Correlation of laminar-turbulent transition data over flat plates in supersonic/hypersonic flow including leading edge bluntness effects

Simeonides, G.

doi:10.1007/s00193-003-0184-3

Cited by 12 publications

(6 citation statements)

References 12 publications

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“…Thus, for all the cases, the boundary layer over the flat plate without shock impingement is expected to be laminar based on the correlation for transitional Reynolds number of hypersonic flows [16]. However, subsequent to flow separation the shear layer can become transitional; this cannot be substantiated from the present experimental data, and hence is not a concern of the present study.…”

Section: Note On Boundary Layer Characteristicsmentioning

confidence: 66%

Correlation for Length of Impinging Shock-Induced Large Separation Bubble at Hypersonic Speed

Sriram

Jagadeesh

2015

AIAA Journal

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Section: Note On Boundary Layer Characteristicsmentioning

confidence: 66%

Correlation for Length of Impinging Shock-Induced Large Separation Bubble at Hypersonic Speed

Sriram

Jagadeesh

2015

AIAA Journal

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“…To estimate transition onset location and transition zone length, ESA applied the criteria of Simeonides [9][10][11] [12]. These take into account the leading edge bluntness thickness which is defined as twice the leading edge curvature radius.…”

Section: Figure 3planes and Sections Considered For The Transition Amentioning

confidence: 99%

Boundary Layer Transition Assessment on a Slender High-Speed Vehicle

Steelant¹,

Passaro²,

Villace³

et al. 2017

21st AIAA International Space Planes and Hypersonics Technologies Conference

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To anticipate the aerodynamic performance of a slender high-speed vehicle throughout a trajectory, the correct determination of transition onset and extent are crucial parameters in the overall evaluation. Though various methods and correlations are worked out on canonical geometries such as flat plates and cones, the present paper will primarily focus on a slender high-speed vehicle concept. Apart from small leading edge radii and 3D flow effects, also practical considerations are included such as gaps and steps indivertibly present due to manufacturing and integration, differential thermal expansion at dissimilar material interfaces, joints etc... A preliminary assessment based on empirical correlations is challenged by a detailed experimental campaign supported by numerical CFD computations. Their applicability range and their limitations are assessed related to the observed flow phenomena.

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“…For the Reynolds numbers based on the distance of shock impingement location from leading edge ranging from 3 × 10 4 to 3.8 × 10 5 for all the cases, the boundary layer over the flat plate without shock impingement is expected to be laminar (35) . However, after the separation, the flow can be transitional or turbulent, especially as the separated shear layer travels a good distance.…”

Section: Flow Morphology and Evolutionmentioning

confidence: 99%

Shock-tunnel investigations on the evolution and morphology of shock-induced large separation bubbles

Sriram

Jagadeesh

2016

Aeronaut. j.

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Shock-tunnel experiments are carried out to study the strong interaction between an impinging shock wave and boundary layer on a flat plate, accompanied bylargeseparation bubble with a length comparable to the distance of the location of shock impingement from the leading edge of the plate. For nominal freestream Mach numbers ranging from 6 to 8.5, moderate to high total enthalpies of 1.3MJ/kg to 6MJ/kg are simulated in the Indian Institute of Science's hypersonic shock tunnels HST-2 (a conventional Hypersonic Shock Tunnel) and Free Piston Shock Tunnel (FPST) with freestream Reynolds numbers ranging from 4 × 106/m to 0.3 × 106/m. The strong impinging shock is generated by a wedge (or shock generator) at an angle of 30.96° to the freestream. From the time-resolved Schlieren flow visualisations using a high-speed camera and surface pressure measurements on the flat plate using fast response sensors, a statistically steady flow field with a large separation bubble was established within the short test time of the shock tunnels (around 600µs in HST-2 and 300µs in FPST). The role of various parameters on the interaction – Mach number, location of shock impingement and flow total enthalpy – are investigated from the measured separation length and surface pressure distribution. For the nominal Mach number of 8.5, with shock impingement at 100mm from the leading edge, the separation length increased from 60mm to 70mm as the total enthalpy is increased from 1.6MJ/kg to 2.4MJ/kg; whereas it dropped drastically to 30-40mm at 6MJ/kg. This is due to the prominence of real gas effects at higher enthalpies.

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Correlation of laminar-turbulent transition data over flat plates in supersonic/hypersonic flow including leading edge bluntness effects

Cited by 12 publications

References 12 publications

Correlation for Length of Impinging Shock-Induced Large Separation Bubble at Hypersonic Speed

Correlation for Length of Impinging Shock-Induced Large Separation Bubble at Hypersonic Speed

Boundary Layer Transition Assessment on a Slender High-Speed Vehicle

Shock-tunnel investigations on the evolution and morphology of shock-induced large separation bubbles

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