def createAdvDoubleTrapezoidWing(myWing, id, cTip, cRoot, span, Sref, dfus,
phiLE, dihedral, twist, xMAC25, etakf, strUID,
yfus, xRoot, etaEng, tcRoot, tcTip):
'''
This method creates a double trapezoid wing geometry in the 'myWing' parameter.
** Introduced a linear twist distribution from *0* at root to *twist* at tip
@author: Jonas Jepsen
@param myWing: wings CPACS object
@param id: the VAMPzero-id of the wing
@param cTip: length of chord at wing tip [m]
@param cRoot: length of chord at wing root [m]
@param span: span of the wing [m]
@param Sref: reference area [m^2]
@param dfus: fuselage diameter [m]
@param phiLE: sweep angle at the leading edge [deg]
@param dihedral: dihedralangle of the wing [deg]
@param twist: twist of the outer wing section [deg]
@param etakf: dimensionless span coordinate [-]
@param strUID: the CPACS-uID of the wing
'''
# sections and positionings will be created, all existing sections and positionings will be deleted
mySections = wingSectionsType()
myPositionings = positioningsType()
# calc Lvl 1 parameters
taperRatio = (cTip / cRoot)
cRoot, cKink, cTip = calcWing(span, Sref, taperRatio, phiLE, etakf, dfus)
# calc length from span, sweep and dihedral
sweep_rad = phiLE / 180. * pi
dihedral_rad = dihedral / 180. * pi
# trying to correct the commented statement that uses dfus. will try to use yfus
# length1 = dfus / 2.
length1 = yfus
length2 = (etakf * span / 2. -
length1) / cos(sweep_rad) / cos(dihedral_rad)
length3 = span / 2. * (1 - etakf) / cos(sweep_rad) / cos(dihedral_rad)
# Increase (or reduce the twist by 4deg as that is the overall angle of incidence of the wing)
twist = twist - 4.
twistgrad = twist / (span / 2.)
twist1 = twistgrad * length1
twist2 = twistgrad * etakf * (span / 2.)
twist3 = twist
createWingSection(mySections, tcRoot / 0.09, 0., 0., 0., cRoot, 1., cRoot,
0., 0., 0., 'NACA0009', 1, strUID + '_Sec1',
strUID + '_Sec1', strUID + '_Sec1')
createWingSection(mySections, tcRoot / 0.18, 0., 0., 0., cRoot, 1., cRoot,
0., 0., 0., 'NACA653218', 1, strUID + '_Sec2',
strUID + '_Sec2', strUID + '_Sec2')
createWingSection(mySections, tcTip / 0.18, 0., 0., 0., cKink, 1., cKink,
0., twist2, 0., 'NACA653218', 1, strUID + '_Sec3',
strUID + '_Sec3', strUID + '_Sec3')
createWingSection(mySections, tcTip / 0.18, 0., 0., 0., cTip, 1., cTip, 0.,
twist3, 0., 'NACA653218', 1, strUID + '_Sec4',
strUID + '_Sec4', strUID + '_Sec4')
createPositioning(myPositionings,
str(id) + '_Pos1', None,
str(id) + '_Sec1', 0., 0., 0., id)
createPositioning(myPositionings,
str(id) + '_Pos2',
str(id) + '_Sec1',
str(id) + '_Sec2', length1, 0., 0., id)
createPositioning(myPositionings,
str(id) + '_Pos3',
str(id) + '_Sec2',
str(id) + '_Sec3', length2, phiLE, dihedral, id)
createPositioning(myPositionings,
str(id) + '_Pos4',
str(id) + '_Sec3',
str(id) + '_Sec4', length3, phiLE, dihedral, id)
myWing.set_sections(mySections)
myWing.set_positionings(myPositionings)
createWingSegments(myWing, strUID, 3)
createComponentSegment(myWing, strUID)
etafus = yfus / (span / 2.)
