Instability Measurements on a Cone-Slice-Flap in Mach-6 Quiet Flow

Francis, Adelbert A.; Dylewicz, Kamil; Klothakis, Angelos; Theofilis, Vassilios; Jewell, Joseph S.

doi:10.2514/6.2024-0500

AIAA SCITECH 2024 Forum 2024

DOI: 10.2514/6.2024-0500

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Instability Measurements on a Cone-Slice-Flap in Mach-6 Quiet Flow

Adelbert A. Francis,

Kamil Dylewicz,

Angelos Klothakis

et al.

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2024

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Cited by 1 publication

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Relaminarization effects in hypersonic flow on a three-dimensional expansion–compression geometry

Pandey,

Casper,

Beresh

2024

J. Fluid Mech.

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This experimental work explores the flow field around a three-dimensional expansion–compression geometry on a slender cone at Mach 8 using high-frequency pressure sensors, high-frame-rate schlieren, temperature-sensitive paint, shear-stress measurements and oil-flow visualizations. The $7^\circ$ cone geometry has a hyperbolic slice which acts as an expansion corner and suppresses the disturbances present in the upstream boundary layer. Downstream of the cone-slice corner, high-frequency boundary-layer disturbances attenuate in all cases. Under laminar conditions, second-mode instabilities from the cone diminish and lower-frequency second-mode waves develop on the slice at a frequency commensurate with the increased boundary layer thickness. For fully turbulent cases, the boundary layer over the slice shows evidence of a two-layered nature with a turbulent outer region and a near-wall region with strong attenuation of high-frequency disturbances and reappearance of lower-frequency instability waves. When a downstream compression ramp is added to the slice, the expanded boundary layer shows enhanced susceptibility to separation such that separation is observed at a $10^{\circ }$ deflection, which is smaller than expected for turbulent conditions. For a $30^{\circ }$ ramp, boundary-layer separation occurs further upstream where the heat flux contours show a decrease in heating that is characteristic of a transitional separation. These results demonstrate the effect of relaminarization caused by an upstream expansion on a subsequent shock-wave/boundary-layer interaction.

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Relaminarization effects in hypersonic flow on a three-dimensional expansion–compression geometry

Pandey,

Casper,

Beresh

2024

J. Fluid Mech.

View full text Add to dashboard Cite

show abstract

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Instability Measurements on a Cone-Slice-Flap in Mach-6 Quiet Flow

Cited by 1 publication

References 20 publications

Relaminarization effects in hypersonic flow on a three-dimensional expansion–compression geometry

Relaminarization effects in hypersonic flow on a three-dimensional expansion–compression geometry

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