Influence of roughness on attachment line boundary layer transition in hypersonic flow

Bénard, Emmanuel; Gaillard, Ludovic Le; Roquefort, T. Alziary de

doi:10.1007/s003480050050

Cited by 13 publications

(6 citation statements)

References 9 publications

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“…39 Results show that the data are generally in agreement with the correlation obtained by Creel A larger body of data exists regarding 2D roughness, usually trip wires applied around the leading edge. Figure 15 compares 2D tape strip data for HIFiRE-5 to other transition data from 2D trips on cylinders by Murakami et al, 40 Benard et al, 41 and Da Costa, as cited in Benard. Data with arrows represent bounding values only.…”

Section: A Discrete Roughness Correlations For the Frustummentioning

confidence: 97%

HIFiRE-5 Flight Vehicle Design

Kimmel

Adamczak

Berger

et al. 2010

40th Fluid Dynamics Conference and Exhibit

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The Hypersonic International Flight Research Experimentation (HIFiRE) program is a hypersonic flight test program executed by the Air Force Research Laboratories (AFRL)and Australian Defence Science and Technology Organization (DSTO). HIFiRE flight 5 is devoted to measuring transition on a three-dimensional body. This paper summarizes payload configuration, trajectory, vehicle stability limits and roughness tolerances. Results show that the proposed configuration is suitable for testing transition on a three-dimensional body. Transition is predicted to occur within the test window, and a design has been developed that will allow the vehicle to be manufactured within prescribed roughness tolerances. I. Nomenclature

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Section: A Discrete Roughness Correlations For the Frustummentioning

confidence: 97%

HIFiRE-5 Flight Vehicle Design

Kimmel

Adamczak

Berger

et al. 2010

40th Fluid Dynamics Conference and Exhibit

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“…al. 16 gives a good summary of the literature in this area. Creel et al, 17 studied these ows in the low-disturbancesupersonic wind tunnel at NASA Langley Research Center.…”

Section: Attachment Line Transitionmentioning

confidence: 99%

Experimental Investigation of High-Enthalpy Effects on Attachment-Line Boundary-Layer Transition

Fujii¹,

Hornung

2003

AIAA Journal

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A series of experiments was performed on high-enthalpy effects on hypersonic boundary-layer transition using nitrogen, air, and carbon dioxide as test gases in the T5 hypervelocity shock tunnel. Previous experiments on a sharp cone showed signi cant high enthalpy effects. This series concerns the attachment line boundary layer on swept cylinders with sweep angles of 60 and 45 deg. The observed trend of transition Reynolds number with enthalpy, which is found to be similar to that in the cone results, shows strong transition delay at the larger sweep angle for carbon dioxide, whereas no signi cant effect is observed in nitrogen and air. The acoustic wave absorption rate due to relaxation shows a quite similar trend in enthalpy dependence to transition Reynolds number for the carbon dioxide case. This suggests that the dominant effect in delaying transition in the case is vibrational relaxation. The comparisons between the magnitude of the strongest ampli cation rate from an inviscid linear stability analysis and the absorption rate due to relaxation show that they are of the same order of magnitude for carbon dioxide and that absorption is not signi cant for nitrogen or air, which supports the stated understanding of the effect of relaxation on transition. Nomenclature

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“…Through the collection of pairs ðR Ã tr1 ; kÞ for all the locations along the attachment-line, it appears that the threshold of transition onset does not vary appreciably downstream of the source of disturbance [20]. However, the transitional extent, k, changes quickly downstream of the roughness element and tends to reach an quasi-asymptotic value of k % 10 for this particular case (Fig.…”

Section: Transitional Regime Modelingmentioning

confidence: 86%

“…This would suggest that transition cannot happen suddenly, even for quasi-asymptotic conditions. For R Ã tr1 % 250, which is the transition threshold for bypass configurations proposed in [19] by using PollÕs approximation and since checked numerous times [20], a good approximation of the transitional extent could be deduced:…”

Section: Transitional Regime Modelingmentioning

confidence: 99%

“…In most of the experiments carried out at high speed thermal methods of transition detection have been used, such as change of the adiabatic wall temperature in supersonic regime [19] and increase of heat transfer. Both detection methods have demonstrated that when transition is forced by a roughness element, a critical roughness height, below which no influence is detected, can be defined as a function of the local Mach number [20]. Within this context, it is also shown that the Reynolds number used in the studies of attachment-line flows following the definition proposed by Poll [14], and noted R Ã , is a valid parameter to predict transition for the case of large disturbances.…”

Section: Introductionmentioning

confidence: 99%

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Transitional and turbulent heat transfer of swept cylinder attachment line in hypersonic flow

Bénard¹,

Cooper

Sidorenko

2006

International Journal of Heat and Mass Transfer

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A wide range of experimental results carried out in low enthalpy facilities is used to sustain simple correlations predicting heat transfer rates on an attachment line in hypersonic flow. It is observed that for long swept cylinders a nearly asymptotic state can be reached for which transition Reynolds number does not change substantially quite far from the apex of the cylinder. Intermittency based on measured heat fluxes was used to describe the laminar-turbulent process. Prediction of turbulent heat transfer rates is established using a reference temperature method that provides quick and relatively accurate estimates for a wide range of Mach number and temperature ratio.

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Influence of roughness on attachment line boundary layer transition in hypersonic flow

Cited by 13 publications

References 9 publications

HIFiRE-5 Flight Vehicle Design

HIFiRE-5 Flight Vehicle Design

Experimental Investigation of High-Enthalpy Effects on Attachment-Line Boundary-Layer Transition

Transitional and turbulent heat transfer of swept cylinder attachment line in hypersonic flow

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