Measurements of Heat Transfer Rates in Separated Regions in a Shock Tube and in a Shock Tunnel

Rom, Josef

doi:10.2514/3.2040

Cited by 9 publications

(6 citation statements)

References 2 publications

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“…L sep (0.023 m),ā δ (384.2 ms -1 ) and U e (1283.6 ms -1 ) are evaluated from the mesh converged numerical solution to the eight degree flare case and St is assumed to be 0.01 [2,3,10]. Table 4 shows a comparison between the experimental surface pressure and heat-transfer establishment times compared to the wave and heat-transfer times.…”

Section: B Heat Transfer and Wave Timesmentioning

confidence: 99%

“…A number of studies have previously examined the establishment times of separations either experimentally [1,2,3,9,10,11], numerically [7,8] or both [12,13,14,15]. A number of different methods of assessing establishment have emerged, although very few studies even discuss their establishment criteria.…”

Section: Previous Literaturementioning

confidence: 99%

“…Assuming typical Stanton numbers for a turbulent flow in a supersonic intermittent facility, St= 0.01 [2,3,10], it is possible estimate the ratio of heat transfer times to wave times:…”

Section: Previous Literaturementioning

confidence: 99%

“…More recently Mallinson et al [6] conducted a dedicated study where they examine establishment times from their own data on a compression corner and that of others [1,2,12], as shown in figure 2. Here a normalization is employed that uses total enthalpy (h 0 ) to expresses establishment times in terms of 'flow lengths':…”

Section: Previous Literaturementioning

confidence: 99%

“…Early studies were relatively rigorous in examining establishment of experiments within intermittent facilities [1,2]. Knowledge of establishment times was very limited and significant effort was expended to ensure the tunnel flow would be established before a model was made.…”

Section: Introductionmentioning

confidence: 99%

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Establishment Times of Hypersonic Shock-Wave/Boundary-Layer Interactions in Intermittent Facilities

2017

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This study examines establishment times of shock-wave boundary-layer interactions across a range of interaction types and intermittent facilities. Successful design of a test-article for a short duration facility is difficult, especially when trying to guarantee establishment of the flow. While this study does not detail design methodologies of a test article it does aim to provide better understanding of establishment metrics and predictive methods that have emerged from other studies in order to help in the design and assessment of experiments. Experimental and numerical data was taken at Mach 8.9 on an axisymmetric blunt-nosed body with an eight degree flare and laminar boundary-layer. It is shown that the global applicability of any single metric is poor and hence an establishment criteria is developed for this study which provides a more global metric of establishment. Further, a framework is provided for when the use of existing establishment metrics is appropriate.

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Section: B Heat Transfer and Wave Timesmentioning

confidence: 99%

Section: Previous Literaturementioning

confidence: 99%

“…Assuming typical Stanton numbers for a turbulent flow in a supersonic intermittent facility, St= 0.01 [2,3,10], it is possible estimate the ratio of heat transfer times to wave times:…”

Section: Previous Literaturementioning

confidence: 99%

Section: Previous Literaturementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Establishment Times of Hypersonic Shock-Wave/Boundary-Layer Interactions in Intermittent Facilities

2017

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Establishment of steady separated flow over a compression-corner in a free-piston shock tunnel

1997

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Experimental investigation of axisymmetric hypersonic shock-wave/turbulent-boundary-layer interactions

2013

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This paper presents time-averaged data for high-Reynolds-number hypersonic shock-wave/boundary-layer interactions, using a body of revolution to achieve high standards of two-dimensionality. The data are collected at nominal Mach 8.9, but a calibration is included that permits weak flow gradients in the test section to be incorporated as part of the data interpretation or flow modelling. The axisymmetric turbulent test boundary layer is developed on a hollow cylinder, aligned axially with the flow. The shock-wave interaction with this boundary layer is then generated by two separate configurations. Firstly, an impinging shock-wave case, that uses a concentric cowl to radiate an axisymmetric shock system onto the test boundary layer: for this case both an attached flow and a separated flow interaction are formed. Secondly, use of a conical-flare afterbody to produce a separated flow interaction. Quantitative data are presented for surface pressures and heat transfer, supported by some schlieren visualization and surface oil flows. A restricted CFD programme is included to assist the interpretation of the experiments.

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Measurements of Heat Transfer Rates in Separated Regions in a Shock Tube and in a Shock Tunnel

Cited by 9 publications

References 2 publications

Establishment Times of Hypersonic Shock-Wave/Boundary-Layer Interactions in Intermittent Facilities

Establishment Times of Hypersonic Shock-Wave/Boundary-Layer Interactions in Intermittent Facilities

Establishment of steady separated flow over a compression-corner in a free-piston shock tunnel

Experimental investigation of axisymmetric hypersonic shock-wave/turbulent-boundary-layer interactions

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