def create(self, n=1):
# cautious! considering multiple created aircraft with same type
super(OpenAP, self).create(n)
actype = bs.traf.type[-1].upper()
# check fixwing or rotor, default fixwing if not found
if actype in self.coeff.actypes_rotor:
self.lifttype[-n:] = coeff.LIFT_ROTOR
self.mass[-n:] = 0.5 * (self.coeff.acs_rotor[actype]['oew'] + self.coeff.acs_rotor[actype]['mtow'])
self.engnum[-n:] = int(self.coeff.acs_rotor[actype]['n_engines'])
self.engpower[-n:] = self.coeff.acs_rotor[actype]['engines'][0][1] # engine power (kW)
else:
# convert to known aircraft type
if actype not in self.coeff.actypes_fixwing:
actype = 'A320'
# populate fuel flow model
es = self.coeff.acs_fixwing[actype]['engines']
e = es[list(es.keys())[0]]
coeff_a, coeff_b, coeff_c = thrust.compute_eng_ff_coeff(e['ff_idl'], e['ff_app'], e['ff_co'], e['ff_to'])
self.lifttype[-n:] = coeff.LIFT_FIXWING
self.Sref[-n:] = self.coeff.acs_fixwing[actype]['wa']
self.mass[-n:] = 0.5 * (self.coeff.acs_fixwing[actype]['oew'] + self.coeff.acs_fixwing[actype]['mtow'])
self.engnum[-n:] = int(self.coeff.acs_fixwing[actype]['n_engines'])
self.ff_coeff_a[-n:] = coeff_a
self.ff_coeff_b[-n:] = coeff_b
self.ff_coeff_c[-n:] = coeff_c
all_ac_engs = list(self.coeff.acs_fixwing[actype]['engines'].keys())
self.engthrust[-n:] = self.coeff.acs_fixwing[actype]['engines'][all_ac_engs[0]]['thr']
self.engbpr[-n:] = self.coeff.acs_fixwing[actype]['engines'][all_ac_engs[0]]['bpr']
# init drag polar coefficients
if actype in self.coeff.dragpolar_fixwing.keys():
self.cd0_clean[-n:] = self.coeff.dragpolar_fixwing[actype]['cd0_clean']
self.cd0_gd[-n:] = self.coeff.dragpolar_fixwing[actype]['cd0_gd']
self.cd0_to[-n:] = self.coeff.dragpolar_fixwing[actype]['cd0_to']
self.cd0_ic[-n:] = self.coeff.dragpolar_fixwing[actype]['cd0_ic']
self.cd0_ap[-n:] = self.coeff.dragpolar_fixwing[actype]['cd0_ap']
self.cd0_ld[-n:] = self.coeff.dragpolar_fixwing[actype]['cd0_ld']
self.k[-n:] = self.coeff.dragpolar_fixwing[actype]['k']
else:
self.cd0_clean[-n:] = self.coeff.dragpolar_fixwing['NA']['cd0_clean']
self.cd0_gd[-n:] = self.coeff.dragpolar_fixwing['NA']['cd0_gd']
self.cd0_to[-n:] = self.coeff.dragpolar_fixwing['NA']['cd0_to']
self.cd0_ic[-n:] = self.coeff.dragpolar_fixwing['NA']['cd0_ic']
self.cd0_ap[-n:] = self.coeff.dragpolar_fixwing['NA']['cd0_ap']
self.cd0_ld[-n:] = self.coeff.dragpolar_fixwing['NA']['cd0_ld']
self.k[-n:] = self.coeff.dragpolar_fixwing['NA']['k']
# append update actypes, after removing unkown types
self.actypes[-n:] = [actype] * n
def create(self, n=1):
# cautious! considering multiple created aircraft with same type
super(OpenAP, self).create(n)
