Hypersonic laminar–turbulent transition on circular cones and scramjet forebodies

Schneider, Steven P.

doi:10.1016/j.paerosci.2003.11.001

Cited by 357 publications

(122 citation statements)

References 174 publications

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“…Small leading edge bluntness moves the boundary layer transition backwards, but an increase of bluntness radius leads to some shift of transition forward. Reverse of boundary layer transition at the cone blunting is known [6,7]. Backward shift of boundary layer transition at the bluntness increase can be explained easily: it is caused by the decrease of Reynolds number calculated with entropy layer characteristics and by entropy layer elongation (before its absorption by boundary layer) at the increase of bluntness radius r. But it is more complicated to explain reversive shift of boundary layer transition forward at further increase of bluntness radius.…”

Section: Resultsmentioning

confidence: 99%

Temperature sensitive paint application for investigation of boundary layer transition in short-duration wind tunnels

Borovoy

Mosharov

Noev

et al. 2012

Progress in Flight Physics

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Application of Temperature Senstive Paint (TSP) technology for investigation of boundary layer transition in short-duration wind tunnels is presented. Investigations were made on sharp and blunted §at plates in UT-1 wind tunnel of TsAGI operated in Ludwieg scheme at Mach numbers 5, 6, and 8 (Reynolds numbers from 5.5 · 10 6 to 26 · 10 6 ). Both natural and induced boundary layer transitions were investigated. BACKGROUNDTemperature Sensitive Paint method is a very e¨ective optical technique for heat §ux measurements. It provides the pattern of heat transfer rates on the whole visible model surface that is essential for three-dimensional (3D) §ows. In few recent years, this technique is successfully developed in TsAGI for short-duration wind tunnels [1,2].Temperature Sensitive Paint is a specially developed paint containing speci¦c luminophore which luminescence depends on temperature. Being excited by the light of appropriate spectral range, the TSP emits the luminescent light of longer wavelength range, and luminescent light intensity decreases with an increase of temperature. Thus, the temperature distribution can be determined in each point of investigated surface from noncontact optical measurement of TSP luminescence intensity by acquiring an image of the whole investigated surface. But luminescence intensity depends not only on temperature but also on excitation light intensity and TSP thickness. To exclude an e¨ect of excitation light intensity and TSP thickness, it is necessary to acquire second reference image of investigated surface at known temperature. Normalization of active image (acquired at unknown temperature distribution) on reference image exclude an e¨ects of Progress in Flight Physics 3 (2012) 15-24

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Section: Resultsmentioning

confidence: 99%

Temperature sensitive paint application for investigation of boundary layer transition in short-duration wind tunnels

Borovoy

Mosharov

Noev

et al. 2012

Progress in Flight Physics

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show abstract

“…Clarification of the transition mechanism and prediction of the transition have been attempted and numerous studies have been conducted analytically, numerically and experimentally. [1][2][3][4][5][6][7] It is known that several factors affect the transition. The transition Reynolds number increases with increases in Mach number and unit Reynolds number.…”

Section: Introductionmentioning

confidence: 99%

Conservation-Law Approach to Prediction of Boundary Layer Transition

Kanda¹

2011

Trans. Japan Soc. Aero. S Sci.

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The boundary layer transition is predicted using the law of mass conservation. The increasing ratio of the boundary layer thickness to the laminar boundary layer thickness at the transition is introduced. Formulas and equations for laminar and turbulent boundary layers are used to predict the transition Reynolds number. The effect of the momentum deficit at the leading edge is also incorporated in this approach under compressible flow conditions. The calculated transition Reynolds number shows reasonable agreement with the experimental results. Under the compressible flow conditions, the calculation simulates the bucket of the transition Reynolds number with a Mach number, the change in the transition Reynolds number due to wall cooling, and the increase in the transition Reynolds number with increase in the bluntness Reynolds number.

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“…The small decrease of the term of the boundary layer thickness ratios and the decrease of the mean friction coefficient result an increase of the length of the transition region in Eq. (6). The experimental results of Horvath et al are between the calculated results by the two wall conditions in Fig.…”

Section: Compressible Boundary Layermentioning

confidence: 66%

“…The calculated length of the transition region is a function of the ratios of the boundary layer thicknesses to the 99% velocity thickness and the mean friction coefficient as shown in Eq. (6). The ratios of the laminar boundary layer are shown in Fig.…”

Section: Compressible Boundary Layermentioning

confidence: 99%

“…Studies to clarify the phenomena in the transition region and the transition mechanism, and to predict the transition have been conducted analytically, numerically and experimentally. [1][2][3][4][5][6] The author has previously presented a prediction model of the boundary layer transition Reynolds number using the law of mass conservation. 7) The model was applied to a flat-plate flow and a cone flow in an incompressible flow and a compressible flow.…”

Section: Introductionmentioning

confidence: 99%

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A Conservation-Law Approach to Predicting the Length of the Boundary Layer Transition Region

Kanda

2012

Trans. Japan Soc. Aero. S Sci.

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The length of the boundary layer transition region is predicted by the conservation of momentum, based on the prediction method of the boundary layer transition by the mass conservation. The predicted length decreased in line with wall cooling and an increase of Mach number. Some calculated lengths agreed with experimental results, and others did not. To examine the insufficient agreement, the effect of the wall temperature on the length is discussed. Under the heated-upstream wall condition, which may appear in hypersonic wind tunnel experiments, the length of the transition region and the transition Reynolds number increased in line with the wall cooling in the prediction calculation. Most of the experimental data are in the region between the calculated results with this heated-upstream wall condition and those with the uniform wall-temperature condition. The similarity of the results predicted by the energy conservation to those predicted by the momentum conservation is also discussed.

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Hypersonic laminar–turbulent transition on circular cones and scramjet forebodies

Cited by 357 publications

References 174 publications

Temperature sensitive paint application for investigation of boundary layer transition in short-duration wind tunnels

Temperature sensitive paint application for investigation of boundary layer transition in short-duration wind tunnels

Conservation-Law Approach to Prediction of Boundary Layer Transition

A Conservation-Law Approach to Predicting the Length of the Boundary Layer Transition Region

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