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MultiElement Airfoils 4.1 Validation for New Cartesian Grid Method

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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