actype = bs.traf.type[-n]
# check fixwing or rotor, default fixwing if not found
if actype in self.coeff.actypes_rotor:
self.lifttype[-n:] = coeff.LIFT_ROTOR
self.mass[-n:] = 0.5 * (self.coeff.acs_rotor[actype]['oew'] +
self.coeff.acs_rotor[actype]['mtow'])
self.engnum[-n:] = int(self.coeff.acs_rotor[actype]['n_engines'])
self.engpower[-n:] = self.coeff.acs_rotor[actype]['engines'][0][
1] # engine power (kW)
else:
# convert to known aircraft type
if actype not in self.coeff.actypes_fixwing:
actype = 'A320'
# populate fuel flow model
es = self.coeff.acs_fixwing[actype]['engines']
e = es[list(es.keys())[0]]
coeff_a, coeff_b, coeff_c = thrust.compute_eng_ff_coeff(
e['ff_idl'], e['ff_app'], e['ff_co'], e['ff_to'])
self.lifttype[-n:] = coeff.LIFT_FIXWING
self.Sref[-n:] = self.coeff.acs_fixwing[actype]['wa']
self.mass[-n:] = 0.5 * (self.coeff.acs_fixwing[actype]['oew'] +
self.coeff.acs_fixwing[actype]['mtow'])
self.engnum[-n:] = int(self.coeff.acs_fixwing[actype]['n_engines'])
self.ff_coeff_a[-n:] = np.ones(n) * coeff_a
self.ff_coeff_b[-n:] = np.ones(n) * coeff_b
self.ff_coeff_c[-n:] = np.ones(n) * coeff_c
all_ac_engs = list(
self.coeff.acs_fixwing[actype]['engines'].keys())
self.engthrust[-n:] = self.coeff.acs_fixwing[actype]['engines'][
all_ac_engs[0]]['thr']
self.engbpr[-n:] = self.coeff.acs_fixwing[actype]['engines'][
all_ac_engs[0]]['bpr']
# append update actypes, after removing unkown types
self.actypes[-n:] = [actype] * n
self.n_ac += n
def create(self, n=1):
# cautious! considering multiple created aircraft with same type
super(OpenAP, self).create(n)
actype = bs.traf.type[-1].upper()
# Check synonym file if not in open ap actypes
if (actype not in self.coeff.actypes_rotor) and (
actype not in self.coeff.dragpolar_fixwing):
if actype in self.coeff.synodict:
# print(actype,"replaced by",self.coeff.synodict[actype])
actype = self.coeff.synodict[actype]
# check fixwing or rotor, default to fixwing
if actype in self.coeff.actypes_rotor:
self.lifttype[-n:] = coeff.LIFT_ROTOR
self.mass[-n:] = 0.5 * (self.coeff.acs_rotor[actype]["oew"] +
self.coeff.acs_rotor[actype]["mtow"])
self.engnum[-n:] = int(self.coeff.acs_rotor[actype]["n_engines"])
self.engpower[-n:] = self.coeff.acs_rotor[actype]["engines"][0][
1] # engine power (kW)
else:
# convert to known aircraft type
if actype not in self.coeff.actypes_fixwing:
actype = "B744"
# populate fuel flow model
es = self.coeff.acs_fixwing[actype]["engines"]
e = es[list(es.keys())[0]]
coeff_a, coeff_b, coeff_c = thrust.compute_eng_ff_coeff(
e["ff_idl"], e["ff_app"], e["ff_co"], e["ff_to"])
self.lifttype[-n:] = coeff.LIFT_FIXWING
