Flow visualization methods for separated three-dimensional shock wave/turbulent boundary-layer interactions

Settles, Gary S.; Teng, Hsueh-Ying

doi:10.2514/3.8085

Cited by 68 publications

(15 citation statements)

References 14 publications

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“…Examples are the injection of smoke into the boundary layer of a model (Veret 1985) and painting titanium tetrachloride onto a surface which reacts with ambient water vapor forming a fine smoke (Freymuth et al 1985). Another approach is the use of a high vapor pressure liquid which is bled into the boundary layer of a supersonic flow (Settles and Teng 1983). The large shear forces atomize the liquid, forming a fine aerosol which can then be used for visualization.…”

Section: Introductionmentioning

confidence: 99%

A planar Mie scattering technique for visualizing supersonic mixing flows

Clemens

Mungal

1991

Experiments in Fluids

146

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A planar Mie scattering technique is described which allows for the direct visualization of fluid mixing in supersonic flows. The mixed fluid is visualized by laser light sheet scattering from small alcohol droplets which condense as a result of the mixing of a vapor laden subsonic stream with a cold supersonic stream. Issues related to the formation, growth and size of the droplets are addressed. The technique reveals details of the turbulent structure which are masked by the spatial integration of schlieren and shadowgraph methods. Comparative visualizations using the vapor screen method to uniformly mark the high-speed fluid are also shown.

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Section: Introductionmentioning

confidence: 99%

A planar Mie scattering technique for visualizing supersonic mixing flows

Clemens

Mungal

1991

Experiments in Fluids

146

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“…The upstream influence is readily observed using surface-flow visualization. 3 ' 4 An example of such a pattern is shown in Fig. 2a while its key features are identified in Fig.…”

mentioning

confidence: 99%

Inception length to a fully developed, fin-generated, shock-wave, boundary-layer interaction

Settles

1991

AIAA Journal

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An experimental study of fin-generated, shock-wave, turbulent, boundary-layer interactions confirmed previous observations that, sufficiently far from the fin apex, such interactions become conical. For Mach numbers from 2.5 to 4 and fin angles from 4 to 22 deg, the inception length to conical symmetry was found to increase weakly with Mach number. Also, the inception length was found to depend primarily on the inviscid shock angle, this angle ranging from 21 to 40 deg. The inception length decreased with shock strength and was small (approximately constant at three boundary-layer thicknesses in length) at the largest shock strengths encountered.

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“…Both shock associated noise and mixing noise was also significantly reduced by trailing edge modifications (Samimy et al 1998;Kerechanin et al 2000). The advantage of trailing edge modifications over other techniques such as tabs (Samimy et al 1993;Zaman et al 1994) is that they do not cause any thrust loss (Kim and Samimy 1999).…”

Section: Introductionmentioning

confidence: 99%

“…Surface flow visu alizations were cond ucted by kerosene Lampblack technique (Settles and Teng 1983). Details on surface flow visualizations are available in Kim and Samimy (1999) .…”

Section: Introductionmentioning

confidence: 99%

Supersonic jet noise control via trailing edge modifications

Kim

Lee

2001

KSME International Journal

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Various experimental data, including mixmg areas, cross correlation factors, surface flow patterns on nozzle walls, and far field noise spectra, was used to draw a noise control mechanism in a supersonic jet. In the underexpanded case, mixing of the jet air with ambient air was significantly enhanced as presented before, and mixing noise was also dramatically reduced. Screech tones, in the overexpanded case, were effectively suppressed by trailing edge modifications, although mixing enhancement was not noticeable. From mixing and noise performance of nozzles with modified trailing edges, enhancing mixing through streamwise vortices seems an effective way to reduce mixing noise in the underexpanded flow regime. However, screech tones in the overexpanded flow regime is well controlled or suppressed by making shock cells and/or spanwise large scale structures irregular and/or less organized by a proper selection of trailing edges. The noise field in the overexpanded flow regime was greatly affected by the symmetricity of the nozzle exit geometry. In the underexpanded flow regime, the effects of the symmetricity of the nozzle exit on mixing were negligible.

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Flow visualization methods for separated three-dimensional shock wave/turbulent boundary-layer interactions

Cited by 68 publications

References 14 publications

A planar Mie scattering technique for visualizing supersonic mixing flows

A planar Mie scattering technique for visualizing supersonic mixing flows

Inception length to a fully developed, fin-generated, shock-wave, boundary-layer interaction

Supersonic jet noise control via trailing edge modifications

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