from __future__ import division # let 5/2 = 2.5 rather than 2 from scalar.units import LBF, SEC, ARCDEG, FT, IN, SLUG, OZF, OZM from scalar.units import AsUnit from Aerothon.ACWing import ACMainWing from Aerothon.DefaultMaterialsLibrary import PinkFoam, Monokote, Basswood, Balsa, Ultracote, AluminumTube, Aluminum from Aerothon.ACWingWeight import ACSolidWing, ACRibWing # # Create the wing # Wing = ACMainWing(1) Wing.b = 144 *IN #Wing.V_Stall = 32.5* FT/SEC Wing.S = 3024*IN**2 Wing.Lift_LO = 60*LBF Wing.Alt_LO = 721 * FT Wing.V_LOstall = 1.1 ############################################################################### # # Geometric properties # ############################################################################### Wing.FullWing = True #Wing.UpperWing.b = 6*FT #Wing.LowerWing.b = 6*FT #=============================================================================== #b=150,S=3200
from Aerothon.DefaultMaterialsLibrary import PinkFoam, Monokote, Basswood,\
Balsa, Ultracote, Poplar
from Aerothon.ACWing import ACMainWing
from Aerothon.ACWingWeight import ACSolidWing, ACRibWing
#==============================================================================#
# WING MODEL
#==============================================================================#
# Create the wing
Wing = ACMainWing(1)
Wing.Airfoil = 'S1223_TC'
# lift-off conditions
Wing.Lift_LO = 55 * LBF # 151107: shiggins guess
#Wing.V_Stall = 38 * FT/SEC #SPH: where does this come from?
Wing.Alt_LO = 710 * FT # approximation for elevation in Ft. Worth, TX
# wing geometry (to launch 54.5 pounds under 200 feet)
#Wing.b = 188*IN # wing span
#Wing.S = 22*FT**2 # wing surface area
# More realistic 12 ft wing
Wing.b = 144 * IN # wing span
Wing.S = 18 * FT**2 # wing surface area
Wing.FullWing = True
# Wing Chord vs Position
# Box Wing
Wing.Fb = [1.0] # Wingspan Position (0 to 1)
chord = [1.0] # Chord at Position with relation to nominal chord
# Tapered Wing
from scalar.units import LBF, SEC, ARCDEG, FT, IN, SLUG, OZF, OZM from scalar.units import AsUnit from Aerothon.ACWing import ACMainWing from Aerothon.DefaultMaterialsLibrary import PinkFoam, Monokote, Basswood, Balsa, Ultracote from Aerothon.ACWingWeight import ACSolidWing, ACRibWing # # Create the wing # Wing = ACMainWing(1) Wing.Lift_LO = None Wing.b = 148 * IN Wing.V_Stall = 38 * FT / SEC Wing.S = 3485 * IN**2 #Wing.Lift_LO = 55*LBF Wing.Alt_LO = 1150 * FT #Look what it typically is in marietta during the competition ############################################################################### # # Geometric properties # ############################################################################### Wing.FullWing = True #Wing.UpperWing.b = 4.5*FT #Wing.LowerWing.b = 4*FT #=============================================================================== #b=150,S=3200 #===============================================================================
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
from __future__ import division # let 5/2 = 2.5 rather than 2 from scalar.units import LBF, SEC, ARCDEG, FT, IN, SLUG, OZF, OZM from scalar.units import AsUnit from Aerothon.ACWing import ACMainWing from Aerothon.DefaultMaterialsLibrary import PinkFoam, Monokote, Basswood, Balsa, Ultracote, AluminumTube, Aluminum, CarbonTube from Aerothon.ACWingWeight import ACSolidWing, ACRibWing # # Create the wing # Wing = ACMainWing(1) Wing.b = 131.5 *IN #Wing.V_Stall = 32.5* FT/SEC Wing.S = 2966*IN**2 Wing.Lift_LO = 60*LBF Wing.Alt_LO = 653 * FT Wing.V_LOstall = 1.1 ############################################################################### # # Geometric properties # ############################################################################### Wing.FullWing = True #Wing.UpperWing.b = 6*FT #Wing.LowerWing.b = 6*FT #=============================================================================== #b=150,S=3200
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 = 31 * LBF # Desired lift at liftoff Wing.V_max_climb = 65 * FT / SEC # liftoff speed Wing.Alt_LO = 920 * FT # liftoff altitude Wing.AR = 8.0 # Aspect Ratio Wing.b = 96 * 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
from Aerothon.ACWingWeight import ACSolidWing, ACRibWing # # Create the wing # Wing = ACMainWing(1) Wing.Lift_LO = None #Initially 147 inches, changed to 105 inches (0.6 total length) Wing.b = 102 * IN #Initially 38 ft/sec Wing.V_Stall = 38 * FT / SEC # Surface Area of wing Wing.S = 1800 * IN**2 #Wing.Lift_LO = 55*LBF #Was 2000 ft since last year's was in Texas Wing.Alt_LO = 200 * FT #Look what it typically is in Lakeland during the competition ############################################################################### # # Geometric properties # ############################################################################### Wing.FullWing = True #Wing.UpperWing.b = 4.5*FT #Wing.LowerWing.b = 4*FT #=============================================================================== #b=150,S=3200 #===============================================================================
from Aerothon.ACWingWeight import ACSolidWing, ACRibWing # # Create the wing # Wing = ACMainWing(1) Wing.Lift_LO = None #Initially 147 inches, changed to 105 inches (0.6 total length) Wing.b = 105 * IN #96 #Initially 38 ft/sec Wing.V_Stall = 38 * FT / SEC #From Jake's Matlab calculation # Surface Area of wing Wing.S = 2147 * IN**2 #Wing.Lift_LO = 55*LBF #Was 2000 ft since last year's was in Texas Wing.Alt_LO = 200 * FT #Lakeland, FL's elevation ############################################################################### # # Geometric properties # ############################################################################### Wing.FullWing = True #Wing.UpperWing.b = 4.5*FT #Wing.LowerWing.b = 4*FT #=============================================================================== #b=150,S=3200 #===============================================================================