S902F + NACA 0012 Flap

This section was designed to be used in a rigid wing sailing rig with a 40% chord flap.

ChartObject Shape
Main: S902F  Flap: NACA 0012  40% of Total Chord
Main Pivot: (0.90, 0)*Main Chord 
Flap Pivot: (-0.15, 0)*Flap Chord
Deflection: 20 degrees

ChartObject Velocities
Main: S902F  Flap: NACA 0012  40% of Total Chord
Main Pivot: (0.90, 0)*Main Chord 
Flap Pivot: (-0.15, 0)*Flap Chord
Deflection: 20 degrees
Reynolds Number = 250,000
Angle of Attack Variation (degrees)

ChartObject Boundary Layer Displacement
Main: S902F  Flap: NACA 0012  40% of Total Chord
Main Pivot: (0.90, 0)*Main Chord 
Flap Pivot: (-0.15, 0)*Flap Chord
Deflection: 20 degrees
Reynolds Number = 250,000
Angle of Attack Variation (degrees)

ChartObject Sectional Lift
Main: S902F  Flap: NACA 0012  40% of Total Chord
Main Pivot: (0.90, 0)*Main Chord 
Flap Pivot: (-0.15, 0)*Flap Chord
Deflection: 20 degrees
Reynolds Number = 250,000
Angle of Attack Variation (degrees)

ChartObject Drag Polar
Main: S902F  Flap: NACA 0012  40% of Total Chord
Main Pivot: (0.90, 0)*Main Chord 
Flap Pivot: (-0.15, 0)*Flap Chord
Deflection: 20 degrees
Reynolds Number = 250,000
Angle of Attack Variation (degrees)

ChartObject Pitching Moment
Main: S902F  Flap: NACA 0012  40% of Total Chord
Main Pivot: (0.90, 0)*Main Chord 
Flap Pivot: (-0.15, 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: S902F  Flap: NACA 0012  40% of Total Chord
Main Pivot: (0.90, 0)*Main Chord 
Flap Pivot: (-0.15, 0)*Flap Chord
Deflection: 20 degrees
Reynolds Number = 250,000
Angle of Attack Variation (degrees)

ChartObject Separation Location
Main: S902F  Flap: NACA 0012  40% of Total Chord
Main Pivot: (0.90, 0)*Main Chord 
Flap Pivot: (-0.15, 0)*Flap Chord
Deflection: 20 degrees
Reynolds Number = 250,000
Angle of Attack Variation (degrees)

ChartObject Drag Polar Comparisons
Main: S902F  Flap: NACA 0012  40% of Total Chord
Main Pivot: (0.90, 0)*Main Chord 
Flap Pivot: (-0.15, 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