Towards transition modelling for supersonic laminar flow control based on spanwise periodic roughness elements

DOI10.1098/RSTA.2005.1551zbMath1152.76404OpenAlexW2137799730WikidataQ51370564 ScholiaQ51370564MaRDI QIDQ5301823

Chau-Lyan Chang, Meelan M. Choudhari, Li Jiang

Publication date: 20 January 2009

Published in: Philosophical Transactions of the Royal Society A: Mathematical, Physical and Engineering Sciences (Search for Journal in Brave)

Full work available at URL: https://doi.org/10.1098/rsta.2005.1551

zbMATH Keywords

transitionsupersoniccrossflowlaminar flow controlreceptivity

Mathematics Subject Classification ID

Turbulent boundary layers (76F40)

Related Items (2)

Spatially developing secondary instabilities in compressible swept airfoil boundary layers ⋮ Interactions between second mode and low-frequency waves in a hypersonic boundary layer

Uses Software

• LASTRAC

Cites Work

• Instability-wave propagation in boundary-layer flows at subsonic through hypersonic Mach numbers
• On the generation of Tollmien-Schlichting waves by sound
• Roughness-induced receptivity to crossflow vortices on a swept wing
• Scattering of acoustic waves into Tollmien-Schlichting waves by small streamwise variations in surface geometry
• Subharmonic resonance, pairing and shredding in the mixing layer
• Receptivity to surface roughness near a swept leading edge
• Simulation of swept-wing vortices using nonlinear parabolized stability equations
• Secondary instability of crossflow vortices and swept-wing boundary-layer transition

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