self.Sref[-n:] = self.coeff.acs_fixwing[actype]["wa"]
self.mass[-n:] = 0.5 * (self.coeff.acs_fixwing[actype]["oew"] +
self.coeff.acs_fixwing[actype]["mtow"])
self.engnum[-n:] = int(self.coeff.acs_fixwing[actype]["n_engines"])
self.ff_coeff_a[-n:] = coeff_a
self.ff_coeff_b[-n:] = coeff_b
self.ff_coeff_c[-n:] = coeff_c
all_ac_engs = list(
self.coeff.acs_fixwing[actype]["engines"].keys())
self.engthrmax[-n:] = self.coeff.acs_fixwing[actype]["engines"][
all_ac_engs[0]]["thr"]
self.engbpr[-n:] = self.coeff.acs_fixwing[actype]["engines"][
all_ac_engs[0]]["bpr"]
# init type specific coefficients
if actype in self.coeff.limits_fixwing.keys():
self.vminic[-n:] = self.coeff.limits_fixwing[actype]["vminic"]
self.vminer[-n:] = self.coeff.limits_fixwing[actype]["vminer"]
self.vminap[-n:] = self.coeff.limits_fixwing[actype]["vminap"]
self.vmaxic[-n:] = self.coeff.limits_fixwing[actype]["vmaxic"]
self.vmaxer[-n:] = self.coeff.limits_fixwing[actype]["vmaxer"]
self.vmaxap[-n:] = self.coeff.limits_fixwing[actype]["vmaxap"]
self.vsmin[-n:] = self.coeff.limits_fixwing[actype]["vsmin"]
self.vsmax[-n:] = self.coeff.limits_fixwing[actype]["vsmax"]
self.hmax[-n:] = self.coeff.limits_fixwing[actype]["hmax"]
self.axmax[-n:] = self.coeff.limits_fixwing[actype]["axmax"]
self.vminto[-n:] = self.coeff.limits_fixwing[actype]["vminto"]
self.cd0_clean[-n:] = self.coeff.dragpolar_fixwing[actype][
"cd0_clean"]
self.k_clean[-n:] = self.coeff.dragpolar_fixwing[actype]["k_clean"]
self.cd0_to[-n:] = self.coeff.dragpolar_fixwing[actype]["cd0_to"]
self.k_to[-n:] = self.coeff.dragpolar_fixwing[actype]["k_to"]
self.cd0_ld[-n:] = self.coeff.dragpolar_fixwing[actype]["cd0_ld"]
self.k_ld[-n:] = self.coeff.dragpolar_fixwing[actype]["k_ld"]
self.delta_cd_gear[-n:] = self.coeff.dragpolar_fixwing[actype][
"delta_cd_gear"]
elif actype in self.coeff.limits_rotor.keys(): # rotorcraft
self.vmin[-n:] = self.coeff.limits_rotor[actype]["vmin"]
self.vmax[-n:] = self.coeff.limits_rotor[actype]["vmax"]
self.vsmin[-n:] = self.coeff.limits_rotor[actype]["vsmin"]
self.vsmax[-n:] = self.coeff.limits_rotor[actype]["vsmax"]
self.hmax[-n:] = self.coeff.limits_rotor[actype]["hmax"]
self.vsmin[-n:] = self.coeff.limits_rotor[actype]["vsmin"]
self.vsmax[-n:] = self.coeff.limits_rotor[actype]["vsmax"]
self.hmax[-n:] = self.coeff.limits_rotor[actype]["hmax"]
self.cd0_clean[-n:] = np.nan
self.k_clean[-n:] = np.nan
self.cd0_to[-n:] = np.nan
self.k_to[-n:] = np.nan
self.cd0_ld[-n:] = np.nan
self.k_ld[-n:] = np.nan
self.delta_cd_gear[-n:] = np.nan
else: # Use default B747-400
print(
"Open AP (perfoap.py): Unknown actype, using default B744 instead."
