Skip to content

Commit

Permalink
Funcional MK2.5
Browse files Browse the repository at this point in the history 
Unificadas funciones y variables en inglés, código correctamente
comentado.
  • Loading branch information
@AunSiro
AunSiro committed Mar 3, 2015
1 parent 15017f4 commit 172a9ce
Show file tree
Hide file tree
Showing 14 changed files with 1,105 additions and 522 deletions.
466 changes: 466 additions & 0 deletions aeropy/Xfoil_Interaction/.ipynb_checkpoints/result_drawer-checkpoint.ipynb
View file

Large diffs are not rendered by default.

101 changes: 55 additions & 46 deletions aeropy/Xfoil_Interaction/Genetic_algorithm_files/ambient.py
View file
Original file line number Diff line number Diff line change
Expand Up @@ -7,31 +7,37 @@
This is a submodule for the genetic algorithm that is explained in
https://docs.google.com/presentation/d/1_78ilFL-nbuN5KB5FmNeo-EIZly1PjqxqIB-ant-GfM/edit?usp=sharing
This script is the main program. It will call the different submodules
and manage the data transfer between them in order to achieve the
genetic optimization of the profile.
'''

This script is the ambient subprogram. Its objective is to calculate the
Mach and Reynolds numbers that XFoil uses to calculate the
aerodynamics of airfoils.
This subprogram consist mainly in models for the International Standard Atmosphere
and an equivalent atmosphere model for Mars.
'''

import numpy as np





def ventana (x, inicio=0, fin=1, f=1.):
_1 = (np.sign(x-inicio))
_2 = (np.sign(-x+fin))
def window (x, start=0, end=1, f=1.):
'''Returns a function f between 'start' and 'endn'.
Returns 0 outside this interval'''
_1 = (np.sign(x-start))
_2 = (np.sign(-x+end))
return 0.25 * (_1+1) * (_2+1) * f

def etc (x, inicio=0, f=1.):
_1 = (np.sign(x-inicio))
def etc (x, start=0, f=1.):
'''Returns 0 until 'start', returns 'f' after.
'''
_1 = (np.sign(x-start))
return 0.5 * (_1+1) * f

def earth_conditions():

'''Returns an array of atmospheric and physical data from which the complete
model of the atmosphere can be built.
'''
heights = np.array([-1.000,
11.019,
20.063,
Expand All @@ -43,7 +49,7 @@ def earth_conditions():
90.000])


# an es el gradiente válido entre H(n-1) y H(n)

temp_gradient = np.array([-6.49,
0,
0.99,
Expand Down Expand Up @@ -72,8 +78,8 @@ def earth_conditions():
return conditions


def temperatura(h, conditions, dT = 0):
'''Calcula la temperatura a una altura h en Km sobre el nivel del mar'''
def temperature(h, conditions, dT = 0):
'''Calculates the value for temperature in Kelvin at a certain altitude'''
grad = 0
heights = conditions[0]
gradient = conditions[1]
Expand All @@ -84,50 +90,48 @@ def temperatura(h, conditions, dT = 0):

for layer in np.arange(0, atm_layer-1,1):
increase = temp_points[layer] + gradient[layer] * (h - heights[layer])
grad = grad + ventana(h, heights[layer],heights[layer+1], increase)
grad = grad + window(h, heights[layer],heights[layer+1], increase)
grad = grad + etc(h, heights[atm_layer-1],temp_points[atm_layer-1] + gradient[atm_layer-1]*(h - heights[atm_layer-1]))
return grad + dT


def segmento_presion_1(z, pi, z0, dT, conditions):
'''calcula la presión en un segmento de atmósfera de temperatura constante'''
def pressure_segment_1(z, pi, z0, dT, conditions):
'''Calculates pressure throught a constant temperature segment of the atmosphere'''
g = conditions[3]
R = conditions[4]
radius = conditions[5]
h = (radius * z) /(radius + z)
h0 = (radius * z0)/(radius + z0)
_ = 1000*(h-h0) * g / (R * temperatura(z, conditions, dT))
_ = 1000*(h-h0) * g / (R * temperature(z, conditions, dT))
return pi * np.e ** -_

def segmento_presion_2(z, pi, Ti, a, dT, conditions):
'''calcula la presión en un segmento de atmósfera con gradiente de temperatura "a" '''
def pressure_segment_2(z, pi, Ti, a, dT, conditions):
'''Calculates pressure throught a variant temperature segment of the atmosphere '''
g = conditions[3]
R = conditions[4]
_ = g / (a*R/1000)
return pi * (temperatura(z, conditions, dT)/(Ti + dT)) ** -_
return pi * (temperature(z, conditions, dT)/(Ti + dT)) ** -_

