# Aspect ratios to consider
RA = [8.0, 2.0, 0.5]
# Use lift slope from thin airfoil theory
a0 = 2.0 * np.pi
# Average chord length
c = 10.0
sec_cl_panair = []
sec_cl_pralines_classical = []
sec_cl_pralines_modifiedslender = []
sec_cl_pralines_hodson = []
for A in RA:
sec_cl_panair.append(panair_wing_cla.sec_cl(c, A, viz=True))
sec_cl_pralines_classical.append(
pralines_wing_cla.sec_cl(A, lowra='Classical'))
sec_cl_pralines_modifiedslender.append(
pralines_wing_cla.sec_cl(A, lowra='ModifiedSlender'))
sec_cl_pralines_hodson.append(pralines_wing_cla.sec_cl(A, lowra='Hodson'))
# Set up a new plot
plt.rc('font', **{'family': 'serif', 'serif': ['Times New Roman']})
plt.rcParams["font.family"] = "Times New Roman"
plt.rcParams["font.size"] = 10
plt.rcParams["lines.markersize"] = 4
plt.figure(figsize=(6.0, 4.0))
lw = 0.5 # Line width
# Plot the results
from phd_scripts.utility_scripts import machup_wing_cla
# Aspect ratios to consider
RA = [8.0, 2.0, 0.5]
# Use lift slope from thin airfoil theory
a0 = 2.0 * np.pi
# Average chord length
c = 10.0
sec_cl_panair = []
sec_cl_pralines_classical = []
sec_cl_pralines_modifiedslender = []
sec_cl_pralines_hodson = []
for A in RA:
sec_cl_panair.append(panair_wing_cla.sec_cl(c, A))
sec_cl_pralines_classical.append(
pralines_wing_cla.sec_cl(A, lowra='Classical'))
sec_cl_pralines_modifiedslender.append(
pralines_wing_cla.sec_cl(A, lowra='ModifiedSlender'))
sec_cl_pralines_hodson.append(pralines_wing_cla.sec_cl(A, lowra='Hodson'))
# Set up a new plot
plt.rc('font', **{'family': 'serif', 'serif': ['Times New Roman']})
plt.rcParams["font.family"] = "Times New Roman"
plt.rcParams["font.size"] = 10
plt.rcParams["lines.markersize"] = 4
plt.figure(figsize=(6.0, 4.0))
lw = 0.5 # Line width
# Plot the results
# Aspect ratios to consider
RA = [8.0, 2.0, 0.5]
# Use lift slope from thin airfoil theory
a0 = 2.0 * np.pi
# Average chord length
c = 10.0
sec_cl_panair = []
sec_cl_machup_classical = []
sec_cl_machup_modifiedslender = []
sec_cl_machup_hodson = []
for A in RA:
sec_cl_panair.append(panair_wing_cla.sec_cl(c, A, viz=False))
sec_cl_machup_classical.append(
machup_wing_cla.sec_cl(A, lowra_method='Classical'))
sec_cl_machup_modifiedslender.append(
machup_wing_cla.sec_cl(A, lowra_method='ModifiedSlender'))
sec_cl_machup_hodson.append(
machup_wing_cla.sec_cl(A, lowra_method='Hodson'))
# Set up a new plot
plt.rc('font', **{'family': 'serif', 'serif': ['Times New Roman']})
plt.rcParams["font.family"] = "Times New Roman"
plt.rcParams["font.size"] = 10
plt.rcParams["lines.markersize"] = 4
plt.figure(figsize=(6.0, 4.0))
lw = 0.5 # Line width
import sys
sys.path.append('..\\..\\..\\')
import numpy as np
import matplotlib.pyplot as plt
from itertools import cycle
from phd_scripts.utility_scripts import panair_wing_cla
# Set up global plot parameters
plt.rc('font', **{'family':'serif', 'serif':['Times New Roman']})
plt.rcParams["font.family"] = "Times New Roman"
plt.rcParams["font.size"] = 10
plt.rcParams["lines.markersize"] = 4
# Define the wing
A = 4 # Aspect ratio
c_avg = 10 # Average chord
# Plot the grid-convergence data
panair_wing_cla.sec_cl(c_avg, A, None, False, True, True)