arXiv (All)
open access
Control of deterministic breakdown to turbulence of hypersonic boundary layer with spanwise non-uniform surface temperature
Direct Numerical Simulation (DNS) of a Mach 6 boundary layer over a flat plate is performed to assess the effect of spanwise non-uniform surface temperature on breakdown to turbulence under deterministic forcing. The streamwise location of laminar to turbulent transition in hypersonic boundary layer
Conceptio Open Archive
Analyze & explore related research in Conceptio
Connect this record directly into your research workflow or AI agent. Explore citations across open repositories, query full text, and export structured proof bundles.
This document is indexed with metadata only: full text is not available in the archive for this record. Open the official source ↗
Related documents
- Supersonic turbulence in 3D isothermal flow collision#669953
- Stabilisation of second Mack mode in hypersonic boundary layers through spanwise non-uniform surface temperature distribution#251985
- Multiphysics modelling of ultrasonic melt treatment in the hot-top and launder during direct-chill casting : path to indirect microstructure simulation#270424
- High-fidelity modeling of high-enthalpy plasma wind tunnels for hypersonic testing#213274
- Data-driven modeling of hypersonic flows in chemical non-equilibrium with catalytic surfaces#609612
Record · ID 1128579
Retrieved via Conceptio: every document is proof-bundled with source, license, and retrieval metadata.
Retrieved via Conceptio: every document is proof-bundled with source, license, and retrieval metadata.
Bring this data into your agent: Connect via MCP or API · 20 free credits to start · no card required
Read the Docs → · View CLI source on GitHub · Conceptio Open Knowledge Archive
Read the Docs → · View CLI source on GitHub · Conceptio Open Knowledge Archive