)
self.vminic[-n:] = self.coeff.limits_fixwing["B744"]["vminic"]
self.vminer[-n:] = self.coeff.limits_fixwing["B744"]["vminer"]
self.vminap[-n:] = self.coeff.limits_fixwing["B744"]["vminap"]
self.vmaxic[-n:] = self.coeff.limits_fixwing["B744"]["vmaxic"]
self.vmaxer[-n:] = self.coeff.limits_fixwing["B744"]["vmaxer"]
self.vmaxap[-n:] = self.coeff.limits_fixwing["B744"]["vmaxap"]
self.vsmin[-n:] = self.coeff.limits_fixwing["B744"]["vsmin"]
self.vsmax[-n:] = self.coeff.limits_fixwing["B744"]["vsmax"]
self.hmax[-n:] = self.coeff.limits_fixwing["B744"]["hmax"]
self.axmax[-n:] = self.coeff.limits_fixwing["B744"]["axmax"]
self.vminto[-n:] = self.coeff.limits_fixwing["B744"]["vminto"]
self.cd0_clean[-n:] = self.coeff.dragpolar_fixwing["B744"][
"cd0_clean"]
self.k_clean[-n:] = self.coeff.dragpolar_fixwing["B744"]["k_clean"]
self.cd0_to[-n:] = self.coeff.dragpolar_fixwing["B744"]["cd0_to"]
self.k_to[-n:] = self.coeff.dragpolar_fixwing["B744"]["k_to"]
self.cd0_ld[-n:] = self.coeff.dragpolar_fixwing["B744"]["cd0_ld"]
self.k_ld[-n:] = self.coeff.dragpolar_fixwing["B744"]["k_ld"]
self.delta_cd_gear[-n:] = self.coeff.dragpolar_fixwing["B744"][
"delta_cd_gear"]
# append update actypes, after removing unkown types
self.actypes[-n:] = [actype] * n
def create(self, n=1):
# cautious! considering multiple created aircraft with same type
super(OpenAP, self).create(n)
actype = bs.traf.type[-1].upper()
# Check synonym file if not in open ap actypes
if (actype not in self.coeff.actypes_rotor) and \
(actype not in self.coeff.dragpolar_fixwing):
if actype in self.coeff.synodict:
#print(actype,"replaced by",self.coeff.synodict[actype])
actype = self.coeff.synodict[actype]
# check fixwing or rotor, default fixwing if not found
if actype in self.coeff.actypes_rotor:
self.lifttype[-n:] = coeff.LIFT_ROTOR
self.mass[-n:] = 0.5 * (self.coeff.acs_rotor[actype]['oew'] +
self.coeff.acs_rotor[actype]['mtow'])
self.engnum[-n:] = int(self.coeff.acs_rotor[actype]['n_engines'])
self.engpower[-n:] = self.coeff.acs_rotor[actype]['engines'][0][
1] # engine power (kW)
else:
# convert to known aircraft type
if actype not in self.coeff.actypes_fixwing:
actype = "B744"
# populate fuel flow model
es = self.coeff.acs_fixwing[actype]['engines']
e = es[list(es.keys())[0]]
coeff_a, coeff_b, coeff_c = thrust.compute_eng_ff_coeff(
e['ff_idl'], e['ff_app'], e['ff_co'], e['ff_to'])
self.lifttype[-n:] = coeff.LIFT_FIXWING
self.Sref[-n:] = self.coeff.acs_fixwing[actype]['wa']
self.mass[-n:] = 0.5 * (self.coeff.acs_fixwing[actype]['oew'] +
self.coeff.acs_fixwing[actype]['mtow'])
self.engnum[-n:] = int(self.coeff.acs_fixwing[actype]['n_engines'])
self.ff_coeff_a[-n:] = coeff_a
self.ff_coeff_b[-n:] = coeff_b
self.ff_coeff_c[-n:] = coeff_c
all_ac_engs = list(
self.coeff.acs_fixwing[actype]['engines'].keys())
self.engthrmax[-n:] = self.coeff.acs_fixwing[actype]['engines'][
all_ac_engs[0]]['thr']
self.engbpr[-n:] = self.coeff.acs_fixwing[actype]['engines'][
all_ac_engs[0]]['bpr']