def presion (h, conditions, dT = 0):
'''Calcula la presion en Pa a una altura h en m sobre el nivel del mar'''
def pressure (h, conditions, dT = 0):
'''Calculates the value for pressure in Pascal at a certain altitude'''

heights = conditions[0]
gradient = conditions[1]
temp_points = conditions[2]
atm_layer = gradient.shape[0]
#Primero, calculamos la presion de cada punto de cambio de capa para la condición de dT pedida
#Suponemos que la presión es siempre constante a 101325 Pa a nivel del mar


pressure_points = np.zeros([atm_layer])
pressure_points[0] = conditions[6]

for layer in np.arange(1, atm_layer, 1):
if (abs(gradient[layer-1]) < 1e-8):
pressure_points[layer] = segmento_presion_1(heights[layer],
pressure_points[layer] = pressure_segment_1(heights[layer],
pressure_points[layer - 1],
heights[layer - 1],
dT, conditions)
else:
pressure_points[layer] = segmento_presion_2(heights[layer],
pressure_points[layer] = pressure_segment_2(heights[layer],
pressure_points[layer - 1],
temp_points[layer - 1],
gradient[layer-1],
Expand All @@ -139,24 +143,24 @@ def presion (h, conditions, dT = 0):
grad = 0
for layer in np.arange(1, atm_layer, 1):
if (abs(gradient[layer-1]) < 1e-8):
funcion = segmento_presion_1(h,
funcion = pressure_segment_1(h,
pressure_points[layer - 1],
heights[layer - 1],
dT, conditions)
else:
funcion = segmento_presion_2(h,
funcion = pressure_segment_2(h,
pressure_points[layer - 1],
temp_points[layer - 1],
gradient[layer-1],
dT, conditions)
grad = grad + ventana(h, heights[layer-1], heights[layer], funcion)
grad = grad + window(h, heights[layer-1], heights[layer], funcion)
if (abs(gradient[layer-1])< 10e-8):
funcion = segmento_presion_1(h,
funcion = pressure_segment_1(h,
pressure_points[layer - 1],
heights[layer - 1],
dT, conditions)
else:
funcion = segmento_presion_2(h,
funcion = pressure_segment_2(h,
pressure_points[layer - 1],
temp_points[layer - 1],
gradient[layer-1],
Expand All @@ -166,13 +170,16 @@ def presion (h, conditions, dT = 0):
return grad


def densidad(h, conditions, dT = 0):
'''Calcula la densidad a una altura h en m sobre el nivel del mar'''
def density(h, conditions, dT = 0):
'''Calculates the value for density in Kg/m3 at a certain altitude'''
R = conditions[4]
return presion(h, conditions, dT)/(R * temperatura(h, conditions, dT))
return pressure(h, conditions, dT)/(R * temperature(h, conditions, dT))


def mars_conditions():
'''Returns an array of atmospheric and physical data from which the complete
model of the atmosphere can be built.
'''
heights = np.array([-8.3,
8.85,
30])
Expand Down Expand Up @@ -200,7 +207,10 @@ def mars_conditions():



def viscosidad(temp, planet):
def viscosity(temp, planet):
'''Calculates the value for viscosity in microPascal*second
for a certain temperature'''

if (planet == 'Earth'):
c = 120
lamb = 1.512041288
Expand All @@ -213,16 +223,20 @@ def viscosidad(temp, planet):


def Reynolds(dens, longitud, vel, visc):
'''Calculates the Reynolds number'''
re = 1000000 * dens * longitud * vel / visc
return re


def aero_conditions(ambient_data):
'''Given a certain conditions, return the value of the Mach and Reynolds
numbers, in that order.
'''
(planet, chord, height, speed_type, speed) = ambient_data
planet_dic = {'Mars':mars_conditions(), 'Earth':earth_conditions()}


sound = (1.4 *presion(height, planet_dic[planet]) / densidad(height,planet_dic[planet]))**0.5
sound = (1.4 *pressure(height, planet_dic[planet]) / density(height,planet_dic[planet]))**0.5

if (speed_type == 'mach'):
mach = speed
Expand All @@ -234,14 +248,9 @@ def aero_conditions(ambient_data):
print('error in the data, invalid speed parameter')



