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The transition of hypersonic boundary layer can lead to a several-foldincrease in surface heat flux and skin friction for the aircraft, significantlyimpacting its flight performance. The corrugated wall, as a passive controlmethod for boundary layer flow, also serves as a type of wall microstructure,making its study on the local rarefaction effect of considerable engineeringsignificance. In this study, we employed the conservative discrete unified gasdynamic scheme and utilized a domain-wide numerical simulation method.Initially, we simulated the hypersonic flat plate flow with different depths ofcorrugated walls under the conditions of incoming flow Mach number of 6 andReynolds number of ${{10}^{7}}$. Subsequently, we investigated the effects ofcorrugated walls, including flat plate corrugated walls and wedge corrugatedwalls, under varying Reynolds numbers for an incoming flow Mach number of 6,and discussed the impact of local rarefaction effect of corrugated walls underdifferent Reynolds numbers. By using the local Knudsen number as the criterion,we found that under these conditions, the occurrence of local rarefactioneffect near the corrugated wall due to consecutive failures does not take placewhen the incoming Reynolds number reaches ${{10}^{7}}$ or ${{10}^{6}}$.However, when the incoming Reynolds number drops to ${{10}^{5}}$, the localrarefaction effect near the corrugated wall becomes evident, with theappearance of non-equilibrium effects in translational and rotationaltemperatures of molecules. This phenomenon becomes more pronounced as theReynolds number decreases further.

Hypersonic wave wall flow based on gas kinetic method