General Aviation Externally Flapped Airfoil

These data are purely theoretical, and were generated using the MCARFA program, a 2D inviscid panel code with and integral boundary layer method. Lift coefficients were crudely corrected for separation, but no corrections were applied to any of the other data. These data are presented for educational purposes only. Basing any aircraft design on these data is not advised.

ChartObject Shape Main: GA30-612 Flap: GA37-315 25% of Main Chord Main Pivot: (1.05,-0.05)*Main Chord Flap Pivot: (0.25,0.00)*Flap Chord Deflection: 20 degrees

ChartObject Velocities Main: GA30-612 Flap: GA37-315 25% of Main Chord Chord Reynolds Number: 2,000,000 Deflection: 20 degrees Angle of Attack Variation (degrees)

ChartObject Shape Main: GA30-612 Flap: GA37-315 25% of Main Chord Main Pivot: (1.05,-0.05)*Main Chord Flap Pivot: (0.25,0.00)*Flap Chord Deflection: 15 degrees

ChartObject Velocities Main: GA30-612 Flap: GA37-315 25% of Main Chord Chord Reynolds Number: 2,000,000 Deflection: 15 degrees Angle of Attack Variation (degrees)

ChartObject Shape Main: GA30-612 Flap: GA37-315 25% of Main Chord Main Pivot: (1.05,-0.05)*Main Chord Flap Pivot: (0.25,0.00)*Flap Chord Deflection: 10 degrees

ChartObject Velocities Main: GA30-612 Flap: GA37-315 25% of Main Chord Chord Reynolds Number: 2,000,000 Deflection: 10 degrees Angle of Attack Variation (degrees)

ChartObject Shape Main: GA30-612 Flap: GA37-315 25% of Main Chord Main Pivot: (1.05,-0.05)*Main Chord Flap Pivot: (0.25,0.00)*Flap Chord Deflection: 5 degrees

ChartObject Velocities Main: GA30-612 Flap: GA37-315 25% of Main Chord Chord Reynolds Number: 2,000,000 Deflection: 5 degrees Angle of Attack Variation (degrees)

ChartObject Shape Main: GA30-612 Flap: GA37-315 25% of Main Chord Main Pivot: (1.05,-0.05)*Main Chord Flap Pivot: (0.25,0.00)*Flap Chord Deflection: 0 degrees

ChartObject Velocities Main: GA30-612 Flap: GA37-315 25% of Main Chord Chord Reynolds Number: 2,000,000 Deflection: 0 degrees Angle of Attack Variation (degrees)

ChartObject Shape Main: GA30-612 Flap: GA37-315 25% of Main Chord Main Pivot: (1.05,-0.05)*Main Chord Flap Pivot: (0.25,0.00)*Flap Chord Deflection: -5 degrees

ChartObject Velocities Main: GA30-612 Flap: GA37-315 25% of Main Chord Chord Reynolds Number: 2,000,000 Deflection: -5 degrees Angle of Attack Variation (degrees)

ChartObject Shape Main: GA30-612 Flap: GA37-315 25% of Main Chord Main Pivot: (1.05,-0.05)*Main Chord Flap Pivot: (0.25,0.00)*Flap Chord Deflection: -10 degrees

ChartObject Velocities Main: GA30-612 Flap: GA37-315 25% of Main Chord Chord Reynolds Number: 2,000,000 Deflection: -10 degrees Angle of Attack Variation (degrees)

ChartObject Lift Curve Main: GA30-612 Flap: GA37-315 25% of Main Chord Main Pivot: (1.05,-0.05)*Main Chord Flap Pivot: (0.25,0.00)*Flap Chord Chord Reynolds Number = 2,000,000

ChartObject Drag By Squire Young Formula Main: GA30-612 Flap: GA37-315 25% of Main Chord Main Pivot: (1.05,-0.05)*Main Chord Flap Pivot: (0.25,0.00)*Flap Chord Chord Reynolds Number = 2,000,000

ChartObject Drag By Squire Young Formula Main: GA30-612 Flap: GA37-315 25% of Main Chord Main Pivot: (1.05,-0.05)*Main Chord Flap Pivot: (0.25,0.00)*Flap Chord Chord Reynolds Number = 2,000,000

ChartObject Quarter Chord Pitching Moment Main: GA30-612 Flap: GA37-315 25% of Main Chord Main Pivot: (1.05,-0.05)*Main Chord Flap Pivot: (0.25,0.00)*Flap Chord Chord Reynolds Number = 2,000,000

