Laser skin friction measurements and CFD comparison of weak-to-strong swept shock/boundary-layer interactions

Kim, K.-S.; Lee, Y.; Alvi, Farrukh S.; Settles, Gary S.; Horstman, C. C.

doi:10.2514/6.1990-378

Cited by 12 publications

(11 citation statements)

References 13 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Also, post-processing of the solution revealed the existence of a weak secondary vortex. Application of the standard Baldwin-Lomax model resulted in poor results, similar to those reported previously by Kim et al (1991).…”

Section: Introductionsupporting

confidence: 86%

“…There are not enough experimental points in this region to verify this feature. However, in a picture of the oil-film interference-fringe pattern, which Kim et al (1991) include in their paper, a strong fringe peak is clearly seen near the fin. According to these authors, the fringe pattern may be regarded as being qualitatively indicative of the actual skin-friction distribution.…”

Section: Comparison With the Experimentsmentioning

confidence: 89%

“…This procedure is useful for a complex flow structure, where the profiles of the moment of vorticity of the boundary layer exhibit more than two maxima. More recently Panaras & Stanewsky (1992), noting the similarity of the topology of the flow structure between a sharp-fin/plate configuration and a slender body at high incidence, have applied the Panaras & Steger (1988) numerical procedure to the calculation of one of the flows studied at the Pennsylvania State University (Kim et al 1991). They have found that the resulting solution agrees very well with the experimental data of G. Settles and his associates (wall pressure, skin friction, surface flow angle).…”

Section: Introductionmentioning

confidence: 99%

“…One of the sharp-fin/plate flows examined by Kim et al (1991) is used as a model. The selected flow is simulated by application of the turbulence modelling procedure of Panaras & Steger (1988) in a upwind Navier-Stokes solver.…”

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

The effect of the structure of swept-shock-wave/turbulent-boundary-layer interactions on turbulence modelling

Panaras¹

1997

J. Fluid Mech.

View full text Add to dashboard Cite

The physical reasons for the difficulty in predicting accurately strong swept-shockwave/turbulent-boundary-layer interactions are investigated. A well-documented sharp-fin/plate flow has been selected as the main test case for analysis. The selected flow is calculated by applying a version of the Baldwin-Lomax turbulence model, which is known to provide reliable results in flows characterized by the appearance of crossflow vortices. After the validation of the results, by comparison with appropriate experimental data, the test case flow is studied by means of stream surfaces which start at the inflow plane, within the undisturbed boundary layer, and which are initially parallel to the plate. Each of these surfaces has been represented by a number of streamlines. Calculation of the spatial evolution of some selected stream surfaces revealed that the inner layers of the undisturbed boundary layer, which are composed of turbulent air, wind around the core of the vortex. However, the outer layers, which are composed of low-turbulence air, fold over the vortex and at the reattachment region penetrate into the separation bubble forming a low-turbulence tongue, which lies along the plate, underneath the vortex. The conical vortex at its initial stage of development is completely composed of turbulent air, but gradually, as it grows linearly in the flow direction, the low-turbulence tongue is formed. Also the tongue grows in the flow direction and penetrates further into the separation region. When it reaches the expansion region inboard of the primary vortex, the secondary vortex starts to be formed at its tip. Examination of additional test cases indicated that the turbulence level of the elongated tongue decreases if the interaction strength increases. The existence of the low-turbulence tongue in strong swept-shockwave/turbulent-boundary-layer interactions creates a mixed-type separation bubble: turbulent in the region of the separation line and almost laminar between the secondary vortex and the reattachment line. This type of separation cannot be simulated accurately with the currently used algebraic turbulence models, because the basic relations of these models are based on the physics of two-dimensional flows, whereas in a separation bubble the whole recirculation region is turbulent. For improving the accuracy of the existing algebraic turbulence models in predicting swept-shockwave/turbulent-boundary-layer interactions, it is necessary to develop new equations for the calculation of the eddy viscosity in the separation region, which will consider the mixed-flow character of the conical vortex. † Present address: PO Box 64053, Athens 15710, Greece.

show abstract

Section: Introductionsupporting

confidence: 86%

Section: Comparison With the Experimentsmentioning

confidence: 89%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

The effect of the structure of swept-shock-wave/turbulent-boundary-layer interactions on turbulence modelling

Panaras¹

1997

J. Fluid Mech.

View full text Add to dashboard Cite

show abstract

“…1). This configuration has been investigated experimentally [1][2][3][4][5][6][7] and computationally [2][3][4][5][6][7][8][9] for a wide range of test conditions. Computations have been successful in predicting the essential features of these flow fields, as well as helping to provide a model for the flow field…”

Section: Introductionmentioning

confidence: 99%

Turbulence Modeling for Sharpfin-Induced Shock Wave/Turbulent Boundary-Layer Interactions

Horstman

1991

Separated Flows and Jets

View full text Add to dashboard Cite

show abstract

Calculation of 3-D Shock Wave-Turbulent Boundary Layer Interactions Generated by Sharp Fins

Knight

1991

Separated Flows and Jets

View full text Add to dashboard Cite

Laser skin friction measurements and CFD comparison of weak-to-strong swept shock/boundary-layer interactions

Cited by 12 publications

References 13 publications

The effect of the structure of swept-shock-wave/turbulent-boundary-layer interactions on turbulence modelling

The effect of the structure of swept-shock-wave/turbulent-boundary-layer interactions on turbulence modelling

Turbulence Modeling for Sharpfin-Induced Shock Wave/Turbulent Boundary-Layer Interactions

Calculation of 3-D Shock Wave-Turbulent Boundary Layer Interactions Generated by Sharp Fins

Contact Info

Product

Resources

About