# Ribs outboard of the Fuselage section are placed at 0.8 m distance
nouterRibs = int(ceil((0.95 - etafus - 0.05) * span / 2. / 0.8))
createRibs(myWing.get_componentSegments().get_componentSegment()[0],
strUID,
'advDoubletrapezoid',
etaFus=etafus,
nRibs=nouterRibs,
etaEng=etaEng,
span=span / 2.)
createSpars(myWing.get_componentSegments().get_componentSegment()[0],
strUID,
'advDoubletrapezoid',
length1 / (span / 2.),
etakf / cos(dihedral_rad),
cTip=cTip,
cRoot=cRoot)
createShell(myWing.get_componentSegments().get_componentSegment()[0],
strUID, 'advDoubletrapezoid')
createWingFuselageAttachment(
myWing.get_componentSegments().get_componentSegment()[0], strUID,
'advDoubletrapezoid')
# Estimate ribNum of outer Rib
iRib = int(span * (0.85 - etaEng) / (2 * 0.8)) - 1
createTanks(myWing.get_componentSegments().get_componentSegment()[0],
strUID,
'advDoubletrapezoid',
nRib=iRib)
# calc wing position
tauK = cTip / cKink
etar = dfus / span
# XN25F = calcXN25F(cRoot, span, phiLE, etar, etakf, tauK, taperRatio)
# xRoot.py = calcXRoot(xMAC25, XN25F)
# set wing x - position and twist
myWing.get_transformation().get_translation().set_x(
doubleBaseType(None, None, None, str(xRoot)))
myWing.get_transformation().get_rotation().set_y(
doubleBaseType(None, None, None, str(4.)))
def createStrutBracedWing(myWing, id, cTip, cRoot, span, Sref, phiLE, dihedral, twist, xMAC25, etaFus, etaStrut, tcRoot, tcTip, xRoot, strUID):
'''
This method creates a double trapezoid wing geometry in the 'myWing' parameter.
@author: Jonas Jepsen
@param myWing: wings CPACS object
@param id: the VAMPzero-id of the wing
@param cTip: length of chord at wing tip [m]
@param cRoot: length of chord at wing root [m]
@param span: span of the wing [m]
@param Sref: reference area [m^2]
@param phiLE: sweep angle at the leading edge [deg]
@param dihedral: dihedralangle of the wing [deg]
@param twist: twist of the outer wing section [deg]
@param etakf: dimensionless span coordinate [-]
@param strUID: the CPACS-uID of the wing
'''
mySections = wingSectionsType()
myPositionings = positioningsType()
# calc Lvl 1 parameters
taperRatio = (cTip/cRoot)
#cRoot, cFuselage, cTip = calcWing(span, Sref, taperRatio, phiLE, etaFus)
cStrut = cRoot+(cTip-cRoot)*(etaStrut-etaFus)/(1-etaFus)
# calc length from span, sweep and dihedral
sweep_rad = phiLE/180. * pi
dihedral_rad = dihedral/180. * pi
length1 = (etaFus*span/2.)
length2 = (etaStrut-etaFus)*span/2/cos(sweep_rad)/cos(dihedral_rad)
length3 = span/2.*(1-etaStrut)/cos(sweep_rad)/cos(dihedral_rad)
# Increase (or reduce the twist by 4deg as that is the overall angle of incidence of the wing)
incidenceAngle = 4.
twist = twist + incidenceAngle
twistgrad = twist / (span / 2.)
