Fig. 12From: Adaptive local discontinuous Galerkin methods with semi-implicit time discretizations for the Navier-Stokes equations(a) Adaptive mesh and the contour plots corresponding to P2 solution for supersonic flow past a NACA0012 airfoil, 30 equally spaced contour lines are used to plot (b) Mach number from 0.15 to 2.15, and (c) pressure from 0.61 to 5.41Back to article page