Exemple #1
0
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]
Exemple #2
0
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