twist2 = twistgrad * length2
twist3 = twist
createWingSection(mySections, tcRoot/0.09, 0.,0.,0., cRoot,1.,cRoot, 0.,incidenceAngle,0., 'NACA0009', 1, strUID + '_Sec1', strUID + '_Sec1', strUID + '_Sec1')
createWingSection(mySections, tcRoot / 0.18, 0.,0.,0., cRoot,1.,cRoot, 0.,incidenceAngle,0., 'NACA653218', 1, strUID + '_Sec2', strUID + '_Sec2', strUID + '_Sec2')
createWingSection(mySections, tcRoot / 0.18, 0.,0.,0., cStrut,1.,cStrut, 0.,twist2,0., 'NACA653218', 1, strUID + '_Sec3', strUID + '_Sec3', strUID + '_Sec3')
createWingSection(mySections, tcTip / 0.18, 0.,0.,0., cTip,1.,cTip, 0.,twist3,0., 'NACA653218', 1, strUID + '_Sec4', strUID + '_Sec4', strUID + '_Sec4')
createPositioning(myPositionings,str(id) + '_Pos1',None, str(id) + '_Sec1',0.,0.,0.,id)
createPositioning(myPositionings,str(id) + '_Pos2',str(id) + '_Sec1',str(id) + '_Sec2',length1,0.,0.,id)
createPositioning(myPositionings,str(id) + '_Pos3',str(id) + '_Sec2',str(id) + '_Sec3',length2,phiLE,dihedral,id)
createPositioning(myPositionings,str(id) + '_Pos4',str(id) + '_Sec3',str(id) + '_Sec4',length3,phiLE,dihedral,id)
myWing.set_sections(mySections)
myWing.set_positionings(myPositionings)
createWingSegments(myWing, strUID, 3)
createComponentSegment(myWing, strUID)
# Ribs outboard of the Fuselage section are placed at 0.8 m distance
nouterRibs = int(ceil((0.95 - etaFus - 0.05) * span / 2. / 0.8))
createRibs(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'strutBracedWing', etaFus=etaFus, nRibs=nouterRibs, etaStrut=etaStrut, span=span / 2., phi25 = phiLE)
createSpars(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'strutBracedWing', etaFus=etaFus, cTip=cTip, cRoot=cRoot)
createShell(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'strutBracedWing')
iRib = int(span * (0.9 - etaStrut) / (2 * 0.8)) - 1
if iRib == 1:
iRib = 2
createTanks(myWing.get_componentSegments().get_componentSegment()[0], strUID, typeOfSeg='strutBracedWing', nRib=iRib)
createWingFuselageAttachment(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'advDoubletrapezoid')
# set wing x - position and twist
myWing.get_transformation().get_translation().set_x(doubleBaseType(None, None, None, str(xRoot)))
def createStrutBracedWing(myWing, id, cTip, cRoot, span, Sref, phiLE, dihedral, twist, xMAC25, etaFus, etaStrut, tcRoot, tcTip, xRoot, strUID):
'''
This method creates a double trapezoid wing geometry in the 'myWing' parameter.
@author: Jonas Jepsen
@param myWing: wings CPACS object
@param id: the VAMPzero-id of the wing
@param cTip: length of chord at wing tip [m]
@param cRoot: length of chord at wing root [m]
@param span: span of the wing [m]
@param Sref: reference area [m^2]
@param phiLE: sweep angle at the leading edge [deg]
@param dihedral: dihedralangle of the wing [deg]
@param twist: twist of the outer wing section [deg]
@param etakf: dimensionless span coordinate [-]
@param strUID: the CPACS-uID of the wing
'''
mySections = wingSectionsType()
myPositionings = positioningsType()
# calc Lvl 1 parameters
taperRatio = (cTip/cRoot)
cRoot = calcWing(b=span, S=Sref, tau=taperRatio, eF=etaFus)
cStrut = cRoot+(cTip-cRoot)*(etaStrut-etaFus)/(1-etaFus)
cTip = taperRatio * cRoot # cRoot was updated in the last step
# calc length from span, sweep and dihedral
sweep_rad = phiLE/180. * pi
dihedral_rad = dihedral/180. * pi
length1 = (etaFus*span/2.)
length2 = (etaStrut-etaFus)*span/2/cos(sweep_rad)/cos(dihedral_rad)
length3 = span/2.*(1-etaStrut)/cos(sweep_rad)/cos(dihedral_rad)
# Increase (or reduce the twist by 4deg as that is the overall angle of incidence of the wing)
incidenceAngle = 4.
twist = twist + incidenceAngle
twistgrad = twist / (span / 2.)
