Numerical investigation of a Mach 6 hypersonic laminar flow on two-dimensional cold-wall compression corners with controlled surface roughness
Author:
Publisher
Elsevier BV
Subject
Fluid Flow and Transfer Processes,Mechanical Engineering,Condensed Matter Physics
Reference29 articles.
1. Shock Wave–Boundary-Layer Interactions;Babinsky;Cambridge University Press,2011
2. Balakumar, P. (2003). Transition in a supersonic boundary-layer due to roughness and acoustic disturbances. 33rd AIAA Fluid Dynamics Conference and Exhibit, 23-26 June 2003, Orlando, FL. DOI: 10.2514/6.2003-3589.
3. Separated laminar boundary layers;Burggraf,1976
4. Görtler Vortices in Hypersonic Flow on Compression Ramps;Cao;AIAA J.,2019
5. Unsteady effects in a hypersonic compression ramp flow with laminar separation;Cao;J. Fluid Mech.,2021
Cited by 3 articles. 订阅此论文施引文献 订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献
1. Flow and heat transfer analysis of laminar flow in hypersonic aircraft with variable specific heat capacity at small attack angles;International Journal of Numerical Methods for Heat & Fluid Flow;2023-11-29
2. Numerical investigation of a Mach 6 laminar shock-wave/boundary-layer interaction on a two-dimensional ramp with 3D controlled surface roughness;International Journal of Heat and Fluid Flow;2023-10
3. The determination of physical dimensions of a hypersonic three-stage compression system considering panel vibration effects;Aerospace Science and Technology;2023-09
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