#!/usr/bin/python3
from xfoil import XFoil
import matplotlib.pyplot as plt
xf = XFoil()
xf.load("revclarky.dat")
xf.Re = 1e5
xf.M = 0
xf.max_iter = 100
a, cl, cd, cm, cp = xf.aseq(-2, 2, 0.5)
plt.plot(a, cl)
plt.title("alfa vs cl")
plt.show()
#plt.plot(xf.airfoil.x,xf.airfoil.y)
#plt.axis('equal')
#plt.show()
try:
for i in range(int(len(airfoils)/2)):
xf = XFoil()
aa = airfoils[2*j]
b = airfoils[2*j+1]
archive3 = open('load.txt', 'w')
for line in range(len(aa)):
aux = [aa[line],b[line]]
string = str(aux).replace("["," ").replace(","," ").replace("]"," ").replace("'"," ")
archive3.writelines(string+ '\n')
aux.clear
# Calculates the aerodynamic coeff using Xfoil
archive3.close()
xf.load('load.txt')
xf.Re = 1e3
xf.max_iter = 100
ann, cl, cd, cm, co = xf.aseq(1, 11, 1)
an = np.linspace(1,10,10)
# Calculates the geometric position of the center of gravity for an airfoil
Xstruct[:,0] = aa
Xstruct[:,1] = b
Surf,Iben,Itor,Xcg,Ycg = Struct.ArfoilProperties(1.0,Xstruct)
# Stores the data in an external file
if i==0:
for z in range(len(an)):
archive2.write( "Cl(A="+str(an[z]).replace("["," ").replace("]"," ")
+");")
aa = Xwing_aero1[:, 0]
b = Xwing_aero1[:, 1]
archive3 = open('lt.txt', 'w')
for line in range(len(aa)):
aux = [aa[line], b[line]]
string = str(aux).replace("[",
" ").replace(",",
" ").replace("]",
" ").replace("'", " ")
archive3.writelines(string + '\n')
aux.clear
# Calculates the aerodynamic coeff using Xfoil
archive3.close()
xf.load('lt.txt')
xf.Re = 1e3
xf.max_iter = 100
ann, cl, cd, cm, co = xf.aseq(1, 11, 1)
an = np.linspace(1, 10, 10)
desired = np.zeros(31)
desired[0:10] = cl
desired[10:20] = cd
desired[20:30] = cm
Surf, Iben, Itor, Xcg, Ycg = Struct.ArfoilProperties(1.0, Xwing_struct1)
desired[30] = Xcg
#2.Initialize Aero and Structural Models
#2.a. Aero Model
Elements, Xc, Xn, Xt, DL, A = Aero.InitializeAeroModel(Xwing_aero)
AoA, Vnorm = 0.0, 6.0
from xfoil import XFoil
import matplotlib.pyplot as plt
xf = XFoil()
xf.load("clarky.dat")
plt.plot(xf.airfoil.x, xf.airfoil.y)
plt.axis('equal')
plt.show()