twist2 = twistgrad * length2
twist3 = twist
createWingSection(mySections, tcRoot/0.09, 0.,0.,0., cRoot,1.,cRoot, 0.,incidenceAngle,0., 'NACA0009', 1, strUID + '_Sec1', strUID + '_Sec1', strUID + '_Sec1')
createWingSection(mySections, tcRoot / 0.18, 0.,0.,0., cRoot,1.,cRoot, 0.,incidenceAngle,0., 'NACA653218', 1, strUID + '_Sec2', strUID + '_Sec2', strUID + '_Sec2')
createWingSection(mySections, tcRoot / 0.18, 0.,0.,0., cStrut,1.,cStrut, 0.,twist2,0., 'NACA653218', 1, strUID + '_Sec3', strUID + '_Sec3', strUID + '_Sec3')
createWingSection(mySections, tcTip / 0.18, 0.,0.,0., cTip,1.,cTip, 0.,twist3,0., 'NACA653218', 1, strUID + '_Sec4', strUID + '_Sec4', strUID + '_Sec4')
createPositioning(myPositionings,str(id) + '_Pos1',None, str(id) + '_Sec1',0.,0.,0.,id)
createPositioning(myPositionings,str(id) + '_Pos2',str(id) + '_Sec1',str(id) + '_Sec2',length1,0.,0.,id)
createPositioning(myPositionings,str(id) + '_Pos3',str(id) + '_Sec2',str(id) + '_Sec3',length2,phiLE,dihedral,id)
createPositioning(myPositionings,str(id) + '_Pos4',str(id) + '_Sec3',str(id) + '_Sec4',length3,phiLE,dihedral,id)
myWing.set_sections(mySections)
myWing.set_positionings(myPositionings)
createWingSegments(myWing, strUID, 3)
createComponentSegment(myWing, strUID)
# Ribs outboard of the Fuselage section are placed at 0.8 m distance
nouterRibs = int(ceil((0.95 - etaFus - 0.05) * span / 2. / 0.8))
createRibs(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'strutBracedWing', etaFus=etaFus, nRibs=nouterRibs, etaStrut=etaStrut, span=span / 2., phi25 = phiLE)
createSpars(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'strutBracedWing', etaFus=etaFus, cTip=cTip, cRoot=cRoot)
createShell(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'strutBracedWing')
iRib = int(span * (0.9 - etaStrut) / (2 * 0.8)) - 1
if iRib == 1:
iRib = 2
createTanks(myWing.get_componentSegments().get_componentSegment()[0], strUID, typeOfSeg='strutBracedWing', nRib=iRib)
createWingFuselageAttachment(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'advDoubletrapezoid')
# set wing x - position and twist
myWing.get_transformation().get_translation().set_x(doubleBaseType(valueOf_=str(xRoot)))
def createAdvDoubleTrapezoidWing(myWing, id, cTip, cRoot, span, Sref, dfus, phiLE, dihedral, twist, xMAC25, etakf, strUID, yfus, xRoot, etaEng, tcRoot, tcTip):
'''
This method creates a double trapezoid wing geometry in the 'myWing' parameter.
** Introduced a linear twist distribution from *0* at root to *twist* at tip
@author: Jonas Jepsen
@param myWing: wings CPACS object
@param id: the VAMPzero-id of the wing
@param cTip: length of chord at wing tip [m]
@param cRoot: length of chord at wing root [m]
@param span: span of the wing [m]
@param Sref: reference area [m^2]
@param dfus: fuselage diameter [m]
@param phiLE: sweep angle at the leading edge [deg]
@param dihedral: dihedralangle of the wing [deg]
@param twist: twist of the outer wing section [deg]
@param etakf: dimensionless span coordinate [-]
@param strUID: the CPACS-uID of the wing
'''
# sections and positionings will be created, all existing sections and positionings will be deleted
mySections = wingSectionsType()
myPositionings = positioningsType()
# calc Lvl 1 parameters
taperRatio = (cTip / cRoot)
cRoot, cKink, cTip = calcWing(span, Sref, taperRatio, phiLE, etakf, dfus)
