Round root section with a Cd of 0.50 Made by Jason Jonkman 1 Number of airfoil tables in this file 0.0 Table ID parameter 0.0 Stall angle (deg) 0.0 No longer used, enter zero 0.0 No longer used, enter zero 0.0 No longer used, enter zero 0.0 Zero Cn angle of attack (deg) 0.0 Cn slope for zero lift (dimensionless) 0.0 Cn extrapolated to value at positive stall angle of attack 0.0 Cn at stall value for negative angle of attack 0.0 Angle of attack for minimum CD (deg) 0.50 Minimum CD value -180.00 0.000 0.5000 0.000 0.00 0.000 0.5000 0.000 180.00 0.000 0.5000 0.000