def __init__(self,
twist,
chord,
radius,
n_blades,
r,
y,
dr,
dy,
Clalpha,
solidity=None,
airfoils=None):
"""
:param twist: Twist distribution, numpy array
:param chord: Chord distribution, numpy array
:param radius: blade radius, float
:param n_blades: number of blades, integer
:param r: non-dimensional radial element locations
:param y: dimensional radial element locations
:param dr: non-dimensional distance between elements
:param dy: dimensional distance between elements
:param Clalpha: linear lift curve slope, usually 2*pi
:param solidity: optional argument for use in test cases where solidity is constant along the blade
:param airfoils: in the form (('airfoil1', r_start, r_end), ('airfoil2', r_start, r_end), etc)
:return:
"""
if solidity is None:
self.chord = chord
self.solidity = n_blades * chord / (2 * np.pi * y)
else:
# Handle case for when we just want to pass a solidity
self.solidity = solidity
self.chord = solidity * np.pi * radius / n_blades
if airfoils is None:
self.airfoils = (('simple', 0, 1), )
else:
self.airfoils = airfoils
self.Cl_tables = {}
self.Cd_tables = {}
for airfoil in self.airfoils:
alpha, Re, CL, CD = create_table(airfoil[0])
self.Cl_tables[airfoil[0]] = ((alpha, Re), CL)
self.Cd_tables[airfoil[0]] = ((alpha, Re), CD)
self.twist = twist
self.radius = radius
self.n_blades = n_blades
self.r = r
self.y = y
self.dr = dr
self.dy = dy
self.Clalpha = Clalpha
# airfoil_fun_r is a list of airfoil names where airfoil_fun_r[0] is the airfoil section at r = 0 and
# airfoil_fun_r[-1] is the airfoil section name at r = 1
self.airfoil_fun_r = []
for r_loc in self.r:
self.airfoil_fun_r.append(self.get_airfoil(r_loc))
def create_Cl_Cd_table(airfoil):
"""
Create "tables" (really these are tuples of the form ((angle of attack, Reynolds number), Cl)) of lift and drag
coefficient as a function of angle of attack and Reynolds number.
:param airfoil: The name of the airfoil. This name should have a corresponding folder in BEMT/bemt/airfoil_data with
output from XFOIL.
:return: The Cl and Cd "tables" as described above.
"""
alphas, Re, CL, CD, Clmax = lookup_table.create_table(airfoil)
Cl_table = ((alphas, Re), CL)
Cd_table = ((alphas, Re), CD)
return Cl_table, Cd_table, Clmax
def __init__(self, twist, chord, radius, n_blades, r, y, dr, dy, solidity=None, airfoils=None, Cl_tables={},
Cd_tables={}):
"""
:param twist: Twist distribution, numpy array
:param chord: Chord distribution, numpy array
:param radius: blade radius, float
:param n_blades: number of blades, integer
:param r: non-dimensional radial element locations
:param y: dimensional radial element locations
:param dr: non-dimensional distance between elements
:param dy: dimensional distance between elements
:param solidity: optional argument for use in test cases where solidity is constant along the blade
:param airfoils: in the form (('airfoil1', r_start, r_end), ('airfoil2', r_start, r_end), etc)
:return:
"""
# Initialize propeller chord and solidity
if solidity is None:
self.chord = chord
self.solidity = n_blades*chord/np.pi/radius
else:
# Handle case for when we just want to pass a solidity
self.solidity = solidity
self.chord = solidity*np.pi*radius/n_blades
# Initialize propeller Cl and Cd tables as copies as the argument values. This can either be an empty dict or
# a dictionary with keys corresponding to the airfoil that makes up the propeller.
self.Cl_tables = Cl_tables
self.Cd_tables = Cd_tables
# Handle case where user does not specify airfoils and use simple case.
if airfoils is None:
self.airfoils = (('simple', 0., 1.),)
self.Cl_tables[self.airfoils[0][0]] = ()
self.Cd_tables[self.airfoils[0][0]] = ()
# Handle case where the airfoil is specified as simple (Cl = 2*pi*alpha, Cd = quadratic wrt alpha)
elif sorted(airfoils) == sorted((('simple', 0.0, 1.0),)):
self.airfoils = airfoils
self.Cl_tables[self.airfoils[0][0]] = ()
self.Cd_tables[self.airfoils[0][0]] = ()
