S907F + NACA 0012 Flap

This section was designed to be used in a rigid wing sailing rig with a 30% chord flap.

ChartObject Shape Main: S907F Flap: NACA 0012 30% of Total Chord Main Pivot: (0.95714, 0)*Main Chord Flap Pivot: (-0.1, 0)*Flap Chord Deflection: 20 degrees

ChartObject Velocities Main: S907F Flap: NACA 0012 30% of Total Chord Main Pivot: (0.95714, 0)*Main Chord Flap Pivot: (-0.1, 0)*Flap Chord Deflection: 20 degrees Reynolds Number = 250,000 Angle of Attack Variation (degrees)

ChartObject Boundary Layer Displacement Main: S907F Flap: NACA 0012 30% of Total Chord Main Pivot: (0.95714, 0)*Main Chord Flap Pivot: (-0.1, 0)*Flap Chord Deflection: 20 degrees Reynolds Number = 250,000 Angle of Attack Variation (degrees)

ChartObject Sectional Lift Main: S907F Flap: NACA 0012 30% of Total Chord Main Pivot: (0.95714, 0)*Main Chord Flap Pivot: (-0.1, 0)*Flap Chord Deflection: 20 degrees Reynolds Number = 250,000 Angle of Attack Variation (degrees)

ChartObject Drag Polar Main: S907F Flap: NACA 0012 30% of Total Chord Main Pivot: (0.95714, 0)*Main Chord Flap Pivot: (-0.1, 0)*Flap Chord Deflection: 20 degrees Reynolds Number = 250,000 Angle of Attack Variation (degrees)

ChartObject Pitching Moment Main: S907F Flap: NACA 0012 30% of Total Chord Main Pivot: (0.95714, 0)*Main Chord Flap Pivot: (-0.1, 0)*Flap Chord Deflection: 20 degrees Reynolds Number = 250,000 Angle of Attack Variation (degrees) Stall effects on Cm not modeled

ChartObject Transition Location Main: S907F Flap: NACA 0012 30% of Total Chord Main Pivot: (0.95714, 0)*Main Chord Flap Pivot: (-0.1, 0)*Flap Chord Deflection: 20 degrees Reynolds Number = 250,000 Angle of Attack Variation (degrees)

ChartObject Separation Location Main: S907F Flap: NACA 0012 30% of Total Chord Main Pivot: (0.95714, 0)*Main Chord Flap Pivot: (-0.1, 0)*Flap Chord Deflection: 20 degrees Reynolds Number = 250,000 Angle of Attack Variation (degrees)


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