Investigation of three-dimensional shock/boundary layer interactions at swept compression corners

Settles, Gary S.; Perkins, J.

doi:10.2514/6.1979-1498

Cited by 7 publications

(8 citation statements)

References 3 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Many experimental efforts have been performed on STBLI during the 70's and 80's. For example, Settles et al [3][4][5][6] and Dolling & Bogdonoff 7 did experiments on compression ramp and swept fin configurations to study 2D and 3D STBLI problems. Also Smits and Muck 8 did experiments on compression ramps of different turning angles to investigate turbulence amplification.…”

Section: Introductionmentioning

confidence: 99%

Analysis of Shockwave/Turbulent Boundary Layer Interaction Using DNS and Experimental Data

Bookey

Martı́n

et al. 2005

43rd AIAA Aerospace Sciences Meeting and Exhibit

View full text Add to dashboard Cite

Shockwave/turbulent boundary layer interactions are studied by comparing direct numerical simulation and experimental data. Two canonical configurations, a 24-degree compression ramp and shock impinging a wall with reflection, are studied. The Mach number for the incoming boundary layer is 2.9. Re θ in the numerical simulation is 2400. Two experimental data sets are used, namely those of Bookey et al 1 at the same flow conditions as the DNS and those of Selig 2 at Re θ of about 70,000. Mean velocity profiles, wall pressure distribution, mass flux turbulence intensity, 2D density correlation and locations of the flow separation and reattachment are compared. In addition, an analysis of the turbulence structure characteristics for the DNS data is given.

show abstract

Section: Introductionmentioning

confidence: 99%

Analysis of Shockwave/Turbulent Boundary Layer Interaction Using DNS and Experimental Data

Bookey

Martı́n

et al. 2005

43rd AIAA Aerospace Sciences Meeting and Exhibit

View full text Add to dashboard Cite

show abstract

“…(25)- (27) are given in reference [5]. and three-dimensional interactions [33,34,35,36,7]. While a much smaller number of DNS or wall resolved LES has been performed on such flows [37,38,39,40,41].…”

Section: Lesmentioning

confidence: 99%

Wall-Modeled Large Eddy Simulation of a Three-Dimensional Shock-Boundary Layer Interaction

Marco¹

2018

2018 AIAA Aerospace Sciences Meeting

View full text Add to dashboard Cite

“…Settles et al [12] focused on experimental investigations for a shock wave boundary layer interaction (SWBLI) on swept compression corners. Compression leading edge angles of 16 and 24 were used on all the geometries and these angles caused nearincipient and wall-separated 2D flows at Mach 3.…”

Section: Supersonic Corner Flowsmentioning

confidence: 99%

Supersonic viscous corner flows

Naidoo

Skews

2011

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

Results of numerical and experimental investigations of steady state supersonic viscous corner flows in simplified geometries that resemble typical wing body-fuselage intersections are presented. These flows are numerically calculated using the computational fluid dynamics code of Fluent and include the use of standard turbulence models. Experimental work includes the use of the oil film flow visualization technique to visualize the surface flow patterns. The flows considered are symmetric about the corner bisector. This article focuses on the development of the three shock structure along the various geometries, specifically focusing on the formation and growth of the shear layers that result from the Mach reflection. The resultant effects of this shear layer on pressure distributions, shear stress, and changes in Mach numbers are discussed. The shock wave boundary layer interaction is also presented.

show abstract

Investigation of three-dimensional shock/boundary layer interactions at swept compression corners

Cited by 7 publications

References 3 publications

Analysis of Shockwave/Turbulent Boundary Layer Interaction Using DNS and Experimental Data

Analysis of Shockwave/Turbulent Boundary Layer Interaction Using DNS and Experimental Data

Wall-Modeled Large Eddy Simulation of a Three-Dimensional Shock-Boundary Layer Interaction

Supersonic viscous corner flows

Contact Info

Product

Resources

About