Jungmu HUR, Jinhwi KIM, Junhyuk NAM, Jinyoung KIM, Bok Jik LEE

DOI Number: N/A

Conference number: HiSST-2025-127

Laminar–turbulent transition in hypersonic boundary layers causes a large increase in surface heat flux and imposes severe aerothermal loads on vehicles. Passive attenuation of boundary-layer disturbances relevant to laminar–turbulent transition using porous surfaces was investigated on a half-smooth, half-porous sharp cone tested in the Seoul National University Hypersonic Shock Tunnel at Mach 6.76. Two configurations were evaluated, a uniform porous surface tuned to the Mack second-mode band measured on the smooth side, and a non-uniform porous surface that mixed two hole diameters to absorb lower frequencies not attenuated by the uniform surface. Surface-pressure and heat-flux measurements were combined with schlieren visualization to document instability growth and breakdown. On the smooth side, Mack second-mode waves amplified and broke down to turbulence. Both porous surfaces reduced the Mack second-mode peak in the pressure spectra, and the non-uniform porous surface provided greater attenuation. Consistently, the time-averaged surface heat flux on the porous side was reduced by approximately 40% relative to the smooth side. The results indicate that appropriately designed porous surfaces can attenuate Mack second-mode disturbances and reduce associated heating on sharp cones.

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In Categories: 1.Events, 1.HiSST 2025, High-Speed Aerodynamics and Aerothermodynamics with application to hypersonic regimes
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