Simulation of blunt-fin-induced shock-wave and turbulent boundary-layer interaction

Hung, C. M.; Buning, Pieter G.

doi:10.1017/s0022112085001471

Cited by 113 publications

(29 citation statements)

References 12 publications

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“…12 and 13a of Ref. 4. The results of the computations show that, due to the additional ground effect generated by the secondary vortex, the pressure spike splits into two.…”

Section: E Ricsson 1 Suggests That the Poor Agreeement Betweenmentioning

confidence: 80%

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Comment on 'Critique of turbulence models for shock-induced flow separation'

Hung

1991

AIAA Journal

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“…12 and 13a of Ref. 4. The results of the computations show that, due to the additional ground effect generated by the secondary vortex, the pressure spike splits into two.…”

Section: E Ricsson 1 Suggests That the Poor Agreeement Betweenmentioning

confidence: 80%

“…4 However, all of the previously discussed features have almost nothing to do with the secondary vortex. When the strength of the secondary vortex increases, the shape of the pressure spike will change.…”

Section: E Ricsson 1 Suggests That the Poor Agreeement Betweenmentioning

confidence: 98%

Comment on 'Critique of turbulence models for shock-induced flow separation'

Hung

1991

AIAA Journal

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“…5 These observations are supported by computational studies as well. 6 We used our own experimental results 7 ¡ 9 and the data of other experiments reported in the literature 1,2 to verify universal applicability of Eq. (1).…”

Section: Comment On ª Supersonic Separation With Obstructionsºmentioning

confidence: 99%

Comment on ''Supersonic Separation with Obstructions''

Özcan

Yuceil

1997

AIAA Journal

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V ERMA and Gupta 1 recently presented experimental data for the supersonic turbulent¯ow past a circular cylinder mounted on a¯at plate at a freestream Mach number of M = 1.6. Using their oil¯ow visualization data, Verma and Gupta 1 made an attempt to correlate the primary separation distance S with the cylinder diameter D and the thickness of the undisturbed boundary-layer d .Reference 1 concludedthat the appropriatelength scale for the separation distance is S/ p ( Dd ) (for H > d ) and proposed the following correlation:Reference 1 stated that ª the length scale chosen for nondimensionalizing S cannot be the cylinder diameter D.º This claim is not supported by the vast amount of experimental data reported in the literature. 2 ¡ 4 Westkaemper 3 was among the ® rst investigators who noted that S/ D correlated with H/ D. Settles and Dolling 4 and Dolling and Rodi 5 noted the similarities between the¯ow® elds of cylinders and hemicylindricallyblunted ® ns mounted on a¯at plate. For blunt ® ns, not only the separation distance but also the spanwise development of the¯ow® eld, as well as its vertical extent, depend primarily on diameter D (Ref. 5). The freestream Mach number M and Reynolds number Re have only secondary effects on the scaling in the turbulent¯ow regime. 5 These observations are supported by computational studies as well. 6 We used our own experimental results 7 ¡ 9 and the data of other experiments reported in the literature 1,2 to verify universal applicability of Eq. (1). All of the data utilized in our analysis were obtained for cylindersby oil¯ow visualization. Figure 1 gives the variationof S/ p (Dd ) with H/ d for seven different M and Re d values. Re d is the Reynolds number based on the undisturbed boundary-layer thickness d , which was measured in Ref. 2 and calculated for the other data sets by using the van Driest transformation.Equation(1) (which is shown by a dashed line in Fig. 1) has a maximum at H/ d = 10.2 and does not produce an asymptotic S value for in® nite H . The solid line in Fig. 1 is a plot of the correlation given bywhich ® ts the data more accurately than Eq. (1). However, there is considerable scatter in the data due, mainly, to the effect of D/ d on the correlation. D/ d values for large H/ d are indicated in Fig. 1. S/ p (Dd ) increases with increasing D/ d for H/ d > 6. A de® nite trend does not exist for H/ d < 6. The ranges of D/ d values for the data used in Fig. 1 are 4.2 < D/ d < 16 (Ref. 1), 0.7 < D/ d < 3.3 (Ref. 2), 0.Sedney and Kitchens 2 note that, when S/ D is plottedas a function of H/ d , a strong dependenceon D/ d is observed.(Figure 4 in Ref. 2 shows that S/ D decreaseswith increasing D/ d .) Figure 1 shows that plotting S/ p (Dd ), instead of S/ D, as a function of H/ d does not remove the dependenceon D/ d . Realizing that H/ d is not a suitable correlationparameter,Sedney and Kitchens 2 proposedthe following correlation:(3) where a and b are weak functions of Reynolds number and depend mainly on M (Refs. 2, 4, and 7). The results of Refs. 2 and 7 indic...

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“…For a second example the blunt fin CFD data set [Hung and Buning 1984] has been resampled to a regular grid of 256 3 voxels with 32 bit floating point vectors in order to fit the currently used framework. The visualization of this data set, see figure 8, shows how the cross sections represented by the vector field perpendicular surfaces visualize the change in flow direction at different levels from the surface of the fin.…”

Section: Examplesmentioning

confidence: 99%

Flow field visualization using vector field perpendicular surfaces

Palmerius

Cooper

Ynnerman

2009

Proceedings of the 25th Spring Conference on Computer Graphics

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This paper introduces Vector Field Perpendicular Surfaces as a means to represent vector data with special focus on variations across the vectors in the field. These surfaces are a perpendicular analogue to streamlines, with the vector data always being parallel to the normals of the surface. In this way the orientation of the data is conveyed to the viewer, while providing a continuous representation across the vectors of the field. This paper describes the properties of such surfaces including an issue with helicity density in the vector data, an approach to generating them, several stop conditions and special means to handle also fields with non-zero helicity density.

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Simulation of blunt-fin-induced shock-wave and turbulent boundary-layer interaction

Cited by 113 publications

References 12 publications

Comment on 'Critique of turbulence models for shock-induced flow separation'

Comment on 'Critique of turbulence models for shock-induced flow separation'

Comment on ''Supersonic Separation with Obstructions''

Flow field visualization using vector field perpendicular surfaces

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