ChartObject Quarter Chord Pitching Moment Main: GA30-612 Flap: GA37-315 25% of Main Chord Main Pivot: (1.05,-0.05)*Main Chord Flap Pivot: (0.25,0.00)*Flap Chord Chord Reynolds Number = 2,000,000

ChartObject Flap Element Aerodynamic Moment Main: GA30-612 Flap: GA37-315 25% of Main Chord Main Pivot: (1.05,-0.05)*Main Chord Flap Pivot: (0.25,0.00)*Flap Chord Chord Reynolds Number = 2,000,000 No Separation Effects Modelled

ChartObject Flap Element Axial Load Main: GA30-612 Flap: GA37-315 25% of Main Chord Main Pivot: (1.05,-0.05)*Main Chord Flap Pivot: (0.25,0.00)*Flap Chord Chord Reynolds Number = 2,000,000 No Separation Effects Modelled

ChartObject Flap Element Normal Load Main: GA30-612 Flap: GA37-315 25% of Main Chord Main Pivot: (1.05,-0.05)*Main Chord Flap Pivot: (0.25,0.00)*Flap Chord Chord Reynolds Number = 2,000,000 No Separation Effects Modelled

ChartObject Main Element Aerodynamic Moment Main: GA30-612 Flap: GA37-315 25% of Main Chord Main Pivot: (1.05,-0.05)*Main Chord Flap Pivot: (0.25,0.00)*Flap Chord Chord Reynolds Number = 2,000,000 No Separation Effects Modelled

ChartObject Main Element Axial Load Main: GA30-612 Flap: GA37-315 25% of Main Chord Main Pivot: (1.05,-0.05)*Main Chord Flap Pivot: (0.25,0.00)*Flap Chord Chord Reynolds Number = 2,000,000 No Separation Effects Modelled

ChartObject Main Element Normal Load Main: GA30-612 Flap: GA37-315 25% of Main Chord Main Pivot: (1.05,-0.05)*Main Chord Flap Pivot: (0.25,0.00)*Flap Chord Chord Reynolds Number = 2,000,000 No Separation Effects Modelled

ChartObject Flap Element Aerodynamic Moment Main: GA30-612 Flap: GA37-315 25% of Main Chord Main Pivot: (1.05,-0.05)*Main Chord Flap Pivot: (0.25,0.00)*Flap Chord Chord Reynolds Number = 2,000,000 No Separation Effects Modelled

ChartObject Flap Element Axial Load Main: GA30-612 Flap: GA37-315 25% of Main Chord Main Pivot: (1.05,-0.05)*Main Chord Flap Pivot: (0.25,0.00)*Flap Chord Chord Reynolds Number = 2,000,000 No Separation Effects Modelled

ChartObject Flap Element Normal Load Main: GA30-612 Flap: GA37-315 25% of Main Chord Main Pivot: (1.05,-0.05)*Main Chord Flap Pivot: (0.25,0.00)*Flap Chord Chord Reynolds Number = 2,000,000 No Separation Effects Modelled

ChartObject Main Element Aerodynamic Moment Main: GA30-612 Flap: GA37-315 25% of Main Chord Main Pivot: (1.05,-0.05)*Main Chord Flap Pivot: (0.25,0.00)*Flap Chord Chord Reynolds Number = 2,000,000 No Separation Effects Modelled

ChartObject Main Element Axial Load Main: GA30-612 Flap: GA37-315 25% of Main Chord Main Pivot: (1.05,-0.05)*Main Chord Flap Pivot: (0.25,0.00)*Flap Chord Chord Reynolds Number = 2,000,000 No Separation Effects Modelled

ChartObject Main Element Normal Load Main: GA30-612 Flap: GA37-315 25% of Main Chord Main Pivot: (1.05,-0.05)*Main Chord Flap Pivot: (0.25,0.00)*Flap Chord Chord Reynolds Number = 2,000,000 No Separation Effects Modelled

ChartObject Main Element Aerodynamic Moment Main: C506F Flap: F501 25% of Main Chord Main Pivot: (1.035,-0.019)*Main Chord Flap Pivot: (0.250,0.116)*Flap Chord Chord Reynolds Number = 730,000 No Separation Effects Modelled

ChartObject Flap Element Aerodynamic Moment Main: C506F Flap: F501 25% of Main Chord Main Pivot: (1.035,-0.019)*Main Chord Flap Pivot: (0.250,0.116)*Flap Chord Chord Reynolds Number = 730,000 No Separation Effects Modelled


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