Revision as of 08:20, 12 August 2013

Planar shock-wave boundary-layer interaction

Semi-confined Flows

Underlying Flow Regime 3-32

Description

Introduction

The problem of the unsteadiness in shock wave/boundary layer interactions (SWBLI) is challenging in many respects. A more general question is related to the unsteadiness or "breathing" of separated flows, whatever the regime, subsonic or supersonic. This is a problem that is important for both applications and basic research. In many aeronautical applications, such as aircraft profiles, air intakes, turbines or compressors, shock waves are formed and generally lead to separation. The resulting separation bubbles are unsteady, in the sense that they produce frequencies much lower (by at least two orders of magnitude) than the identified frequencies of the turbulent flow. Another difficulty arises if high-speed flows are considered, in which case the unsteadiness is also dependent on Mach number.

Review of UFR studies and choice of test case

Provide a brief review of past studies of this UFR which have included test case comparisons of experimental measurements with CFD results. Identify your chosen study (or studies) on which the document will focus. State the test-case underlying the study and briefly explain how well this represents the UFR? Give reasons for this choice (e.g a well constructed test case, a recognised international comparison exercise, accurate measurements, good quality control, a rich variety of turbulence or physical models assessed etc.) . If possible, the study should be taken from established data bases. Indicate whether of not the experiments have been designed for the purpose of CFD validation (desirable but not mandatory)?

Contributed by: Jean-Paul Dussauge — Orange