from __future__ import division # let 5/2 = 2.5 rather than 2 from scalar.units import LBF, SEC, ARCDEG, FT, IN, SLUG from scalar.units import AsUnit from Aerothon.ACWing import ACMainWing from Aerothon.DefaultMaterialsLibrary import PinkFoam, Monokote, Basswood, Balsa from Aerothon.ACWingWeight import ACSolidWing, ACRibWing # # Create the wing # Wing = ACMainWing(1) Wing.Lift_LO = 35 * LBF Wing.V_max_climb = 65 * FT / SEC Wing.V_Stall = 35 * FT / SEC Wing.Alt_LO = 920 * FT #Wing.AR = 5.0 Wing.b = 95 * IN ############################################################################### # # Geometric properties # ############################################################################### Wing.FullWing = True #Wing.UpperWing.b = 4.5*FT #Wing.LowerWing.b = 4*FT Wing.TR = [1, 0.85, 1] Wing.Gam = [0 * ARCDEG, 0 * ARCDEG, 0 * ARCDEG]
from __future__ import division # let 5/2 = 2.5 rather than 2 from scalar.units import LBF, SEC, ARCDEG, FT, IN, SLUG from scalar.units import AsUnit from Aerothon.ACWing import ACMainWing from Aerothon.DefaultMaterialsLibrary import PinkFoam, Monokote, Basswood, Balsa from Aerothon.ACWingWeight import ACSolidWing, ACRibWing # # Create the wing # Wing = ACMainWing(1) Wing.Lift_LO = 60 * LBF # Desired lift at liftoff Wing.V_max_climb = 65 * FT / SEC # liftoff speed Wing.Alt_LO = 200 * FT # liftoff altitude Wing.AR = 8.0 # Aspect Ratio Wing.b = 12 * 12 * IN # Wingspan ############################################################################### # # Geometric properties # ############################################################################### Wing.FullWing = True Wing.Fb = [0.4, 0.8, 1] # Span fraction corresponding to inputs below Wing.TR = [1, 0.8, .7] # Taper ratio Wing.Gam = [20 * ARCDEG, 20 * ARCDEG, 20 * ARCDEG] # Dihedral Wing.Lam = [0 * ARCDEG, 0 * ARCDEG, 0 * ARCDEG] # wing sweep angles Wing.CEdge = 'LE' # Defines constant edge Wing.ConstUpper = True