from IPython.display import YouTubeVideo
YouTubeVideo('_symWK4T7n0')

from IPython.display import YouTubeVideo
YouTubeVideo('jIqIupqTJU8')

import math
import numpy
import csv
from scipy import integrate
from matplotlib import pyplot

#Creating Colors for graphs
color05 = '#791532'
color10 = '#C2607C'
color15 = '#864E18'
color20 = '#D7A06A'
color25 = '#114653'
color30 = '#447985'
color35 = '#3F7715'
color40 = '#88BF5E'
color45 = '#29195C'
color50 = '#625294'

#reads of the Airfoil geometries from the cvs data files
alpha00, G00 = numpy.loadtxt('./2_5ms/00.csv', dtype=float, delimiter=',', unpack=True)
alpha02, G02 = numpy.loadtxt('./2_5ms/02.csv', dtype=float, delimiter=',', unpack=True)
alpha03, G03 = numpy.loadtxt('./2_5ms/03.csv', dtype=float, delimiter=',', unpack=True)
alpha04, G04 = numpy.loadtxt('./2_5ms/04.csv', dtype=float, delimiter=',', unpack=True)
alpha05, G05 = numpy.loadtxt('./2_5ms/05.csv', dtype=float, delimiter=',', unpack=True)
alpha06, G06 = numpy.loadtxt('./2_5ms/06.csv', dtype=float, delimiter=',', unpack=True)
alpha07, G07 = numpy.loadtxt('./2_5ms/07.csv', dtype=float, delimiter=',', unpack=True)
alpha09, G09 = numpy.loadtxt('./2_5ms/09.csv', dtype=float, delimiter=',', unpack=True)
alpha12, G12 = numpy.loadtxt('./2_5ms/12.csv', dtype=float, delimiter=',', unpack=True)
alpha17, G17 = numpy.loadtxt('./2_5ms/17.csv', dtype=float, delimiter=',', unpack=True)

# #lets plot the geometry
%matplotlib inline

#Plotting
size = 10
pyplot.figure(figsize=(size,size))# (y_end-y_start)/(x_end-x_start)*size))
pyplot.grid(True)
pyplot.xlabel('(Alpha) Angle of Attack', fontsize=16)
pyplot.ylabel('(CL) Coefficient of Lift', fontsize=16)
pyplot.title('CL vs Alpha at 2.5 m/s', fontsize=20)
pyplot.xlim(0, 10.0)
pyplot.ylim(0.2, 1.0)
pyplot.plot(alpha00, G00, label="No Ground Effect",
            color=color05, linestyle='--', linewidth=6);
pyplot.plot(alpha02, G02, label="0.2 m",
            color=color10, linestyle='-', linewidth=4);
pyplot.plot(alpha03, G03, label="0.3 m",
            color=color15, linestyle='-', linewidth=4);
pyplot.plot(alpha04, G04, label="0.4 m",
            color=color20, linestyle='-', linewidth=4);
pyplot.plot(alpha05, G05, label="0.5 m",
            color=color25, linestyle='-', linewidth=4);
pyplot.plot(alpha06, G06, label="0.6 m",
            color=color30, linestyle='-', linewidth=4);
pyplot.plot(alpha07, G07, label="0.7 m",
            color=color35, linestyle='-', linewidth=4);
pyplot.plot(alpha09, G09, label="0.9 m",
            color=color40, linestyle='-', linewidth=4);
pyplot.plot(alpha12, G12, label="1.2 m",
            color=color45, linestyle='-', linewidth=4);
pyplot.plot(alpha17, G17, label="1.7 m",
            color=color50, linestyle='-', linewidth=4);
pyplot.legend(bbox_to_anchor=(1.05, 1), loc=2, borderaxespad=0.);

#reads of the Airfoil geometries from the cvs data files
alpha00, G00 = numpy.loadtxt('./3ms/00.csv', dtype=float, delimiter=',', unpack=True)
alpha02, G02 = numpy.loadtxt('./3ms/02.csv', dtype=float, delimiter=',', unpack=True)
alpha03, G03 = numpy.loadtxt('./3ms/03.csv', dtype=float, delimiter=',', unpack=True)
alpha04, G04 = numpy.loadtxt('./3ms/04.csv', dtype=float, delimiter=',', unpack=True)
alpha05, G05 = numpy.loadtxt('./3ms/05.csv', dtype=float, delimiter=',', unpack=True)
alpha06, G06 = numpy.loadtxt('./3ms/06.csv', dtype=float, delimiter=',', unpack=True)
alpha07, G07 = numpy.loadtxt('./3ms/07.csv', dtype=float, delimiter=',', unpack=True)
alpha09, G09 = numpy.loadtxt('./3ms/09.csv', dtype=float, delimiter=',', unpack=True)
alpha11, G10 = numpy.loadtxt('./3ms/10.csv', dtype=float, delimiter=',', unpack=True)
alpha16, G16 = numpy.loadtxt('./3ms/16.csv', dtype=float, delimiter=',', unpack=True)

