af_extrap2 = af.extrapolate(cdmax, AR=AR, cdmin=cdmin)
# 5 ---------
# 6 ---------
# create new airfoil that uses the same angles of attack at each Reynolds number
af_common1 = af.interpToCommonAlpha()
# default approach uses a union of all defined angles of attack
# alternatively, specify the exact angles to use
alpha = np.arange(-180, 180)
af_common2 = af.interpToCommonAlpha(alpha)
# 6 ---------
# 7 ---------
# extract a data grid from airfoil
alpha, Re, cl, cd = af.createDataGrid()
# cl[i, j] is the lift coefficient for alpha[i] and Re[j]
# 7 ---------
# 8 ---------
af.writeToAerodynFile('output.dat')
# 8 ---------
af_extrap2 = af.extrapolate(cdmax, AR=AR, cdmin=cdmin)
# 5 ---------
# 6 ---------
# create new airfoil that uses the same angles of attack at each Reynolds number
af_common1 = af.interpToCommonAlpha()
# default approach uses a union of all defined angles of attack
# alternatively, specify the exact angles to use
alpha = np.arange(-180, 180)
af_common2 = af.interpToCommonAlpha(alpha)
# 6 ---------
# 7 ---------
# extract a data grid from airfoil
alpha, Re, cl, cd = af.createDataGrid()
# cl[i, j] is the lift coefficient for alpha[i] and Re[j]
# 7 ---------
# 8 ---------
af.writeToAerodynFile("output.dat")
# 8 ---------
def solve_nonlinear(self, params, unknowns, resids):
# determine aspect ratio = (rotor radius / chord_75% radius)\
# if provided, cdmax is computed from AR'
bl = params['blade_length']
dr = params['rotor_diameter']
hr = 0.5 * dr - bl
rotor_radius = 0.5 * dr
chord = params['chord_st'] * bl
s = params['s_st']
r = (s * bl + hr) / rotor_radius
chord_75 = np.interp(0.75, r, chord)
AR = rotor_radius / chord_75
# write aerodyn files
af_name_base = 'cs_'
af_name_suffix = '_aerodyn'
tcs = params['cs_polars_tc']
n_cs_alpha = params['n_cs_alpha']
pol = params['cs_polars']
nmet = 0
# TODO: blend polars determined with different methods
for i, tc in enumerate(self.blend_var):
af_name = af_name_base + \
'%03d_%04d' % (i, tc * 1000) + af_name_suffix
re_polars = []
for nre, re in enumerate(self.res):
# create polar object
p = Polar(re,
pol[:n_cs_alpha[i, nre, nmet], 0, i, nre, nmet],
pol[:n_cs_alpha[i, nre, nmet], 1, i, nre, nmet],
pol[:n_cs_alpha[i, nre, nmet], 2, i, nre, nmet],
pol[:n_cs_alpha[i, nre, nmet], 3, i, nre, nmet])
# extrapolate polar
if tc < self.tc_max:
p_extrap = p.extrapolate(self.cdmax,
AR,
self.cdmin,
self.nalpha)
else:
p_extrap = p.extrapolate_as_cylinder()
p_extrap.useCM = self.useCM
re_polars.append(p_extrap)
# TODO: output as HAWC2/FAST format
# See if HAWC can take several af tables with different Re
# numbers
'''
unknowns['airfoildata:aoa%02d' % i] = p_extrap.alpha
unknowns['airfoildata:cl%02d' % i] = p_extrap.cl
unknowns['airfoildata:cd%02d' % i] = p_extrap.cd
unknowns['airfoildata:cm%02d' % i] = p_extrap.cm
'''
# create airfoil object
af = Airfoil(re_polars)
af.interpToCommonAlpha()
af.writeToAerodynFile(af_name + '.dat')
if self.plot_polars:
figs = af.plot(single_figure=True)
titles = ['cl', 'cd', 'cm']
for (fig, title) in zip(figs, titles):
fig.savefig(af_name + '_' + title + '.png', dpi=400)
fig.savefig(af_name + '_' + title + '.pdf')
self._get_unknowns(unknowns)
