Python ACMainWing.CEdge示例

示例#1

        Wing.Lam.append(0.0)
        Wing.Gam.append(0.0)
    elif i == len(Wing.Fb) - 1:
        Wing.TR.append(chord[i] / chord[i - 1])
        Wing.Lam.append(10 * ARCDEG)
        Wing.Gam.append(0.0)
    else:
        Wing.TR.append(chord[i] / chord[i - 1])
        Wing.Lam.append(-3 * ARCDEG)
        Wing.Gam.append(0.0)

# shiggins: this is dihedral for each section defined by Wing.Fb (invalid if ConstUpper == True)
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)

#==============================================================================#

示例#2

文件： wing_matt.py 项目： Aerothon-2020/TutorialAircraft

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

###############################################################################
#
# 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.

示例#3

###############################################################################
#
# 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]
Wing.Lam = [0 * ARCDEG, 0 * ARCDEG, 0 * ARCDEG]
Wing.Fb = [0.5, 0.9, 1]
Wing.CEdge = 'LE'
Wing.ConstUpper = True

###############################################################################
#
# Aerodynamic properties
#
###############################################################################

#
# Set the airfoils
#
Wing.Airfoil = 'e423'

Wing.o_eff = 0.98
Wing.FWCF = 0.98

示例#4

文件： Wing.py 项目： Aerothon-2020/Adv2020Aircraft

Wing.Fb      = [0.598,1.0] #Span Fraction
#Wing.TR      = [1.0,0.4] #Max L/D
#Wing.Fb      = [0.467,1] #Max L/D
#Wing.TR      = [1.0,0.2] #Max CL
#Wing.Fb      = [0.53,1] #Max CL
#Wing.TR      = [1.0,0.3] #Max e
#Wing.Fb      = [0.467,1] #Max e
#===============================================================================
# 
#===============================================================================

Wing.Gam     = [ 0*ARCDEG,0*ARCDEG]
Wing.Lam     = [ 0*ARCDEG,0*ARCDEG]

#Wing.SweepFc = 0.5
Wing.CEdge   = 'LE' #LE of wing to be tapered or constant LE
Wing.ConstUpper = False

#
# Add Vertical Winglets

#Wing.AddWinglet("Winglet",2)
#Winglet = Wing.Winglets.Winglet
#
#Winglet.b = 3 *IN
#Winglet.Airfoil = 'NACA0006'
#Winglet.Lam = [0*ARCDEG, 0*ARCDEG]
#Winglet.Gam = [0*ARCDEG, 0*ARCDEG]
#Winglet.Fb  = [0.1, 1.0]
#Winglet.TR  = [0.25, 0.5]
#Winglet.SweepFc = 0