Effect of leading edge bluntness on the interaction of ramp induced shock wave with laminar boundary layer at hypersonic speed

DOI10.1016/j.compfluid.2014.03.004zbMath1391.76280OpenAlexW2057573191MaRDI QIDQ1641365

Bibin John, Vinayak Kulkarni

Publication date: 19 June 2018

Published in: Computers and Fluids (Search for Journal in Brave)

Full work available at URL: https://doi.org/10.1016/j.compfluid.2014.03.004

zbMATH Keywords

hypersonicsshock boundary layer interactionsleading edge bluntness

Mathematics Subject Classification ID

General aerodynamics and subsonic flows (76G25) Hypersonic flows (76K05)

Related Items (3)

On the length scales of hypersonic shock-induced large separation bubbles near leading edges ⋮ Hypersonic flow over spherically blunted double cones ⋮ Numerical study of bluntness effects on laminar leading edge separation in hypersonic flow

Uses Software

• AUSM

Cites Work

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• A sequel to AUSM: AUSM\(^ +\)
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• Performance comparison of flux schemes for numerical simulation of high-speed inviscid flows
• Numerical assessment of correlations for shock wave boundary layer interaction
• Convergence to steady state solutions of the Euler equations on unstructured grids with limiters
• Analysis of hypersonic compression ramp laminar flows under sharp leading edge conditions
• Separation length in high-enthalpy shock/boundary-layer interaction
• The hypersonic laminar boundary layer near sharp compression and expansion corners
• Validation procedure for the analysis of shock-wave/boundary-layer interaction problems

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