Artificially Induced Boundary-Layer Transition on Blunt-Slender Cones at Hypersonic Speeds

Boudreau, A H

doi:10.2514/3.57651

Cited by 15 publications

(4 citation statements)

References 7 publications

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“…A one-sided bilinear interpolation is applied to calculate the accurate flow conditions in the sharp irregular boundary. Johansen, McCorquodale and Colella [21,22] developed a similar sharp-interface Cartesian grid [6]. method for solving two-dimensional Poisson and heat equations on irregular domains.…”

Section: Introductionmentioning

confidence: 99%

A high-order cut-cell method for numerical simulation of hypersonic boundary-layer instability with surface roughness

Wang

Zhong

2010

Journal of Computational Physics

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Section: Introductionmentioning

confidence: 99%

A high-order cut-cell method for numerical simulation of hypersonic boundary-layer instability with surface roughness

Wang

Zhong

2010

Journal of Computational Physics

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“…Refs. [23][24][25][26][27][28][29][30][31]. A primary concern is that transition, with the associated increased heating levels, will occur during the high-heating portion of the entry trajectory with a potential negative impact on the TPS.…”

Section: A Issuesmentioning

confidence: 99%

Aeroheating Design Issues for Reusable Launch Vehicles -- A Perspective

Zoby

Thompson

Wurster

2004

34th AIAA Fluid Dynamics Conference and Exhibit

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An overview of basic aeroheating design issues for Reusable Launch Vehicles (RLV), which addresses the application of hypersonic ground-based testing, and computational fluid dynamic (CFD) and engineering codes, is presented. Challenges inherent to the prediction of aeroheating environments required for the successful design of the RLV Thermal Protection System (TPS) are discussed in conjunction with the importance of employing appropriate experimental/computational tools. The impact of the information garnered by using these tools in the resulting analyses, ultimately enhancing the RLV TPS design is illustrated. A wide range of topics is presented in this overview; e.g. the impact of flow physics issues such as boundary-layer transition, including effects of distributed and discrete roughness, shockshock interactions, and flow separation/reattachment. Also, the benefit of integrating experimental and computational studies to gain an improved understanding of flow phenomena is illustrated. From computational studies, the effect of low-density conditions and of uncertainties in material surface properties on the computed heating rates are highlighted as well as the significant role of CFD in improving the Outer Mold Line (OML) definition to reduce aeroheating while maintaining aerodynamic performance. Appropriate selection of the TPS design trajectories and trajectory shaping to mitigate aeroheating levels and loads are discussed. Lastly, an illustration of an aeroheating design process is presented whereby data from hypersonic wind-tunnel tests are integrated with predictions from CFD codes and engineering methods to provide heating environments along an entry trajectory as required for TPS design. I.

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“…10. An example surface roughness on test models for hypersonic boundary layer transition: 1) isolated roughness, 2) distributed roughness [25].…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation of Hypersonic Boundary Layer Receptivity, Transient Growth and Transition With Surface Roughness

Zhong¹

2009

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The public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing the burden, to the Department of Defense, Executive Service Directorate (0704'()188). Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. The objective of this research is to conduct DNS studies of hypersonic boundary layer receptivity, transient growth and transition with surface roughness. The main approach is to use DNS as a research tool to study the boundary layer receptivity and transient-growth mechanisms in hypersonic flows, including the development of numerical algorithms and parallel computer codes of higher order numerical methods for the simulation of hypersonic flows with surface roughness of fmite heights. During the three-year period, we have conducted DNS studies on the hypersonic boundary layer flows over flat plates and blunt cones. A new high-order cut -cell method has been developed for the numerical simulation of hypersonic boundary layer transition with finite height surface roughness. The method has been applied to the numerical simulations of two-dimensional hypersonic flows over a flat plate. Furthermore, the stabilization effect of the surface porous coating over a flat plate is extensively studied by series of numerical simulations. We also collaborate with Prof. Tumin in the University of Arizona to compare numerical and theoretical results on receptivity of a Mach 5.92 flow over a flat plate to wall blowing-suction, and to analyze the nonparallel flow effect.

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Artificially Induced Boundary-Layer Transition on Blunt-Slender Cones at Hypersonic Speeds

Cited by 15 publications

References 7 publications

A high-order cut-cell method for numerical simulation of hypersonic boundary-layer instability with surface roughness

A high-order cut-cell method for numerical simulation of hypersonic boundary-layer instability with surface roughness

Aeroheating Design Issues for Reusable Launch Vehicles -- A Perspective

Numerical Simulation of Hypersonic Boundary Layer Receptivity, Transient Growth and Transition With Surface Roughness

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