Python ACMainWing.Lift_LO 예제들

예제 #1

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

예제 #2

from scalar.units import LBF, SEC, ARCDEG, FT, IN, SLUG, OZF, OZM
from scalar.units import AsUnit
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)

예제 #3

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
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

예제 #4

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]

예제 #5

from scalar.units import LBF, SEC, ARCDEG, FT, IN, SLUG, OZF, OZM
from scalar.units import AsUnit
from Aerothon.DefaultMaterialsLibrary import PinkFoam, Monokote, Basswood,\
     Balsa, Ultracote, Poplar, AluminumBalsa
from Aerothon.ACWing import ACMainWing
from Aerothon.ACWingWeight import ACSolidWing, ACRibWing

#==============================================================================#
# WING MODEL
#==============================================================================#
# Create the wing
Wing = ACMainWing(1)
Wing.Airfoil = 'S1223_TC'  # will probably stick with this airfoil because of past trade studies

# lift-off conditions
Wing.Lift_LO = 60 * LBF  # aircraft max weight is 55lbs, will keep at 60lbs for safety factor
#Wing.V_Stall = 38 * FT/SEC #SPH: where does this come from?
Wing.Alt_LO = 197 * FT  # approximation for elevation in Ft. Worth, TX

# wing geometry (to launch 54.5 pounds under 200 feet)
Wing.b = 143.5 * IN  # wing span
Wing.S = 3300 * IN**2  # wing surface area using a constant chord length of 25in

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
### Straight Tapered Wing
##Wing.Fb = [0.2, 1.0] # Wingspan Position (0 to 1)

예제 #6

파일: wing_matt.py 프로젝트: Aerothon-2020/TutorialAircraft

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

예제 #7

파일: wing_carter.py 프로젝트: Aerothon-2020/Reg2019Aircraft

from scalar.units import LBF, SEC, ARCDEG, FT, IN, SLUG, OZF, OZM
from scalar.units import AsUnit
from Aerothon.DefaultMaterialsLibrary import PinkFoam, Monokote, Basswood,\
     Balsa, Ultracote, Poplar, AluminumBalsa
from Aerothon.ACWing import ACMainWing
from Aerothon.ACWingWeight import ACSolidWing, ACRibWing

#==============================================================================#
# WING MODEL
#==============================================================================#
# Create the wing
Wing = ACMainWing(1)
Wing.Airfoil = 'S1223'

# lift-off conditions
Wing.Lift_LO = 60 * LBF  # Should this be 55 lbs or are you just playing it safe?
#Wing.V_Stall = 38 * FT/SEC #SPH: where does this come from?
Wing.Alt_LO = 197 * FT  # approximation for elevation in Ft. Worth, TX

# wing geometry (to launch 54.5 pounds under 200 feet)
Wing.b = 144 * IN  # wing span
Wing.S = 3744 * IN**2  # wing surface area (was 3695.04)
# More realistic 12 ft wing
#Wing.b = 144*IN      # wing span
#Wing.S = 20*FT**2  # wing surface area

Wing.FullWing = True

# Wing Chord vs Position
### Box Wing
##Wing.Fb = [1.0 ] # Wingspan Position (0 to 1)

예제 #8

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

예제 #9

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 = 24 * IN
#Wing.V_Stall = 32.5* FT/SEC
Wing.S = 1.604 * 144 * IN**2
Wing.Lift_LO = 9 / 16 * 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