# init drag polar coefficients
if actype in self.coeff.dragpolar_fixwing.keys():
self.cd0_clean[-n:] = self.coeff.dragpolar_fixwing[actype][
'cd0_clean']
self.cd0_gd[-n:] = self.coeff.dragpolar_fixwing[actype][
'cd0_gd']
self.cd0_to[-n:] = self.coeff.dragpolar_fixwing[actype][
'cd0_to']
self.cd0_ic[-n:] = self.coeff.dragpolar_fixwing[actype][
'cd0_ic']
self.cd0_ap[-n:] = self.coeff.dragpolar_fixwing[actype][
'cd0_ap']
self.cd0_ld[-n:] = self.coeff.dragpolar_fixwing[actype][
'cd0_ld']
self.k[-n:] = self.coeff.dragpolar_fixwing[actype]['k']
else:
self.cd0_clean[-n:] = self.coeff.dragpolar_fixwing['NA'][
'cd0_clean']
self.cd0_gd[-n:] = self.coeff.dragpolar_fixwing['NA']['cd0_gd']
self.cd0_to[-n:] = self.coeff.dragpolar_fixwing['NA']['cd0_to']
self.cd0_ic[-n:] = self.coeff.dragpolar_fixwing['NA']['cd0_ic']
self.cd0_ap[-n:] = self.coeff.dragpolar_fixwing['NA']['cd0_ap']
self.cd0_ld[-n:] = self.coeff.dragpolar_fixwing['NA']['cd0_ld']
self.k[-n:] = self.coeff.dragpolar_fixwing['NA']['k']
# append update actypes, after removing unkown types
self.actypes[-n:] = [actype] * n
def create(self, n=1):
# cautious! considering multiple created aircraft with same type
super().create(n)
actype = bs.traf.type[-1].upper()
# Check synonym file if not in open ap actypes
if (actype not in self.coeff.actypes_rotor) and (
actype not in self.coeff.dragpolar_fixwing):
if actype in self.coeff.synodict.keys():
# warn = f"Warning: {actype} replaced by {self.coeff.synodict[actype]}"
# print(warn)
# bs.scr.echo(warn)
actype = self.coeff.synodict[actype]
# initialize aircraft / engine performance parameters
# check fixwing or rotor, default to fixwing
if actype in self.coeff.actypes_rotor:
self.lifttype[-n:] = coeff.LIFT_ROTOR
self.mass[-n:] = 0.5 * (self.coeff.acs_rotor[actype]["oew"] +
self.coeff.acs_rotor[actype]["mtow"])
self.engnum[-n:] = int(self.coeff.acs_rotor[actype]["n_engines"])
self.engpower[-n:] = self.coeff.acs_rotor[actype]["engines"][0][1]
else:
# convert to known aircraft type
if actype not in self.coeff.actypes_fixwing:
# warn = f"Warning: {actype} replaced by B744"
# print(warn)
# bs.scr.echo(warn)
actype = "B744"
# populate fuel flow model
es = self.coeff.acs_fixwing[actype]["engines"]
e = es[list(es.keys())[0]]
coeff_a, coeff_b, coeff_c = thrust.compute_eng_ff_coeff(
e["ff_idl"], e["ff_app"], e["ff_co"], e["ff_to"])
self.lifttype[-n:] = coeff.LIFT_FIXWING
self.Sref[-n:] = self.coeff.acs_fixwing[actype]["wa"]
self.mass[-n:] = 0.5 * (self.coeff.acs_fixwing[actype]["oew"] +
self.coeff.acs_fixwing[actype]["mtow"])
self.engnum[-n:] = int(self.coeff.acs_fixwing[actype]["n_engines"])
self.ff_coeff_a[-n:] = coeff_a
self.ff_coeff_b[-n:] = coeff_b
self.ff_coeff_c[-n:] = coeff_c
all_ac_engs = list(
self.coeff.acs_fixwing[actype]["engines"].keys())
self.engthrmax[-n:] = self.coeff.acs_fixwing[actype]["engines"][
all_ac_engs[0]]["thr"]
self.engbpr[-n:] = self.coeff.acs_fixwing[actype]["engines"][
all_ac_engs[0]]["bpr"]
# init type specific coefficients for flight envelops
if actype in self.coeff.limits_rotor.keys(): # rotorcraft
