Spanwise non-uniform surface temperature creates control streaks that cut high-frequency shear stress by 30% and delay transition for second Mack mode breakdown while reducing peak heat flux for first Mack mode in hypersonic boundary layers.
The aerodynamic heating mechanism is attributed to high-frequency dilatation work due to the second Mack mode
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Control of deterministic breakdown to turbulence of hypersonic boundary layer with spanwise non-uniform surface temperature
Spanwise non-uniform surface temperature creates control streaks that cut high-frequency shear stress by 30% and delay transition for second Mack mode breakdown while reducing peak heat flux for first Mack mode in hypersonic boundary layers.