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MultiElement Airfoils 4.1 Navier-Stokes Solutions

MultiElement Airfoils can be used to solve the Navier-Stokes equations governing viscous compressible flows. The current capability is for laminar flows with Reynolds numbers less than 50,000. This is useful for analyzing household equipment, hand launched gliders and airfoils for micro UAVs.

The following computations were performed using an automatic cartesian grid generation routine. The method features our original boundary scheme for compressible flows. Designers and engineers can use the new version of MultiElement Airfoils to test unconventional shapes used for sails, race car wing and spoilers and airplane control surfaces.

Figure 1: Flat Plate Grid, M = 0.15, Re=200

Figure 2: Mach Number. Red - 0.2, Blue - 0.0, Re=200

Figure 3: Wall Shear Stress, Symbol- MEFoil, Line - Falkner Skan, Re=200

Figure 4: Wall Friction Coefficient, Symbol- MEFoil, Line - Falkner Skan, Re=200

Figure 5: NACA 0012, M=0.8, Angle=10 Deg.

Figure 6: Mach Number, Red-1.2, Blue-0.0, Upper Seperation at 35% chord.

Figure 7: Surface Pressure Coefficient, Cl=0.55

Figure 8: Surface Friction Coefficient, Profile Cd=0.27

Figure 9: Grid for Extreme Ground Effect Wing, Speed=200 mph

Figure 10: Mach Number, Red-0.5, Blue-0.0

Figure 11: Grid for Paper Airplane Airfoil, Re=1000

Figure 12: Streamlines Around Paper Airplane Airfoil

Figure 13: Pressure Coefficient at Airfoil Surface

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