org/10.2514/1.a32645.

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42

Riley, Zachary B., and Jack J. McNamara. "Interaction Between Compliant Structures and Boundary-Layer Transition in Hypersonic Flow." AIAA Journal 55, no. 8 (August 2017): 2645–63. http://dx.doi.org/10.2514/1.j055521.

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43

Chen, X., G. L. Huang, and C. B. Lee. "Hypersonic boundary layer transition on a concave wall: stationary Görtler vortices." Journal of Fluid Mechanics 865 (February 19, 2019): 1–40. http://dx.doi.org/10.1017/jfm.2019.24.

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This study investigates the stability and transition of Görtler vortices in a hypersonic boundary layer using linear stability theory and direct numerical simulations. In the simulations, Görtler vortices are separately excited by wall blowing and suction with spanwise wavelengths of 3, 6 and 9 mm. In addition to primary streaks with the same wavelength as the blowing and suction, secondary streaks with half the wavelength also emerge in the 6 and 9 mm cases. The streaks develop into mushroom structures before breaking down. The breakdown processes of the three cases are dominated by a sinuous-mode instability, a varicose-mode instability and a combination of the two, respectively. Both fundamental and subharmonic instabilities are relevant in all cases. Multiple modes are identified in the secondary-instability stage, some of which originate from the primary instabilities (first and second Mack modes). We demonstrate that the first Mack mode can be destabilized to either a varicose-mode or sinuous-mode streak instability depending on its frequency and wavelength, whereas the second Mack mode undergoes a stabilizing stage before turning into a varicose mode in the 6 and 9 mm cases. An energy analysis reveals the stabilizing and destabilizing mechanisms of the primary instabilities under the influence of Görtler vortices, highlighting the role played by the spanwise production based on the spanwise gradient of the streamwise velocity in both varicose and sinuous modes. The effects introduced by the secondary streaks are examined by filtering the secondary streaks in two new simulations with nominally identical conditions to those of the 6 and 9 mm cases. Remarkably, the secondary streaks can destabilize the Görtler vortices, therefore advancing the transition. The stability theory results are in good agreement with those from direct numerical simulations.

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44

Zhou, L., C. Yan, Z. H. Hao, and R. F. Du. "Improved k – ω – γ model for hypersonic boundary layer transition prediction." International Journal of Heat and Mass Transfer 94 (March 2016): 380–89. http://dx.doi.org/10.1016/j.ijheatmasstransfer.2015.11.048.

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45

Chen, Yu, and Nick Gibbons. "Simulations of Hypersonic Boundary-Layer Transition over a Flat Plate with the Spalart-Allmaras One-Equation BCM Transitional Model." Mathematics 10, no. 19 (September 21, 2022): 3431. http://dx.doi.org/10.3390/math10193431.

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Transitional flow has a significant impact on vehicles operating at supersonic and hypersonic speeds. An economic way to simulate this problem is to use computational fluid dynamics (CFD) codes. However, not all CFD codes can solve transitional flows. This paper examines the ability of the Spalart–Allmaras one-equation BCM (SA-BCM) transitional model to solve hypersonic transitional flow, implemented in the open-source CFD code Eilmer. Its performance is validated via existing wind tunnel data. Eight different hypersonic flow conditions are applied. A flat plate model is built for the numerical tests. The results indicate that the existing SA-BCM model is sensitive to the freestream turbulence intensity and the grid size. It is not accurate in all the test cases, though the transitional length can be matched by tuning the freestream intensity. This is likely due to the intermittency term of the SA-BCM model not being appropriately calibrated for high-velocity flow, though if the model can be recalibrated it may be able to solve the general high-velocity flows. Although the current SA-BCM model is only accurate under certain flow conditions after one calibration process, it remains attractive to CFD applications. As a one-equation model, the SA-BCM model runs much faster than multiple-equation flow models.

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46

Liu, Shenshen, Xianxu Yuan, Zhiyong Liu, Qiang Yang, Guohua Tu, Xi Chen, Yewei Gui, and Jianqiang Chen. "Design and transition characteristics of a standard model for hypersonic boundary layer transition research." Acta Mechanica Sinica 37, no. 11 (October 20, 2021): 1637–47. http://dx.doi.org/10.1007/s10409-021-01136-5.

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Chen, Shuo. "The effect of concave roughness on the hypersonic flat-plate boundary-layer transition." International Journal of Modern Physics B 34, no. 14n16 (June 1, 2020): 2040091. http://dx.doi.org/10.1142/s0217979220400913.

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In order to reveal the effect of aircraft surface concave roughness on the transition, several hypersonic quiet wind tunnel tests were carried out on the flat-plate model with independent concave roughness on the surface. The experimental Mach number was 6.5 and the total temperature was 430 K. Using infrared thermal imaging technology, a general rule of the effect of concave roughness on the boundary layer transition was obtained. The flow visualization results and the PCB pressure measurement results showed that the concave roughness promotes the transition by increasing the growth of the first mode wave rather than the growth of the second mode wave.

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Grubin, S. E., and V. N. Trigub. "The long-wave limit in the asymptotic theory of hypersonic boundary-layer stability." Journal of Fluid Mechanics 246 (January 1993): 381–95. http://dx.doi.org/10.1017/s0022112093000187.

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This paper discusses the long-wave limit of the asymptotic theory of hypersonic boundary-layer stability for a gas with the Prandtl number ½ < σ < 1 and with the viscosity–temperature law being a power function. The investigation is confined to the local-parallel approximation.In the long-wave limit the vorticity mode starts to interact with the acoustic disturbances in the boundary-layer region. The general solution of the linear problem in the boundary-layer inner region is analysed numerically and analytically. This solution is matched with the long-wave vorticity-mode solution near the transition layer. As a result, the inviscid instability problem for a hypersonic boundary layer is formulated. The analytical solution of this problem is found and analysed. The different limits of the solution are considered and the universal forms of the dependence are obtained. A similarity parameter is found which is a function of the Prandtl number and the power in the viscosity–temperature law. A significant change of the solution behaviour is noticed when this parameter passes a critical value. The asymptotic structure of the amplification rate, as a function of the wavenumber, is described and discussed.

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Dong, Ming, and Chuang Li. "Effect of Two-Dimensional Short Rectangular Indentations on Hypersonic Boundary-Layer Transition." AIAA Journal 59, no. 7 (July 2021): 2368–81. http://dx.doi.org/10.2514/1.j059957.

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Hollis, Brian R. "Surface Heating and Boundary-Layer Transition on a Hypersonic Inflatable Aerodynamic Decelerator." Journal of Spacecraft and Rockets 55, no. 4 (July 2018): 856–76. http://dx.doi.org/10.2514/1.a34046.

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