Structure of supersonic turbulent flow past a sharp fin

Knight, Doyle; Horstman, C. C.; Shapey, B.; Bogdonoff, S. M.

doi:10.2514/3.9787

Cited by 99 publications

(30 citation statements)

References 17 publications

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“…The plateau and dip have been commonly attributed to a highly swept vortical structure in separated interactions. 18 The data at 5 = 31.8 and 50.8 mm are also evidently in the inception zone and this nonconical behavior will be more vividly seen next.…”

Section: Quasiconical Symmetrymentioning

confidence: 99%

“…3a that is associated with the separated flow is the X-foot structure in which the main, freestream shock bifurcates into a forward, separation shock and a rear, internal shock. The visualizations reveal that the separated boundary layer thickens while pathlines obtained through computer simulations 18 show that the separated flow consists of a highly swept vortical structure. The separation shock appears straight in flow visualization and its angle is i|/ ss .…”

Section: Nomenclaturementioning

confidence: 99%

See 1 more Smart Citation

Quasiconical free interaction between a swept shock and a turbulent boundary layer

1993

AIAA Journal

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Previous observations that fin-generated interactions are quasiconical in nature were further confirmed by surface pressure measurements spanning Mach 2.5-3.5, which encompassed unseparated through strongly separated interactions. For strongly separated interactions in which the shock wave is bifurcated into a X.-foot structure, the conical free interaction hypothesis was validated through an appropriate scaling of the far-field surface pressure distribution. The behavior of the \-foot structure, such as the decrease of the slope of the separation shock with interaction strength, was explained by invoking the conical free interaction hypothesis. Through the conical free interaction hypothesis, it was further shown that the triple-shock intersection behaves in a complicated manner with changes in interaction strength.

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Section: Quasiconical Symmetrymentioning

confidence: 99%

Section: Nomenclaturementioning

confidence: 99%

Quasiconical free interaction between a swept shock and a turbulent boundary layer

1993

AIAA Journal

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“…The necessary additional gas mass in §ows into the separation area between the plate surface and the dividing line DL. Such separation §ow pattern near a ¦n is con¦rmed by the numerical §ow simulation in [4].…”

Section: Flow Patternmentioning

confidence: 93%

“…The separation zone can be divided into two regions [2,4]: the initial region located near the ¦n leading edge and the region of a developed separation distant from the ¦n leading edge. The length of the initial region is about (10 12)δ for the laminar undisturbed boundary layer (δ is the layer£s thickness at the ¦n leading edge), and it is equal to (6 8)δ for the turbulent one [2].…”

Section: Flow Patternmentioning

confidence: 99%

Three-dimensional shock-wave/boundary-layer interaction at the presence of entropy layer

Borovoy

Егоров

Maximenko

et al. 2013

Progress in Flight Physics

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An experimental and numerical investigation of a gas §ow on a §at plate near a single ¦n and a ¦n pair, generating crossings shocks, is performed. The study is focused on the plate bluntness in §uence on the §ow ¦eld and the heat transfer in the interaction region. The experiments are carried out in a short duration wind tunnel at Mach numbers M = 5, 6, and 8 and Reynolds numbers Re ∞L up to 27 · 10 6 . Luminescent substances are used for heat §ux and pressure distribution measurements and for the surface §ow visualization. In addition, the heat §ux is measured with thermocouple sensors. For a numerical §ow simulation, the three-dimensional (3D) Reynolds-averaged Navier Stokes (RANS) equations are solved using the q ω turbulence model. It is found that even a small plate blunting a¨ects heat transfer and pressure distributions signi¦cantly. Moreover, in the case of crossing shocks, it can cause a global transformation of the §ow structure in the area of the interaction between the shock waves and the boundary layer.

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“…The spillage flow is revealed by the oil dots direction in Fig.3 (b). The primary separation zone (S1, R1) and a secondary separation zone (S2, R2) are caused by the interaction between the sidewall induced shock and the baseplate boundary layer [5,6] . The shock subsequently impinge on the sidewall upstream the cowl and a separation zone (S3, R3) is generated, looking like a triangle "∇" with a larger separation near the cowl lip due to the higher back pressure.…”

Section: Resultsmentioning

confidence: 99%

Research on Three-Dimensional Scramjet Inlet

LJ¹,

Yb²,

LH³

et al. 2006

14th AIAA/AHI Space Planes and Hypersonic Systems and Technologies Conference

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Abstract:The three-dimensional compression scramjet inlet has been investigated by using surface oil dot visualization and numerical simulation. The research has revealed the details of the internal flow pattern, which included the structure of the shock waves, the spillage, the spatial vortical structures, and the boundary layer separations etc.. These features determined the performance of the inlet, which gave the mass flow capture ratio of 0.86, total pressure recovery of 0.41. The results showed that the arrangement of the shocks is critical for such kind of inlet. More researches have been carried out to investigate the effect of the cowl shape, and the results showed the flow field would be changed little for the cowls with different shapes but the same internal contraction ratios.

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Structure of supersonic turbulent flow past a sharp fin

Cited by 99 publications

References 17 publications

Quasiconical free interaction between a swept shock and a turbulent boundary layer

Quasiconical free interaction between a swept shock and a turbulent boundary layer

Three-dimensional shock-wave/boundary-layer interaction at the presence of entropy layer

Research on Three-Dimensional Scramjet Inlet

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