**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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