Skip to main content Accessibility help
  • Get access
    Check if you have access via personal or institutional login
  • Cited by 9
  • Print publication year: 2011
  • Online publication date: June 2012

2 - Physical Introduction


Shock Wave–Boundary-Layer Interactions: Why They Are Important

The repercussions of a shock wave–boundary layer interaction (SBLI) occurring within a flow are numerous and frequently can be a critical factor in determining the performance of a vehicle or a propulsion system. SBLIs occur on external or internal surfaces, and their structure is inevitably complex. On the one hand, the boundary layer is subjected to an intense adverse pressure gradient that is imposed by the shock. On the other hand, the shock must propagate through a multilayered viscous and inviscid flow structure. If the flow is not laminar, the production of turbulence is enhanced, which amplifies the viscous dissipation and leads to a substantial rise in the drag of wings or – if it occurs in an engine – a drop in efficiency due to degrading the performance of the blades and increasing the internal flow losses. The adverse pressure gradient distorts the boundary-layer velocity profile, causing it to become less full (i.e., the shape parameter increases). This produces an increase in the displacement effect that influences the neighbouring inviscid flow. The interaction, experienced through a viscous-inviscid coupling, can greatly affect the flow past a transonic airfoil or inside an air-intake. These consequences are exacerbated when the shock is strong enough to separate the boundary layer, which can lead to dramatic changes in the entire flowfield structure with the formation of intense vortices or complex shock patterns that replace a relatively simple, predominantly inviscid, unseparated flow structure. In addition, shock-induced separation may trigger large-scale unsteadiness, leading to buffeting on wings, buzz for air-intakes, or unsteady side loads in nozzles. All of these conditions are likely to limit a vehicle's performance and, if they are strong enough, can cause structural damage.

Related content

Powered by UNSILO
Shapiro, A. HThe Dynamics and Thermodynamics of Compressible Fluid FlowNew YorkThe Ronald Press Company 1953
Edney, BAnomalous heat transfer and pressure distributions on blunt bodies at hypersonic speeds in the presence of an impinging shockAeronautical Research Institute of Sweden 115 1968
Oswatitsch, K 1945
Coles, D. EThe law of the wake in the turbulent boundary layerJ. Fluid Mech 2 1956 191
Cousteix, JCouche limite laminaireToulouseC??padu??s-Editions 1988
Cousteix, JTurbulence et couche limiteToulouseC??padu??s-Editions 1989
Lighthill, M. JOn boundary layer upstream influence. Part II: Supersonic flows without separationProc. Roy. Soc. A 217 1953 478
Stewartson, KWilliams, P. GSelf-induced separationProc. Roy. Soc., A 312 1969 181
Henderson, L. FThe reflection of a shock wave at a rigid will in the presence of a boundary layerJ. Fluid Mech 30 1967 699
Settles, G. S 1975
Green, J. EInteraction between shock waves and turbulent boundary layersProgress in Aerospace Science 11 1970 235
Shang, J. SHankey, W. LLaw, C. HNumerical simulation of shock wave/turbulent boundary-layer interactionAIAA J 14 1976 1451
Chapman, D. RKuhen, D. MLarson, H. KInvestigation of separated flows in supersonic and subsonic streams with emphasis on the effect of transitionNACA TN 3869 1957
Délery, JMarvin, J. GShock Wave/Boundary Layer InteractionsAGARDograph 280 1986
Zhukoski, E. ETurbulent boundary-layer separation in front of a forward-facing stepAIAA J 5 1967 1746
Schmucker, R. H 1973
Hakkinen, R. JGreber, ITrilling, LAbarbanel, S. S 1959
Gadd, G. EHolder, D. WRegan, J. DAn experimental investigation of the interaction between shock waves and boundary layersProc. Roy. Soc. A 226 1954 226
Elfstrom, G. MTurbulent hypersonic flow at a wedge compression cornerJ. Fluid Mech 53 1972 113
Lewis, J. EKubota, TLees, LExperimental investigation of supersonic laminar two-dimensional boundary layer separation in a compression corner with and without coolingAIAA Paper67 6 1967 7
Spaid, F. WFrishett, J. CIncipient separation of a supersonic, turbulent boundary layer, including effects of heat transferAIAA J 10 1972 915
Délery, J 1992
Délery, JCoët, M.-C 1990
Holden, M 1977
Hayes, W. DProbstein, R. FHypersonic flow theoryNew YorkAcademic Press 1966
Coët, M.-CDélery, JChanetz, B 1992
Grasso, FLeone, G 1992
Mallinson, S. GGai, S. LMudford, N. RHigh enthalpy, hypersonic compression corner flowAIAA J 34 1996 1130
Legendre, R 1977
Délery, JLegendre, RobertWerlé, HenriToward the elucidation of three-dimensional separationAnn. Rev Fluid Mech 33 2001 129
Barberis, DMolton, P 1995
Dupont, PHaddad, CDebiève, J.-FSpace and time organization in a shock-induced boundary layerJ. Fluid Mech 559 2006 255
Furlano, F 2001
Regenscheit, BVersuche zur Widerstandsverringerung eines Flügels bei hoher Machscher – Zahl durch Absaugung der hinter dem Gebiet unstetiger Verdichtung abgelösten GrenzschichtZWB, Forschungsbericht 1424 1941
Fage, ASargent, R. FARC R&M 1913 1943
Délery, JShock-wave/turbulent boundary-layer interaction and its controlProgress in Aerospace Sciences 22 1985 209
Stanewsky, EDélery, JFulker, JGeissler, WEUROSHOCK: Drag Reduction by Passive Shock ControlNotes on Numerical Fluid Mechanics 56 1997
Délery, J.Handbook of Compressible AerodynamicsISTE ??? WILEY & Sons 2010