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.
To achieve statistical convergence, the computations for the uncontrolled configurations are advanced in time for approximately 1.5 convective times ( ΛπΏπ₯/Λπ’β)
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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.