self.vmin[-n:] = self.coeff.limits_rotor[actype]["vmin"]
self.vmax[-n:] = self.coeff.limits_rotor[actype]["vmax"]
self.vsmin[-n:] = self.coeff.limits_rotor[actype]["vsmin"]
self.vsmax[-n:] = self.coeff.limits_rotor[actype]["vsmax"]
self.hmax[-n:] = self.coeff.limits_rotor[actype]["hmax"]
self.vsmin[-n:] = self.coeff.limits_rotor[actype]["vsmin"]
self.vsmax[-n:] = self.coeff.limits_rotor[actype]["vsmax"]
self.hmax[-n:] = self.coeff.limits_rotor[actype]["hmax"]
self.cd0_clean[-n:] = np.nan
self.k_clean[-n:] = np.nan
self.cd0_to[-n:] = np.nan
self.k_to[-n:] = np.nan
self.cd0_ld[-n:] = np.nan
self.k_ld[-n:] = np.nan
self.delta_cd_gear[-n:] = np.nan
else:
if actype not in self.coeff.limits_fixwing.keys():
actype = "B744"
self.vminic[-n:] = self.coeff.limits_fixwing[actype]["vminic"]
self.vminer[-n:] = self.coeff.limits_fixwing[actype]["vminer"]
self.vminap[-n:] = self.coeff.limits_fixwing[actype]["vminap"]
self.vmaxic[-n:] = self.coeff.limits_fixwing[actype]["vmaxic"]
self.vmaxer[-n:] = self.coeff.limits_fixwing[actype]["vmaxer"]
self.vmaxap[-n:] = self.coeff.limits_fixwing[actype]["vmaxap"]
self.vsmin[-n:] = self.coeff.limits_fixwing[actype]["vsmin"]
self.vsmax[-n:] = self.coeff.limits_fixwing[actype]["vsmax"]
self.hmax[-n:] = self.coeff.limits_fixwing[actype]["hmax"]
self.axmax[-n:] = self.coeff.limits_fixwing[actype]["axmax"]
self.vminto[-n:] = self.coeff.limits_fixwing[actype]["vminto"]
self.hcross[-n:] = self.coeff.limits_fixwing[actype]["crosscl"]
self.mmo[-n:] = self.coeff.limits_fixwing[actype]["mmo"]
self.cd0_clean[-n:] = self.coeff.dragpolar_fixwing[actype][
"cd0_clean"]
self.k_clean[-n:] = self.coeff.dragpolar_fixwing[actype]["k_clean"]
self.cd0_to[-n:] = self.coeff.dragpolar_fixwing[actype]["cd0_to"]
self.k_to[-n:] = self.coeff.dragpolar_fixwing[actype]["k_to"]
self.cd0_ld[-n:] = self.coeff.dragpolar_fixwing[actype]["cd0_ld"]
self.k_ld[-n:] = self.coeff.dragpolar_fixwing[actype]["k_ld"]
self.delta_cd_gear[-n:] = self.coeff.dragpolar_fixwing[actype][
"delta_cd_gear"]
# append update actypes, after removing unknown types
self.actype[-n:] = [actype] * n
# Update envelope speed limits
mask = np.zeros_like(self.actype, dtype=bool)
mask[-n:] = True
self.vmin[-n:], self.vmax[-n:] = self._construct_v_limits(mask)
def create(self, n=1):
# cautious! considering multiple created aircraft with same type
super(OpenAP, self).create(n)
actype = bs.traf.type[-1].upper()
# check fixwing or rotor, default fixwing if not found
if actype in self.coeff.actypes_rotor:
self.lifttype[-n:] = coeff.LIFT_ROTOR
self.mass[-n:] = 0.5 * (self.coeff.acs_rotor[actype]['oew'] +
self.coeff.acs_rotor[actype]['mtow'])
self.engnum[-n:] = int(self.coeff.acs_rotor[actype]['n_engines'])
self.engpower[-n:] = self.coeff.acs_rotor[actype]['engines'][0][
1] # engine power (kW)
else:
# convert to known aircraft type
if (actype not in self.coeff.actypes_fixwing) or (
actype not in self.coeff.limits_fixwing.keys()):
print(
"WARNING: Aircraft type: %s was not found. It is set to %s."
