Tomographic PIV investigation of roughness-induced transition in a hypersonic boundary layer

Avallone, Francesco; Ye, Q.; Schrijer, F.F.J.; Scarano, Fulvio; Cardone, Gennaro

doi:10.1007/s00348-014-1852-z

Cited by 13 publications

(6 citation statements)

References 31 publications

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“…2.4. Particle image velocimetry Due to rapid developments in CCD cameras since the first application of PIV in hypersonic flows (Moraitis & Riethmuller 1988), this technique is now more commonly used in high-speed flows (Scarano 2005;Schrijer, Scarano & van Oudheusden 2006;Sahoo, Papageorge & Smits 2010;Schreyer, Sahoo & Smits 2011;Williams & Smits 2012;Avallone et al 2014). The key issues include the selection of seeding particles, their dispersion in the flow and the analysis of particle image recordings (Scarano 2005).…”

Section: Temperature-sensitive Paintmentioning

confidence: 99%

Newly identified principle for aerodynamic heating in hypersonic flows

et al. 2018

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Instability evolution in a transitional hypersonic boundary layer and its effects on aerodynamic heating are investigated over a 260 mm long flared cone. Experiments are conducted in a Mach 6 wind tunnel using Rayleigh-scattering flow visualization, fast-response pressure sensors, fluorescent temperature-sensitive paint (TSP) and particle image velocimetry (PIV). Calculations are also performed based on both the parabolized stability equations (PSE) and direct numerical simulations (DNS). Four unit Reynolds numbers are studied, 5.4, 7.6, 9.7 and $11.7\times 10^{6}~\text{m}^{-1}$ . It is found that there exist two peaks of surface-temperature rise along the streamwise direction of the model. The first one (denoted as HS) is at the region where the second-mode instability reaches its maximum value. The second one (denoted as HT) is at the region where the transition is completed. Increasing the unit Reynolds number promotes the second-mode dissipation but increases the strength of local aerodynamic heating at HS. Furthermore, the heat generation rates induced by the dilatation and shear processes (respectively denoted as $w_{\unicode[STIX]{x1D703}}$ and $w_{\unicode[STIX]{x1D714}}$ ) were investigated. The former item includes both the pressure work $w_{\unicode[STIX]{x1D703}1}$ and dilatational viscous dissipation $w_{\unicode[STIX]{x1D703}2}$ . The aerodynamic heating in HS mainly arose from the high-frequency compression and expansion of fluid accompanying the second mode. The dilatation heating, especially $w_{\unicode[STIX]{x1D703}1}$ , was more than five times its shear counterpart. In a limited region, the underestimated $w_{\unicode[STIX]{x1D703}2}$ was also larger than $w_{\unicode[STIX]{x1D714}}$ . As the second-mode waves decay downstream, the low-frequency waves continue to grow, with the consequent shear-induced heating increasing. The latter brings about a second, weaker growth of surface-temperature HT. A theoretical analysis is provided to interpret the temperature distribution resulting from the aerodynamic heating.

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Section: Temperature-sensitive Paintmentioning

confidence: 99%

Newly identified principle for aerodynamic heating in hypersonic flows

et al. 2018

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“…This suggests that some coherent vortical structures are still present in the flow. The previous observations coupled with the experimental investigation using Tomographic PIV reported in Avallone et al [32] suggest that the OSP vortices still survive in the transitional region. Starting from the transition location and moving downstream the wake width increases.…”

Section: Figure 5 Reynolds Number Evaluated At the Estimated Transitmentioning

confidence: 72%

“…The strength of the vortices decreases with increasing distance from the roughness elements as clearly visible from the decrease in K in figure 6. The reduction in the heat transfer rate is mainly associated to the weaker SP vortices that are more susceptible to breaking down according to the experimental evidence of Avallone et al [32] and discussion of Iyver and Mahesh [22]. [22].…”

Section: Figure 5 Reynolds Number Evaluated At the Estimated Transitmentioning

confidence: 91%

IR thermography investigation on roughness induced transition in high-speed flows

Avallone¹,

Schrijer²,

Cardone³

2014

Proceedings of the 2014 International Conference on Quantitative InfraRed Thermography

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Boundary layer transition in high-speed flows is a phenomenon that despite extensive research over the years is still extremely hard to predict. The presence of protrusions or gaps can lead to an accelerated laminar-to-turbulent transition enhancing the thermal loads and the skin friction coefficient. In the current investigation, high-resolution heat transfer measurements using infrared thermography are performed on the flow past several different roughness geometries (cylinders and pizza-box) at free stream Mach number equal to 7.5 and three unit Reynolds number (14 • 10 , 11 • 10 , 8 • 10 ). The roughness elements are applied on a plate that is oriented at a 5° angle of attack with respect to the flow direction. For each Reynolds number the roughness element is positioned at 30 mm and at 60 mm from the leading edge. The measurements establish the roughness effectiveness in promoting transition and they provide insight into the flow topology.

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“…Avallone et al. 220 employed tomographic PIV to study the roughness-induced transition in a hypersonic boundary layer at Mach 7.5. In their work, a 200 mJ/pulse Nd:YAG laser (Quantel Evergreen) and 400 nm TiO 2 seeding particles were used in the PIV setup.…”

Section: Flow-field Diagnosticsmentioning

confidence: 99%

“…Planar PIV techniques that were mentioned above can only measure two velocity components for a cross-section of a flow, whereas tomographic PIV can be used to show the instantaneous 3D velocity of volumetric flows. Avallone et al 220 employed tomographic PIV to study the roughnessinduced transition in a hypersonic boundary layer at Mach 7.5. In their work, a 200 mJ/pulse Nd:YAG laser (Quantel Evergreen) and 400 nm TiO 2 seeding particles were used in the PIV setup.…”

Section: Particle Imaging Velocimetrymentioning

confidence: 99%

Advanced Laser-Based Techniques for Gas-Phase Diagnostics in Combustion and Aerospace Engineering

Ehn

Zhu

et al. 2017

Appl Spectrosc

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Gaining information of species, temperature, and velocity distributions in turbulent combustion and high-speed reactive flows is challenging, particularly for conducting measurements without influencing the experimental object itself. The use of optical and spectroscopic techniques, and in particular laser-based diagnostics, has shown outstanding abilities for performing non-intrusive in situ diagnostics. The development of instrumentation, such as robust lasers with high pulse energy, ultra-short pulse duration, and high repetition rate along with digitized cameras exhibiting high sensitivity, large dynamic range, and frame rates on the order of MHz, has opened up for temporally and spatially resolved volumetric measurements of extreme dynamics and complexities. The aim of this article is to present selected important laser-based techniques for gas-phase diagnostics focusing on their applications in combustion and aerospace engineering. Applicable laser-based techniques for investigations of turbulent flows and combustion such as planar laser-induced fluorescence, Raman and Rayleigh scattering, coherent anti-Stokes Raman scattering, laser-induced grating scattering, particle image velocimetry, laser Doppler anemometry, and tomographic imaging are reviewed and described with some background physics. In addition, demands on instrumentation are further discussed to give insight in the possibilities that are offered by laser flow diagnostics.

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Tomographic PIV investigation of roughness-induced transition in a hypersonic boundary layer

Cited by 13 publications

References 31 publications

Newly identified principle for aerodynamic heating in hypersonic flows

Newly identified principle for aerodynamic heating in hypersonic flows

IR thermography investigation on roughness induced transition in high-speed flows

Advanced Laser-Based Techniques for Gas-Phase Diagnostics in Combustion and Aerospace Engineering

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