# #lets plot the geometry
%matplotlib inline

#Plotting
size = 10
pyplot.figure(figsize=(size,size))# (y_end-y_start)/(x_end-x_start)*size))
pyplot.grid(True)
pyplot.xlabel('(Alpha) Angle of Attack', fontsize=16)
pyplot.ylabel('(CL) Coefficient of Lift', fontsize=16)
pyplot.title('CL vs Alpha at 3 m/s', fontsize=20)
pyplot.xlim(0, 10.0)
pyplot.ylim(0.2, 1.0)
pyplot.plot(alpha00, G00, label="No Ground Effect",
            color=color05, linestyle='--', linewidth=6);
pyplot.plot(alpha02, G02, label="0.2 m",
            color=color10, linestyle='-', linewidth=4);
pyplot.plot(alpha03, G03, label="0.3 m",
            color=color15, linestyle='-', linewidth=4);
pyplot.plot(alpha04, G04, label="0.4 m",
            color=color20, linestyle='-', linewidth=4);
pyplot.plot(alpha05, G05, label="0.5 m",
            color=color25, linestyle='-', linewidth=4);
pyplot.plot(alpha06, G06, label="0.6 m",
            color=color30, linestyle='-', linewidth=4);
pyplot.plot(alpha07, G07, label="0.7 m",
            color=color35, linestyle='-', linewidth=4);
pyplot.plot(alpha09, G09, label="0.9 m",
            color=color40, linestyle='-', linewidth=4);
pyplot.plot(alpha12, G10, label="1.1 m",
            color=color45, linestyle='-', linewidth=4);
pyplot.plot(alpha17, G16, label="1.6 m",
            color=color50, linestyle='-', linewidth=4);
pyplot.legend(bbox_to_anchor=(1.05, 1), loc=2, borderaxespad=0.);

#reads of the Airfoil geometries from the cvs data files
alpha00, G00 = numpy.loadtxt('./10ms/00.csv', dtype=float, delimiter=',', unpack=True)
alpha02, G02 = numpy.loadtxt('./10ms/02.csv', dtype=float, delimiter=',', unpack=True)
alpha03, G03 = numpy.loadtxt('./10ms/03.csv', dtype=float, delimiter=',', unpack=True)
alpha04, G04 = numpy.loadtxt('./10ms/04.csv', dtype=float, delimiter=',', unpack=True)
alpha05, G05 = numpy.loadtxt('./10ms/05.csv', dtype=float, delimiter=',', unpack=True)
alpha06, G06 = numpy.loadtxt('./10ms/06.csv', dtype=float, delimiter=',', unpack=True)
alpha07, G07 = numpy.loadtxt('./10ms/07.csv', dtype=float, delimiter=',', unpack=True)
alpha09, G09 = numpy.loadtxt('./10ms/09.csv', dtype=float, delimiter=',', unpack=True)
alpha12, G12 = numpy.loadtxt('./10ms/12.csv', dtype=float, delimiter=',', unpack=True)
alpha17, G17 = numpy.loadtxt('./10ms/17.csv', dtype=float, delimiter=',', unpack=True)

