Fig. 12
(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 5.41
Fig. 12 | Advances in Aerodynamics