Direct Numerical Simulation of Laminar-Turbulent Transition in a Flared Cone Boundary Layer at Mach 6
Author:
Affiliation:
1. University of Arizona, Tucson
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.2016-0846
Reference22 articles.
1. The Effect of Pressure Gradients on Transition Zone Length in Hypersonic Boundary Layers.
2. Direct Numerical Simulation of Hypersonic Boundary-Layer Flow on a Flared Cone
3. Hypersonic boundary layer stability over a flared cone in a quiet tunnel
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1. Numerical Investigation of Nonlinear Boundary-Layer Transition for Cones at Mach 6;AIAA Journal;2021-06
2. Nonlinear Instability Characterization of Hypersonic Laminar Boundary Layer;AIAA Journal;2020-12
3. History and Progress of Boundary-Layer Transition on a Mach-6 Flared Cone;Journal of Spacecraft and Rockets;2019-03
4. Nonlinear Spectral Broadening Dynamics of Second Mode Waves on a Hypersonic Flared Cone;2018 Fluid Dynamics Conference;2018-06-24
5. Hypersonic Boundary-Layer Transition: Comparison of the Fundamental Resonance Breakdown for a Flared and Straight Cone at Mach 6;2018 Fluid Dynamics Conference;2018-06-24
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