# compute a 3D corrected and extended airfoil
af_extrap1 = af.extrapolate(cdmax)
# a second example using the optional inputs
AR = 17 # blade aspect ratio. If provided, cdmax is estimated using the aspect ratio.
cdmin = 0.001 # minimum drag coefficient. Viterna's method can occasionally produce
# negative drag coefficients. A minimum is used to prevent unphysical data.
# The passed in value is used to override the default.
af_extrap2 = af.extrapolate(cdmax, AR=AR, cdmin=cdmin)
# ------
# 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)
# ------
# extract a data grid from airfoil
alpha, Re, cl, cd, cm = af.createDataGrid()
# cl[i, j] is the lift coefficient for alpha[i] and Re[j]
# write a new AeroDyn file
af.writeToAerodynFile("output.dat")
# ------
cdmax = 1.3
# compute a 3D corrected and extended airfoil
af_extrap1 = af.extrapolate(cdmax)
# a second example using the optional inputs
AR = 17 # blade aspect ratio. If provided, cdmax is estimated using the aspect ratio.
cdmin = 0.001 # minimum drag coefficient. Viterna's method can occasionally produce
# negative drag coefficients. A minimum is used to prevent unphysical data.
# The passed in value is used to override the default.
af_extrap2 = af.extrapolate(cdmax, AR=AR, cdmin=cdmin)
# ------
# 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)
# ------
# extract a data grid from airfoil
alpha, Re, cl, cd, cm = af.createDataGrid()
# cl[i, j] is the lift coefficient for alpha[i] and Re[j]
# write a new AeroDyn file
af.writeToAerodynFile('output.dat')
# ------