The following computations were performed using the new cartesian grid generation routine. The method features our original boundary scheme for compressible flows.

Figure 1: NACA 0012 Pressure Contours, M = 0.30

Figure 2: Surface Cp, M = 0.3

Figure 3: Circular Cylinder Pressure Contours, M = 0.20

Figure 4: Circular Cylinder Surface Cp, M = 0.20

Figure 5: MultiElement Airfoil, Pressure Distribution, M=0.20

Figure 6: Surface Cp for M = 0.20

Figure 7: 5-Element Airfoil, Pressure Distribution, M=0.227

Figure 8: Surface Cp for 5-Element Airfoil, M=.227

Figure 9: 5-Element Airfoil with Spoiler, Mach Number Distribution, M=0.227

Figure 10: Surface Cp for 5-Element Airfoil with Spoiler

Figure 11: Transonic Airfoil past RAE 2822, M=0.729

Figure 12: Surface Cp for RAE 2822, M=.729

Figure 13: Supersonic Flat Plate, 10 deg, M = 3.0

Figure 14: Surface Mach Number, M = 3.0

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