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Figure 10: The geometric configuration of the flow past the plate. In this figure, D is the location that incident shock impinges the plate if the flow were assumed inviscid.

Figure 10 The geometric configuration of the flow past the plate. In this figure, D is the location that incident shock impinges the plate if the flow were assumed inviscid.

Related Figures (17)

Figure 1: The schematic of inviscid fluxes entering and leaving the control volume in generalized coor- dinates. Department Of Mechanical & Aerospace Engineering Carleton University, Ottawa, Canada
Figure 1: The schematic of inviscid fluxes entering and leaving the control volume in generalized coor- dinates. Department Of Mechanical & Aerospace Engineering Carleton University, Ottawa, Canada
Figure 2: Schematic of geometry for the laminar flow over a flat plate.
Figure 2: Schematic of geometry for the laminar flow over a flat plate.
Figure 3: Grids for the flow over the flat plate; 31 grid along the plate and 21 across the plate with the clustering factor 1.7 near the bottom wall.
Figure 3: Grids for the flow over the flat plate; 31 grid along the plate and 21 across the plate with the clustering factor 1.7 near the bottom wall.
Figure 4: comparison of velocity profile for the flow over the flat plate.
Figure 4: comparison of velocity profile for the flow over the flat plate.
Figure 6: Schematic of geometry for the laminar flow between two parallel plates. The dimension of the plate in the z direction is indicated by 6, with b — oO. Figure 5: Comparisons of skin friction along the plate.
Figure 6: Schematic of geometry for the laminar flow between two parallel plates. The dimension of the plate in the z direction is indicated by 6, with b — oO. Figure 5: Comparisons of skin friction along the plate.
Figure 8: Comparisons of velocity profile wu between the two parallel plates.
Figure 8: Comparisons of velocity profile wu between the two parallel plates.
Figure 7: Comparisons of pressure distribution be- tween the two parallel plates.
Figure 7: Comparisons of pressure distribution be- tween the two parallel plates.
Figure 9: Schematic of shock-wave interaction with laminar boundary layer on a flat plate.
Figure 9: Schematic of shock-wave interaction with laminar boundary layer on a flat plate.
Figure 11: Density contours; shock-wave interaction with laminar boundary layer on a flat plate, per- formed by current study.
Figure 11: Density contours; shock-wave interaction with laminar boundary layer on a flat plate, per- formed by current study.
Figure 12: A closer look at the separation bubble generated by a strong enough shock wave impinging on the boundary layer, as obtained by current study.
Figure 12: A closer look at the separation bubble generated by a strong enough shock wave impinging on the boundary layer, as obtained by current study.
Figure 14: Pressure contour for the shock boundary layer interaction, obtained by current study on 201 x 201 grid. Figure 13: Pressure distribution along the line y = 0.01 meter; pressure rise and pressure drop due to the leading edge shock, incident shock, compression wave, expansion fans and re-compression waves are shown here, obtained by current study.
Figure 14: Pressure contour for the shock boundary layer interaction, obtained by current study on 201 x 201 grid. Figure 13: Pressure distribution along the line y = 0.01 meter; pressure rise and pressure drop due to the leading edge shock, incident shock, compression wave, expansion fans and re-compression waves are shown here, obtained by current study.
Figure 16: Comparison of pressure distribution on the wall for viscous and inviscid flow analysis, ob- tained by current study. Figure 15: Pressure contour for the shock impinge- ment to the solid wall, obtained for inviscid flow by current study on 85 x 91 grid.
Figure 16: Comparison of pressure distribution on the wall for viscous and inviscid flow analysis, ob- tained by current study. Figure 15: Pressure contour for the shock impinge- ment to the solid wall, obtained for inviscid flow by current study on 85 x 91 grid.
Figure 17: Comparison of computed pressure distri- bution over the wall with experimental values. The computation is performed in three grid densities.
Figure 17: Comparison of computed pressure distri- bution over the wall with experimental values. The computation is performed in three grid densities.
Figure 18: Comparison of skin friction over the wall with experimental values. The computation is per- formed in three grid density.
Figure 18: Comparison of skin friction over the wall with experimental values. The computation is per- formed in three grid density.
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