# calc length from span, sweep and dihedral
sweep_rad = phiLE / 180. * pi
dihedral_rad = dihedral / 180. * pi
# trying to correct the commented statement that uses dfus. will try to use yfus
# length1 = dfus / 2.
length1 = yfus
length2 = (etakf * span / 2. - length1) / cos(sweep_rad) / cos(dihedral_rad)
length3 = span / 2.*(1 - etakf) / cos(sweep_rad) / cos(dihedral_rad)
# Increase (or reduce the twist by 4deg as that is the overall angle of incidence of the wing)
twist = twist - 4.
twistgrad = twist / (span / 2.)
twist1 = twistgrad * length1
twist2 = twistgrad * etakf * (span / 2.)
twist3 = twist
createWingSection(mySections, tcRoot / 0.09, 0., 0., 0., cRoot, 1., cRoot, 0., 0., 0., 'NACA0009', 1, strUID + '_Sec1', strUID + '_Sec1', strUID + '_Sec1')
createWingSection(mySections, tcRoot / 0.18, 0., 0., 0., cRoot, 1., cRoot, 0., 0., 0., 'NACA653218', 1, strUID + '_Sec2', strUID + '_Sec2', strUID + '_Sec2')
createWingSection(mySections, tcTip / 0.18, 0., 0., 0., cKink, 1., cKink, 0., twist2, 0., 'NACA653218', 1, strUID + '_Sec3', strUID + '_Sec3', strUID + '_Sec3')
createWingSection(mySections, tcTip / 0.18, 0., 0., 0., cTip, 1., cTip, 0., twist3, 0., 'NACA653218', 1, strUID + '_Sec4', strUID + '_Sec4', strUID + '_Sec4')
createPositioning(myPositionings, str(id) + '_Pos1', None, str(id) + '_Sec1', 0., 0., 0., id)
createPositioning(myPositionings, str(id) + '_Pos2', str(id) + '_Sec1', str(id) + '_Sec2', length1, 0., 0., id)
createPositioning(myPositionings, str(id) + '_Pos3', str(id) + '_Sec2', str(id) + '_Sec3', length2, phiLE, dihedral, id)
createPositioning(myPositionings, str(id) + '_Pos4', str(id) + '_Sec3', str(id) + '_Sec4', length3, phiLE, dihedral, id)
myWing.set_sections(mySections)
myWing.set_positionings(myPositionings)
createWingSegments(myWing, strUID, 3)
createComponentSegment(myWing, strUID)
etafus = yfus / (span / 2.)
# Ribs outboard of the Fuselage section are placed at 0.8 m distance
nouterRibs = int(ceil((0.95 - etafus - 0.05) * span / 2. / 0.8))
createRibs(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'advDoubletrapezoid', etaFus=etafus, nRibs=nouterRibs, etaEng=etaEng, span=span / 2.)
createSpars(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'advDoubletrapezoid', length1 / (span / 2.), etakf / cos(dihedral_rad), cTip=cTip, cRoot=cRoot)
createShell(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'advDoubletrapezoid')
createWingFuselageAttachment(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'advDoubletrapezoid')
# Estimate ribNum of outer Rib
iRib = int(span * (0.85 - etaEng) / (2 * 0.8)) - 1
createTanks(myWing.get_componentSegments().get_componentSegment()[0], strUID, 'advDoubletrapezoid', nRib=iRib)
# calc wing position
tauK = cTip / cKink
etar = dfus / span
# XN25F = calcXN25F(cRoot, span, phiLE, etar, etakf, tauK, taperRatio)
# xRoot.py = calcXRoot(xMAC25, XN25F)
# set wing x - position and twist
myWing.get_transformation().get_translation().set_x(doubleBaseType(valueOf_=str(xRoot)))
myWing.get_transformation().get_rotation().set_y(doubleBaseType(valueOf_=str(4.)))