UFR 3-32 Evaluation: Difference between revisions
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== Comparison of CFD Calculations with Experiments == | == Comparison of CFD Calculations with Experiments == | ||
===LES versus experiment at shock generator angle of 8 degrees=== | |||
Velocity fluctuations in a plane parallel to the wall evidence the | |||
presence of low and high velocity streaks that populates canonical boundary | |||
layers. After the separation (identified by the first dashed line), the | |||
size of turbulent structures in the spanwise direction significantly | |||
increases and further downstream the turbulence slowly relaxes toward its | |||
canonical state. This figure illustrates the fact that the simulation is | |||
capable of capturing most of the finest turbulent structures present in a | |||
supersonic boundary layer. | |||
<br/> | <br/> | ||
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Revision as of 09:07, 12 August 2013
Planar shock-wave boundary-layer interaction
Semi-confined Flows
Underlying Flow Regime 3-32
Evaluation
Comparison of CFD Calculations with Experiments
LES versus experiment at shock generator angle of 8 degrees
Velocity fluctuations in a plane parallel to the wall evidence the
presence of low and high velocity streaks that populates canonical boundary
layers. After the separation (identified by the first dashed line), the
size of turbulent structures in the spanwise direction significantly
increases and further downstream the turbulence slowly relaxes toward its
canonical state. This figure illustrates the fact that the simulation is
capable of capturing most of the finest turbulent structures present in a
supersonic boundary layer.
Contributed by: Jean-Paul Dussauge — Orange
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