An Experimental Contribution to the Flat Plate 2D Compression Ramp, Shock/Boundary Layer Interaction Problem at Mach 14 : Test Case 3.7

Simeonides, G.; Wendt, J. F.

doi:10.1007/978-3-642-76527-8_14

Cited by 2 publications

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“…Test case 2 For the second test case of $2.3, originally presented at the Hypersonic Workshop at Antibes (Desideri et al 1991), the flow was initially assumed to be fully laminar. The calculations, however, exhibited heat transfer distributions on the ramp surface after reattachment that were too low compared with the measurements provided by Simeonides & Wendt (1990). Upon further examination of the data (on the basis of the criteria discussed in $3.2), it was realized that the increase in Reynolds number relative to test case 1 caused the onset of transition to move upstream close to the reattachment point ($53.1, 3.2).…”

Section: 3)mentioning

confidence: 88%

Experimental and computational investigations of hypersonic flow about compression ramps

Simeonides

Haase

1995

J. Fluid Mech.

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Comprehensive results of a joint experimental and computational study of the two-dimensional flow field over flat plate/compression ramp configurations at Mach 14 are presented. These geometries are aimed to simulate, in a simplified manner, the region around deflected control surfaces of hypersonic re-entry vehicles. The test cases considered cover a range of realistic flow conditions with Reynolds numbers to the hinge line varying between 4.5 × 105 and 2.6 × 106 (with a reference length taken as the distance between the leading edge and the hinge line) and a wall-to-total-temperature ratio of 0.12. The combination of flow and geometric parameters gives rise to fully laminar strong shock wave/boundary layer interactions with extensive separation, and transitional interactions with transition occurring near the reattachment point. A fully turbulent interaction is also considered which, however, was only approximately achieved in the experiments by means of excessive tripping of the oncoming hypersonic laminar boundary layer. Emphasis has been placed upon the quality and level of confidence of both experiments and computations, including a discussion on the laminar-turbulent transition process and the associated striation phenomenon. The favourable comparison between the experimental and computational results has profided the grounds for an enhanced understanding of the relevant flow processes and their modelling. Particularly in relation to transitional shock wave/boundary layer interactions, where laminar-turbulent transition is promoted by the adverse pressure gradient and flow concavity in the reattachment region, a method is proposed to compute extreme adverse effects in the interaction region avoiding such inhibiting requirements as transition modelling or turbulence modelling over separated regions.

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Section: 3)mentioning

confidence: 88%