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The boundary layer in hypersonic regimes—typically defined by free-stream Mach numbers exceeding five—exhibits a complex interplay of compressibility, high thermal gradients and non-equilibrium ...
This study experimentally investigates the effects of nose-tip bluntness on boundary-layer transition over a \(7^\circ\) half-angle cone at Mach 6.76, using the Seoul National University Hypersonic ...