# Handle case where the airfoil is something other than simple. For these cases we assume either the Cl and Cd
# tables have been created outside of the optimization (i.e., the Cl_tables and Cd_tables arguments are not
# empty) in which case the attribute variables have already been initialized to the input variables. If the
# input variables are empty, create the tables from the airfoil data in BEMT/bemt/airfoil_data.
else:
self.airfoils = airfoils
if not Cl_tables:
for airfoil in self.airfoils:
# The alpha values returned from create_table are in degrees, therefore the table will need to be
# queried in degrees
alpha, Re, CL, CD = create_table(airfoil[0])
self.Cl_tables[airfoil[0]] = ((alpha, Re), CL)
self.Cd_tables[airfoil[0]] = ((alpha, Re), CD)
self.twist = twist
self.radius = radius
self.n_blades = n_blades
self.r = r
self.y = y
self.dr = dr
self.dy = dy
# airfoil_fun_r is a list of airfoil names where airfoil_fun_r[0] is the airfoil section at r = 0 and
# airfoil_fun_r[-1] is the airfoil section name at r = 1
self.airfoil_fun_r = []
for r_loc in self.r:
self.airfoil_fun_r.append(self.get_airfoil(r_loc))
from lookup_table import create_table, interpolate, interpolate_griddata, interp_weights
from scipy.interpolate import griddata, interp2d
import numpy as np
import matplotlib.pyplot as plt
airfoil = 'SDA1075_494p'
this_Re = 90000
alpha, Re, CL, CD = create_table(airfoil)
Cl_table = ((alpha, Re), CL)
Cd_table = ((alpha, Re), CD)
# Cl_table = interp2d(alpha, Re, CL)
# Cd_table = interp2d(alpha, Re, CD)
this_Re = [10940.86555083, 13419.20972376, 21080.74104361, 29969.83072693, 36438.89917782, 41373.73264073,
45842.63697827, 50839.13217244, 55877.23014428, 60612.78159125, 65482.99369756, 70332.56842598,
75197.56024198, 80340.67175443, 85377.27859881, 90330.64760795, 89890.63129127, 8576.42658423]
this_alpha = [18.64167177, 24.07602684, 22.66423279, 17.7874695, 15.73267543, 14.17419872, 13.62414577, 13.25507582,
12.86662159, 12.49683968, 12.0619762, 11.66907308, 11.28712304, 10.99017599, 10.7326172, 10.53891917,
8.73624857, 1.69642724]
# Cl_vec = [getCl(this_alpha[i], this_Re[i]) for i in xrange(len(this_Re))]
# Cd_vec = [getCd(this_alpha[i], this_Re[i]) for i in xrange(len(this_Re))]
# print "Cl = " + str(Cl_vec)
# print "Cd = " + str(Cd_vec)
# this_alphas = [alpha[i] for i in xrange(len(alpha)) if abs(Re[i] - this_Re) < 0.05]
from flask import Flask
import os
import lookup_table as table
from os import listdir
from os.path import isfile, join
import pickle
if __name__ == '__main__':
# grabbing all the species names from kmz
onlyfiles = [
f for f in listdir("/nfs/range_shapefiles")
if isfile(join("range_shapefiles", f))
]
all_species = [name.split(",")[0] for name in onlyfiles if name]
grid_cells = table.create_table()
file_Name = "gridtable"
fileObject = open(file_Name, 'wb')
pickle.dump(grid_cells, fileObject)
fileObject.close()
from lookup_table import create_table
from matplotlib import pyplot as plt
import numpy as np
alphas, reynolds_numbers, CLs, CDs, Clmax = create_table('SDA1075_494p')
Re20k_CL = []
Re20k_CD = []
Re20k_alpha = []
Re30k_CL = []
Re30k_CD = []
Re30k_alpha = []
Re40k_CL = []
Re40k_CD = []
Re40k_alpha = []
Re50k_CL = []
Re50k_CD = []
Re50k_alpha = []
Re60k_CL = []
Re60k_CD = []
Re60k_alpha = []
Re100k_CL = []
Re100k_CD = []
Re100k_alpha = []
Re250k_CL = []
def create_Cl_Cd_table(airfoil):
alphas, Re, CL, CD, Clmax = lookup_table.create_table(airfoil)
Cl_table = ((alphas, Re), CL)
Cd_table = ((alphas, Re), CD)
return Cl_table, Cd_table, Clmax