#Wing.SweepFc = 0.75 # shiggins 151107: not sure how this is calculated
Wing.CEdge = 'LE' #LE of wing to be tapered or constant LE, shiggins 151107: will override LAM
#==============================================================================#
# Aerodynamic properties
#==============================================================================#
# Finite wing correction factor: make 2D airfoil data match the 3D wing profile
Wing.FWCF = 0.98
# Oswald efficiency
Wing.o_eff = 0.97
# Polar slope evaluations
Wing.ClSlopeAt = (0 * ARCDEG, 7 * ARCDEG)
Wing.CmSlopeAt = (0 * ARCDEG, 7 * ARCDEG)
#==============================================================================#
# Control Surfaces
#==============================================================================#
# Define the control surfaces
Wing.AddControl('Aileron')
Wing.Aileron.Fc = 0.30 # chord length of the aileron
Wing.Aileron.Fb = ((6 * 3.25) / 52.0) #Span of the aileron
Wing.Aileron.Ft = 0.0 #Adjusted to make Aileron begin at a Wing rib
Wing.Aileron.SgnDup = -1.0
Wing.Aileron.Weight = 0.01 * LBF
Wing.Aileron.WeightGroup = "MainWing"
Wing.Aileron.Servo.Fc = 0.47
###############################################################################
#
# Set the airfoils
#
Wing.Airfoil = 'e423'
Wing.o_eff = 0.98
Wing.FWCF = 0.98
#
# Polar slope evaluations
#
Wing.ClSlopeAt = (6 * ARCDEG, 7 * ARCDEG)
Wing.CmSlopeAt = (-1 * ARCDEG, 0 * ARCDEG)
###############################################################################
#
# Control surfaces
#
###############################################################################
#
# Define the control surfaces
#
Wing.AddControl('Aileron')
Wing.Aileron.Fc = 0.25
Wing.Aileron.Fb = 0.4
Wing.Aileron.Ft = 0.1
Wing.Aileron.SgnDup = -1.
Wing.Airfoil = 'S1223_TC'
#
# Finite wing correction factor. Used to make 2D airfoil data match the 3D wing profiles.
#
Wing.FWCF = 0.98
#
# Oswald efficiency
#
Wing.o_eff = 0.98
#
# Polar slope evaluations
#
Wing.ClSlopeAt = (0*ARCDEG, 15*ARCDEG)
Wing.CmSlopeAt = (0*ARCDEG, 15*ARCDEG)
###############################################################################
#
# Control surfaces
#
###############################################################################
#
# Define the control surfaces
#
Wing.AddControl('Aileron')
Wing.Aileron.Fc = 0.250
Wing.Aileron.Fb = 1-0.66 #Adjusted to make Aileron begin at a Wing rib
Wing.Aileron.Ft = 0.0 #Adjusted to make Aileron end at a Wing rib
Wing.Aileron.SgnDup = -1.
#
###############################################################################
#
# Set the airfoils
#
Wing.Airfoil = 'CLi4005b' # Chooses airfoil from /AircraftDesign/Airfoils.. just load in normal .dat files like you would to xflr5
Wing.o_eff = 0.98 # Oswald Efficiency
Wing.FWCF = 0.98 # I'm... not srue what this does it isn't referenced in any calculations.
#
# Polar slope evaluations
#
Wing.ClSlopeAt = (6 * ARCDEG, 7 * ARCDEG
) # Just the range that the polars will be drawn
Wing.CmSlopeAt = (-1 * ARCDEG, 0 * ARCDEG) # Range polars will be drawn
###############################################################################
#
# Control surfaces
#
###############################################################################
#
# Define the control surfaces
#
Wing.AddControl('Aileron')
Wing.Aileron.Fc = 0.25 # Percentage of chord aileron will take up
Wing.Aileron.Fb = 0.3 # Percentage of span
Wing.Aileron.Ft = 0.2 # Percentage distance from tip
Wing.Aileron.SgnDup = -1.