# Set the airfoils 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.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.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"
# # 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 # ############################################################################### # # 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