############################################################################### # # Aerodynamic properties # ############################################################################### # # Set the airfoils # Wing.Airfoil = 'S1223_A' # # Finite wing correction factor. Used to make 2D airfoil data match the 3D wing profiles. # Wing.FWCF = 0.98 * 1.1 # # Oswald efficiency # Wing.o_eff = 0.97 * 1.2 # # Polar slope evaluations # Wing.ClSlopeAt = (0 * ARCDEG, 7 * ARCDEG) Wing.CmSlopeAt = (0 * ARCDEG, 7 * ARCDEG) ############################################################################### # # Control surfaces
else:
Wing.TR.append(chord[i] / chord[i - 1])
Wing.Lam.append(-3 * ARCDEG)
Wing.Gam.append(0.0)
# shiggins: this is dihedral for each section defined by Wing.Fb (invalid if ConstUpper == True)
Wing.ConstUpper = True #top surfaces of the airfoils lie against upper wing surf
#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.Lam = [0 * ARCDEG, 0 * ARCDEG, 0 * ARCDEG] # wing sweep angles
Wing.CEdge = 'LE' # Defines constant edge
Wing.ConstUpper = True
###############################################################################
#
# Aerodynamic properties
#
###############################################################################
#
# 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
#
###############################################################################
#