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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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