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Some physical aspects of shock wave/boundary layer interactions

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Abstract

When the flow past a vehicle flying at high velocity becomes supersonic, shock waves form, caused either by a change in the slope of a surface, a downstream obstacle or a back pressure constraining the flow to become subsonic. In modern aerodynamics, one can cite a large number of circumstances where shock waves are present. The encounter of a shock wave with a boundary layer results in complex phenomena because of the rapid retardation of the boundary layer flow and the propagation of the shock in a multilayered structure. The consequence of shock wave/boundary layer interaction (SWBLI) are multiple and often critical for the vehicle or machine performance. The shock submits the boundary layer to an adverse pressure gradient which may strongly distort its velocity profile. At the same time, in turbulent flows, turbulence production is enhanced which amplifies the viscous dissipation leading to aggravated performance losses. In addition, shock-induced separation most often results in large unsteadiness which can damage the vehicle structure or, at least, severely limit its performance. The article first presents basic and well-established results on the physics of SWBLI corresponding to a description in terms of an average two-dimensional steady flow. Such a description allows apprehending the essential properties of SWBLIs and drawing the main features of the overall flow structure associated with SWBLI. Then, some emphasis is placed on unsteadiness in SWBLI which constitutes a salient feature of this phenomenon. In spite of their importance, fluctuations in SWBLI have been considered since a relatively recent date although they represent a domain which deserves a special attention because of its importance for a clear physical understanding of interactions and of its practical consequences as in aeroelasticity.

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Abbreviations

(C):

Designates a shock

E(f):

Power spectral density

f :

Frequency

h :

Height of the separated bubble

L :

Interaction length

M :

Mach number

M c :

Convective Mach number

M e :

Mach number at the boundary layer outer edge

p :

Pressure

p st :

Stagnation pressure

r :

Density ratio

R :

Designates the reattachment point

s :

Velocity ratio

S :

Designates the separation point

S L :

Strouhal number

T :

Designates a triple point

U D :

Flow velocity on the separated flow dividing streamline

U e :

Flow velocity at the boundary layer outer edge

U s :

Shock displacement velocity

X 0 :

Interaction origin

\({\Phi(M_c)}\) :

Normalized spreading rate of the mixing layer

\({\varphi}\) :

Shock induced deflection

δ :

Boundary layer thickness

(Γ):

Designates a shock polar

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Authors and Affiliations

  1. ONERA/DAFE, Centre de Meudon, Meudon, France

    Jean Délery

  2. IUSTI, UMR 6595 CNRS-Université d’Aix Marseille, Marseille, France

    Jean-Paul Dussauge

Authors
  1. Jean Délery
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  2. Jean-Paul Dussauge
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Correspondence to Jean-Paul Dussauge.

Additional information

Communicated by A. Hadjadj.

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Délery, J., Dussauge, JP. Some physical aspects of shock wave/boundary layer interactions. Shock Waves 19, 453–468 (2009). https://doi.org/10.1007/s00193-009-0220-z

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