S901F + NACA 0012 Flap

This airfoil was designed to be used as a rigid wing sail rig with a 50% chord flap.

ChartObject Shape Main: S901F Flap: NACA 0012 50% of Total Chord Main Pivot: (0.90, 0)*Main Chord Flap Pivot: (-0.10, 0)*Flap Chord Deflection: 20 degrees

ChartObject Velocities Main: S901F Flap: NACA 0012 50% of Total Chord Main Pivot: (0.9625, 0)*Main Chord Flap Pivot: (-0.15, 0)*Flap Chord Deflection: 20 degrees Reynolds Number = 2,000,000 Angle of Attack Variation (degrees)

ChartObject Boundary Layer Displacement Main: S901F Flap: NACA 0012 50% of Total Chord Main Pivot: (0.9625, 0)*Main Chord Flap Pivot: (-0.15, 0)*Flap Chord Deflection: 20 degrees Reynolds Number = 2,000,000 Angle of Attack Variation (degrees)

ChartObject Sectional Lift Main: S901F Flap: NACA 0012 50% of Total Chord Main Pivot: (0.9625, 0)*Main Chord Flap Pivot: (-0.15, 0)*Flap Chord Deflection: 20 degrees Reynolds Number = 2,000,000 Angle of Attack Variation (degrees)

ChartObject Drag Polar Main: S901F Flap: NACA 0012 50% of Total Chord Main Pivot: (0.9625, 0)*Main Chord Flap Pivot: (-0.15, 0)*Flap Chord Deflection: 20 degrees Reynolds Number = 2,000,000 Angle of Attack Variation (degrees)

ChartObject Pitching Moment Main: S901F Flap: NACA 0012 50% of Total Chord Main Pivot: (0.9625, 0)*Main Chord Flap Pivot: (-0.15, 0)*Flap Chord Reynolds Number = 2,000,000 Angle of Attack Variation (degrees) Stall effects on Cm not modeled

ChartObject Transition Location Main: S901F Flap: NACA 0012 50% of Total Chord Main Pivot: (0.9625, 0)*Main Chord Flap Pivot: (-0.15, 0)*Flap Chord Deflection: 20 degrees Reynolds Number = 2,000,000 Angle of Attack Variation (degrees)

ChartObject Separation Location Main: S901F Flap: NACA 0012 50% of Total Chord Main Pivot: (0.9625, 0)*Main Chord Flap Pivot: (-0.15, 0)*Flap Chord Deflection: 20 degrees Reynolds Number = 2,000,000 Angle of Attack Variation (degrees)


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