454150 Dsmc Simulations of Leading Edge Flat-Plate Boundary Layer Flows at High Mach Number
The variation of streamwise velocity, temperature, number-density, and mean free path along the wall normal direction away from the plate surface is studied. The qualitative nature of the streamwise velocity at high Mach number is similar to those in the incompressible limit (parabolic profile). However, there are important differences. The amplitudes of the streamwise velocity increase as the Mach number increases and turned into a more flatter profile near the wall. There is significant velocity and temperature slip ((Pradhan and Kumaran, J. Fluid Mech-2011); (Kumaran and Pradhan, J. Fluid Mech-2014)) at the surface of the plate, and the slip increases as the Mach number is increased. It is interesting to note that for the highest Mach numbers considered here, the streamwise velocity at the wall exceeds the sound speed, and the flow is supersonic throughout the flow domain. The subsonic region near the wall, expected when a no-slip boundary condition is applied, is not present when there is wall slip at sufficiently high Mach number.
In a compressible leading-edge flat plate boundary layer flows we determine the mean free path at different streamwise direction (x = 0.2, and 0.8m) away from the plate surface and found significant differences due to the variation in the streamwise location. This is due to the variation in the local temperature across the boundary layer by the viscous heating. The leading edge shock wave is evidently captured in the present DSMC simulations. An important finding is that the wall heating (by increasing the wall temperature in the simulations) increases the local mean free path at the wall. However away from the wall the mean free path profiles remains unaffected by the wall heating.
Key words:Compressible boundary layer, leading-edge flat plate, DSMC simulations.
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