| Issue |
Volume 5, Juin 2013
Progress in Flight Physics
|
|
|---|---|---|
| Page(s) | 93 - 106 | |
| Section | Chapter Two. Boundary layer stability | |
| DOI | https://doi.org/10.1051/eucass/201305093 | |
| Published online | 14 June 2013 | |
Effects of shock on hypersonic boundary layer stability
von Karman Institute 72 Chaussée de Waterloo, Rhode-St-Genèse 1640, Belgium
The design of hypersonic vehicles requires the estimate of the laminar to turbulent transition location for an accurate sizing of the thermal protection system. Linear stability theory is a fast scientific way to study the problem. Recent improvements in computational capabilities allow computing the flow around a full vehicle instead of using only simplified boundary layer equations. In this paper, the effect of the shock is studied on a mean flow provided by steady Computational Fluid Dynamics (CFD) computations and simplified boundary layer calculations.
© Owned by the authors, published by EDP Sciences, 2013
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