Abstr:UFR 3-32: Difference between revisions
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=== Underlying Flow Regime 3-32 === | === Underlying Flow Regime 3-32 === | ||
= Abstract = | = Abstract = | ||
The interaction between a shock wave and a boundary layer remains an | |||
issue for both applications and basic research. In aeronautical | |||
situations, such interactions are at the origin of unsteadiness which | |||
may be detrimental for air frames and mechanical structures. The | |||
understanding of such phenomena is not always clear because the | |||
frequencies involved in the unsteadiness are much below any other | |||
characteristic frequency in the flow (see Dolling 2001 and Smits and | |||
Dussauge 2006 for reviews). Only a few interpretations have been | |||
proposed, although recent attempts seem to offer more comprehensive | |||
views (see Dupont, Debiève, Dussauge 2011 for example). A severe test | |||
case is proposed in the European program UFAST (Unsteady eFfects of | |||
shock wAve induced SeparaTion) to illustrate this problem: the | |||
reflection of an oblique shock on the turbulent boundary layer of a flat | |||
plate at a Mach number of 2.25, at different angles of deviation | |||
producing different cases of separation. This well documented experiment | |||
is presented, including mean and turbulent flow measurements together | |||
with spectral measurements to determine the dominant frequencies of the | |||
unsteadiness. | |||
Of course RANS model can only provide a global description | |||
of mean quantities. More advanced models like LES or DES have the | |||
ability to capture the unsteadiness. Comparisons with LES and DES | |||
numerical simulations are presented and discussed, and best practice | |||
guidelines are proposed. These studies are available in the UFAST | |||
database, as published in Doerffer 2009 and in Doerffer et al. 2010. | |||
<br/> | <br/> | ||
---- | ---- |
Revision as of 08:16, 12 August 2013
Planar shock-wave boundary-layer interaction
Semi-confined Flows
Underlying Flow Regime 3-32
Abstract
The interaction between a shock wave and a boundary layer remains an
issue for both applications and basic research. In aeronautical
situations, such interactions are at the origin of unsteadiness which
may be detrimental for air frames and mechanical structures. The
understanding of such phenomena is not always clear because the
frequencies involved in the unsteadiness are much below any other
characteristic frequency in the flow (see Dolling 2001 and Smits and
Dussauge 2006 for reviews). Only a few interpretations have been
proposed, although recent attempts seem to offer more comprehensive
views (see Dupont, Debiève, Dussauge 2011 for example). A severe test
case is proposed in the European program UFAST (Unsteady eFfects of
shock wAve induced SeparaTion) to illustrate this problem: the
reflection of an oblique shock on the turbulent boundary layer of a flat
plate at a Mach number of 2.25, at different angles of deviation
producing different cases of separation. This well documented experiment
is presented, including mean and turbulent flow measurements together
with spectral measurements to determine the dominant frequencies of the
unsteadiness.
Of course RANS model can only provide a global description
of mean quantities. More advanced models like LES or DES have the
ability to capture the unsteadiness. Comparisons with LES and DES
numerical simulations are presented and discussed, and best practice
guidelines are proposed. These studies are available in the UFAST
database, as published in Doerffer 2009 and in Doerffer et al. 2010.
Contributed by: Jean-Paul Dussauge — Orange
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