Transition Prediction in Hypersonic Boundary Layers Using Receptivity and Freestream Spectra.
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TLDR
The location of transition onset predicted from the simulation including the freestream spectrum, receptivity, and the linear and the weakly nonlinear evolutions yields a solution close to the measured onset location for the sharp cone.Abstract:
Boundary-layer transition in hypersonic flows over a straight cone can be predicted using measured freestream spectra, receptivity, and threshold values for the wall-pressure fluctuations at the tr...read more
Citations
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Journal ArticleDOI
Direct numerical simulations of hypersonic boundary-layer transition for a flared cone: fundamental breakdown
Christoph Hader,Hermann F. Fasel +1 more
TL;DR: In this paper, direct numerical simulations were carried out to investigate the laminar-turbulent transition for a flared cone at Mach 6 at zero angle of attack at the Boeing/AFOSR Mach 6 Quiet Tunnel (BAM6QT) at Purdue University.
Journal ArticleDOI
Flow structures in transitional and turbulent boundary layers
Cunbiao Lee,Xianyang Jiang +1 more
Journal ArticleDOI
Towards simulating natural transition in hypersonic boundary layers via random inflow disturbances
Christoph Hader,Hermann F. Fasel +1 more
TL;DR: In this paper, a random forcing approach was implemented into a high-order accurate finite-difference code in order to investigate the natural laminar-turbulent transition in hypersonic boundary layers.
Journal ArticleDOI
Nose-Tip Bluntness Effects on Transition at Hypersonic Speeds
Pedro Paredes,Meelan M. Choudhari,Fei Li,Joseph S. Jewell,Roger L. Kimmel,Eric C. Marineau,Guillaume Grossir +6 more
TL;DR: The existing database of transition measurements in hypersonic ground facilities has established that as the nose-tip bluntness is increased the onset of boundary-layer transition over a circular c....
Proceedings ArticleDOI
Investigation of mach 10 boundary layer stability of sharp cones at angle-of-attack, part 1: Experiments
Eric C. Marineau,C. George Moraru,Daniel R. Lewis,Joseph D. Norris,John Lafferty,Heath B. Johnson +5 more
TL;DR: In this paper, the boundary-layer transition and stability characteristics of sharp cones at angle-of-attack were investigated with measurements at Mach 10 in the Arnold Engineering Development Complex (AEDC) Hypervelocity Wind Tunnel 9 on a 1.5m long, 7-deg cone at unit Reynolds numbers between 1.8 and 15 million per meter.
References
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Book ChapterDOI
Essentially Non-Oscillatory and Weighted Essentially Non-Oscillatory Schemes for Hyperbolic Conservation Laws
TL;DR: In this paper, the authors describe the construction, analysis, and application of ENO and WENO schemes for hyperbolic conservation laws and related Hamilton-Jacobi equations, where the key idea lies at the approximation level, where a nonlinear adaptive procedure is used to automatically choose the locally smoothest stencil, hence avoiding crossing discontinuities in the interpolation procedure as much as possible.
Journal ArticleDOI
Wind Tunnel Experiments Relating to Supersonic and Hypersonic Boundary-Layer Transition
TL;DR: In this paper, hot-wire anemometry is used to study the origin and growth of "natural" fluctuations in zero pressure-gradient boundary layers for several Mach numbers between 1.6 and 8.5.
Essentially Non-Oscillatory and Weighted Essentially Non-Oscillatory Schemes for Hyperbolic Conservation Laws
TL;DR: The construction, analysis, and application of ENO and WENO schemes for hyperbolic conservation laws and related Hamilton-Jacobi equations are described, where a nonlinear adaptive procedure is used to automatically choose the locally smoothest stencil.
Proceedings ArticleDOI
On hypersonic boundary-layer stability
TL;DR: In this paper, a review of experimental hypersonic boundary-layer stability results obtained using hot-wire anemometry techniques is presented, where data were obtained at a freestream Mach number of 8 on watercooled and uncooled 7-degree half angle cones and on a water-cooled cylinder.
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