re = Reynolds(densidad(height, planet_dic[planet]), chord, vel, viscosidad(temperatura(height, planet_dic[planet]), planet))
visc = viscosity(temperature(height, planet_dic[planet]), planet)
re = Reynolds(density(height, planet_dic[planet]), chord, vel, visc)



return [mach, re]
#
#ambient_data = ('Earth', 03.0003, 11, 'speed', 30.1)
#
#result = aero_conditions(('Earth', 0.03, 11, 'mach', 0.1))
#print(result)
41 changes: 21 additions & 20 deletions ...action/Genetic_algorithm_files/analice.py → ...action/Genetic_algorithm_files/analyze.py
View file
Original file line number Diff line number Diff line change
Expand Up @@ -7,41 +7,38 @@
This is a submodule for the genetic algorithm that is explained in
https://docs.google.com/presentation/d/1_78ilFL-nbuN5KB5FmNeo-EIZly1PjqxqIB-ant-GfM/edit?usp=sharing
This script is the main program. It will call the different submodules
and manage the data transfer between them in order to achieve the
genetic optimization of the profile.
This script is the analysis subprogram. Its objective is to assign a score to
every airfoil by reading the aerodynamic characteristics that XFoil
has calculated.
'''



import subprocess
import sys
import os
import interfaz as interfaz

import numpy as np
import initial as initial



#generation = 0
#starting_profiles = 20
#
#genome = initial.start_pop(starting_profiles)
#
#interfaz.xfoil_calculate_population(generation,genome)
#
#num_pop = genome_matrix.shape[0]

def pop_analice (generation, num_pop):
'''For a given generation and number of airfoils, returns an array which
contains the maximun Lift Coefficient and Maximum Aerodinamic Efficiency
for every airfoil.
'''
pop_results = np.zeros([num_pop,2])
for profile_number in np.arange(1,num_pop+1,1):
pop_results[profile_number - 1, :] = profile_analice (generation, profile_number)

return pop_results


def profile_analice (generation, profile_number):
def profile_analice (generation, profile_number):
'''For a given generation and profile, searches for the results of the
aerodynamic analysis made in Xfoil. Then, searches for the maximum
values of the Lift Coefficient and Aerodynamic Efficiency and returns them
as an 1x2 array.
'''
profile_name = 'gen' + str(generation) + 'prof' + str(profile_number)
data_root = "aerodata\data" + profile_name + '.txt'
datos = np.loadtxt(data_root, skiprows=12, usecols=[1,2])
Expand All @@ -60,14 +57,18 @@ def profile_analice (generation, profile_number):
return np.array([clmax , maxefic])

def adimension(array):
'''Adimensionalyzes an array with its maximun value
'''
max_value = max(array)
adim = array / max_value
return adim

def score(generation, num_pop):

def score(generation, num_pop, weights):
'''For a given generation, number of airfoils and weight parameters, returns
an array of the scores of all airfoils.
'''
pop_results = pop_analice (generation, num_pop)
cl_score = adimension(pop_results[:,0])
efic_score = adimension(pop_results[:,1])
total_score = 0.3 * cl_score + 0.7 * efic_score
total_score = weights[0] * cl_score + weights[1] * efic_score
return total_score
20 changes: 11 additions & 9 deletions aeropy/Xfoil_Interaction/Genetic_algorithm_files/cross.py
View file
Original file line number Diff line number Diff line change
Expand Up @@ -7,25 +7,27 @@
This is a submodule for the genetic algorithm that is explained in
https://docs.google.com/presentation/d/1_78ilFL-nbuN5KB5FmNeo-EIZly1PjqxqIB-ant-GfM/edit?usp=sharing
This script is the main program. It will call the different submodules
and manage the data transfer between them in order to achieve the
genetic optimization of the profile.
This script is the cross subprogramme. Its objective is to generate
a whole new population genome from the genome of the previous generation
winners (parents).
In order to eliminate the chance of randomly getting worse results,
the parents are preserved as the first elements of the new population.
'''



import subprocess
import sys
import os
import interfaz as interfaz
import numpy as np
import initial as initial

import numpy as np



def cross(parents, num_pop):
'''Generates a population of (num_pop) airfoil genomes by mixing randomly
the genomes of the given parents.
The parents are preserved as the first elements of the new population.
'''
children = np.zeros([num_pop, 16])
num_parents = parents.shape[0]
children[0:num_parents] = parents
Expand Down
Loading

0 comments on commit 172a9ce

Please sign in to comment.