C506 Summary Data

These data are theoretical airfoil characteristics for an airfoil designed to be used on an ultralight. Both main wing and flap were specifically designed to work together. These data were generated with the MCARFA program, a 2D inviscid panel code with an integral boundary layer method. Lift coefficients have been crudely corrected to account for separation, but no other corrections have been applied to the data. These data are presented for educational purposes only. Basing the design of any aircraft on these data is not advised.

ChartObject ShapeMain: C505F Flap: F501 25% of Main ChordMain Pivot: (1.035,-0.019)*Main Chord Flap Pivot: (0.250,0.116)*Flap ChordDeflection: 20 degrees

ChartObject VelocitiesMain: C505F Flap: F501 25% of Main ChordChord Reynolds Number: 730,000Deflection: 20 degreesAngle of Attack Variation (degrees)

ChartObject Lift CurveMain: C506F Flap: F501 25% of Main ChordMain Pivot: (1.035,-0.019)*Main Chord Flap Pivot: (0.250,0.116)*Flap ChordChord Reynolds Number = 730,000

ChartObject Drag By Squire Young FormulaMain: C506F Flap: F501 25% of Main ChordMain Pivot: (1.035,-0.019)*Main Chord Flap Pivot: (0.250,0.116)*Flap ChordChord Reynolds Number = 730,000

ChartObject Quarter Chord Pitching MomentMain: C506F Flap: F501 25% of Main ChordMain Pivot: (1.035,-0.019)*Main Chord Flap Pivot: (0.250,0.116)*Flap ChordChord Reynolds Number = 730,000

Last Updated on 4/24/99
By Thomas E. Speer
Email: tspeer@gte.net