% (actype, 'A320'))
actype = 'A320'
# populate fuel flow model
if not self.coeff.acs_fixwing[actype]['engines']:
print(
"WARNING: Engine type of %s was not found. Aircraft type is set to %s."
% (actype, 'A320'))
actype = 'A320'
es = self.coeff.acs_fixwing[actype]['engines']
e = es[list(es.keys())[0]]
coeff_a, coeff_b, coeff_c = thrust.compute_eng_ff_coeff(
e['ff_idl'], e['ff_app'], e['ff_co'], e['ff_to'])
self.lifttype[-n:] = coeff.LIFT_FIXWING
self.Sref[-n:] = self.coeff.acs_fixwing[actype]['wa']
self.mass[-n:] = 0.5 * (self.coeff.acs_fixwing[actype]['oew'] +
self.coeff.acs_fixwing[actype]['mtow'])
self.engnum[-n:] = int(self.coeff.acs_fixwing[actype]['n_engines'])
self.ff_coeff_a[-n:] = coeff_a
self.ff_coeff_b[-n:] = coeff_b
self.ff_coeff_c[-n:] = coeff_c
all_ac_engs = list(
self.coeff.acs_fixwing[actype]['engines'].keys())
self.engthrust[-n:] = self.coeff.acs_fixwing[actype]['engines'][
all_ac_engs[0]]['thr']
self.engbpr[-n:] = self.coeff.acs_fixwing[actype]['engines'][
all_ac_engs[0]]['bpr']
# init drag polar coefficients
if actype in self.coeff.dragpolar_fixwing.keys():
self.cd0_clean[-n:] = self.coeff.dragpolar_fixwing[actype][
'cd0_clean']
self.cd0_gd[-n:] = self.coeff.dragpolar_fixwing[actype][
'cd0_gd']
self.cd0_to[-n:] = self.coeff.dragpolar_fixwing[actype][
'cd0_to']
self.cd0_ic[-n:] = self.coeff.dragpolar_fixwing[actype][
'cd0_ic']
self.cd0_ap[-n:] = self.coeff.dragpolar_fixwing[actype][
'cd0_ap']
self.cd0_ld[-n:] = self.coeff.dragpolar_fixwing[actype][
'cd0_ld']
self.k[-n:] = self.coeff.dragpolar_fixwing[actype]['k']
else:
self.cd0_clean[-n:] = self.coeff.dragpolar_fixwing['NA'][
'cd0_clean']
self.cd0_gd[-n:] = self.coeff.dragpolar_fixwing['NA']['cd0_gd']
self.cd0_to[-n:] = self.coeff.dragpolar_fixwing['NA']['cd0_to']
self.cd0_ic[-n:] = self.coeff.dragpolar_fixwing['NA']['cd0_ic']
self.cd0_ap[-n:] = self.coeff.dragpolar_fixwing['NA']['cd0_ap']
self.cd0_ld[-n:] = self.coeff.dragpolar_fixwing['NA']['cd0_ld']
self.k[-n:] = self.coeff.dragpolar_fixwing['NA']['k']
# append update actypes, after removing unkown types
self.actypes[-n:] = [actype] * n
