S821F + NACA 0012

This airfoil was designed to be used for a rigid wing sailing rig with a 20% chord flap.

ChartObject Shape Main: S821F Flap: NACA 0012 25% of Total Chord Main Pivot: (0.96667, 0)*Main Chord Flap Pivot: (-0.10, 0)*Flap Chord Deflection: 20 degrees

ChartObject Velocities Main: S821F Flap: NACA 0012 25% of Total Chord Main Pivot: (0.96667, 0)*Main Chord Flap Pivot: (-0.10, 0)*Flap Chord Deflection: 20 degrees Reynolds Number = 250,000 Angle of Attack Variation (degrees)

ChartObject Boundary Layer Displacement Main: S821F Flap: NACA 0012 25% of Total Chord Main Pivot: (0.96667, 0)*Main Chord Flap Pivot: (-0.10, 0)*Flap Chord Deflection: 20 degrees Reynolds Number = 250,000 Angle of Attack Variation (degrees)

ChartObject Sectional Lift Main: S821F Flap: NACA 0012 25% of Total Chord Main Pivot: (0.96667, 0)*Main Chord Flap Pivot: (-0.10, 0)*Flap Chord Deflection: 20 degrees Reynolds Number = 250,000 Angle of Attack Variation (degrees)

ChartObject Drag Polar Main: S821F Flap: NACA 0012 25% of Total Chord Main Pivot: (0.96667, 0)*Main Chord Flap Pivot: (-0.10, 0)*Flap Chord Deflection: 20 degrees Reynolds Number = 250,000 Angle of Attack Variation (degrees)

ChartObject Transition Location Main: S821F Flap: NACA 0012 25% of Total Chord Main Pivot: (0.96667, 0)*Main Chord Flap Pivot: (-0.10, 0)*Flap Chord Deflection: 20 degrees Reynolds Number = 250,000 Angle of Attack Variation (degrees)

ChartObject Separation Location Main: S821F Flap: NACA 0012 25% of Total Chord Main Pivot: (0.96667, 0)*Main Chord Flap Pivot: (-0.10, 0)*Flap Chord Deflection: 20 degrees Reynolds Number = 250,000 Angle of Attack Variation (degrees)

ChartObject Pitching Moment Main: S821F Flap: NACA 0012 25% of Total Chord Main Pivot: (0.96667, 0)*Main Chord Flap Pivot: (-0.10, 0)*Flap Chord Deflection: 20 degrees Reynolds Number = 250,000 Angle of Attack Variation (degrees) Stall effects on Cm not modeled


Last Updated on 6/17/99
By Thomas E. Speer
Email: tspeer@gte.net