The interaction of weak shock waves in form of an N -wave with the supersonic laminar boundary layer on a flat plate with blunt leading edge at the free-stream Mach number M = 2.5 is numerically studied. The numerical results are compared with known experimental data. The combined influence of the N -wave and the leading edge bluntness on the laminar-turbulent transition process is discussed.
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Егоров et al. (2024) studied this question.
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