# #lets plot the geometry
%matplotlib inline

#Plotting
size = 10
pyplot.figure(figsize=(size,size))# (y_end-y_start)/(x_end-x_start)*size))
pyplot.grid(True)
pyplot.xlabel('(Alpha) Angle of Attack', fontsize=16)
pyplot.ylabel('(CL) Coefficient of Lift', fontsize=16)
pyplot.title('CL vs Alpha at 5 m/s', fontsize=20)
pyplot.xlim(0, 10.0)
pyplot.ylim(0.2, 1.0)
pyplot.plot(alpha00, G00, label="No Ground Effect",
            color=color05, linestyle='--', linewidth=6);
pyplot.plot(alpha02, G02, label="0.2 m",
            color=color10, linestyle='-', linewidth=4);
pyplot.plot(alpha03, G03, label="0.3 m",
            color=color15, linestyle='-', linewidth=4);
pyplot.plot(alpha04, G04, label="0.4 m",
            color=color20, linestyle='-', linewidth=4);
pyplot.plot(alpha05, G05, label="0.5 m",
            color=color25, linestyle='-', linewidth=4);
pyplot.plot(alpha06, G06, label="0.6 m",
            color=color30, linestyle='-', linewidth=4);
pyplot.plot(alpha07, G07, label="0.8 m",
            color=color35, linestyle='-', linewidth=4);
pyplot.plot(alpha09, G09, label="1.0 m",
            color=color40, linestyle='-', linewidth=4);
pyplot.plot(alpha12, G12, label="1.5 m",
            color=color45, linestyle='-', linewidth=4);
pyplot.plot(alpha17, G17, label="2.1 m",
            color=color50, linestyle='-', linewidth=4);
pyplot.legend(bbox_to_anchor=(1.05, 1), loc=2, borderaxespad=0.);

#reads of the Airfoil geometries from the cvs data files
alpha00, G00 = numpy.loadtxt('./5ms/00.csv', dtype=float, delimiter=',', unpack=True)
alpha02, G02 = numpy.loadtxt('./5ms/02.csv', dtype=float, delimiter=',', unpack=True)
alpha03, G03 = numpy.loadtxt('./5ms/03.csv', dtype=float, delimiter=',', unpack=True)
alpha04, G04 = numpy.loadtxt('./5ms/04.csv', dtype=float, delimiter=',', unpack=True)
alpha05, G05 = numpy.loadtxt('./5ms/05.csv', dtype=float, delimiter=',', unpack=True)
alpha06, G06 = numpy.loadtxt('./5ms/06.csv', dtype=float, delimiter=',', unpack=True)
alpha08, G08 = numpy.loadtxt('./5ms/08.csv', dtype=float, delimiter=',', unpack=True)
alpha10, G10 = numpy.loadtxt('./5ms/10.csv', dtype=float, delimiter=',', unpack=True)
alpha15, G15 = numpy.loadtxt('./5ms/15.csv', dtype=float, delimiter=',', unpack=True)
alpha21, G21 = numpy.loadtxt('./5ms/21.csv', dtype=float, delimiter=',', unpack=True)

# #lets plot the geometry
%matplotlib inline

#Plotting
size = 10
pyplot.figure(figsize=(size,size))# (y_end-y_start)/(x_end-x_start)*size))
pyplot.grid(True)
pyplot.xlabel('(Alpha) Angle of Attack', fontsize=16)
pyplot.ylabel('(CL) Coefficient of Lift', fontsize=16)
pyplot.title('CL vs Alpha at 10 m/s', fontsize=20)
pyplot.xlim(0, 10.0)
pyplot.ylim(0.2, 1.0)
pyplot.plot(alpha00, G00, label="No Ground Effect",
            color=color05, linestyle='--', linewidth=6);
pyplot.plot(alpha02, G02, label="0.2 m",
            color=color10, linestyle='-', linewidth=4);
pyplot.plot(alpha03, G03, label="0.3 m",
            color=color15, linestyle='-', linewidth=4);
pyplot.plot(alpha04, G04, label="0.4 m",
            color=color20, linestyle='-', linewidth=4);
pyplot.plot(alpha05, G05, label="0.5 m",
            color=color25, linestyle='-', linewidth=4);
pyplot.plot(alpha06, G06, label="0.6 m",
            color=color30, linestyle='-', linewidth=4);
pyplot.plot(alpha08, G08, label="0.8 m",
            color=color35, linestyle='-', linewidth=4);
pyplot.plot(alpha10, G10, label="1.0 m",
            color=color40, linestyle='-', linewidth=4);
pyplot.plot(alpha15, G15, label="1.5 m",
            color=color45, linestyle='-', linewidth=4);
pyplot.plot(alpha21, G21, label="2.1 m",
            color=color50, linestyle='-', linewidth=4);
pyplot.legend(bbox_to_anchor=(1.05, 1), loc=2, borderaxespad=0.);

#reads of the Airfoil geometries from the cvs data files
alpha00, G00 = numpy.loadtxt('./Full5ms/00.csv', dtype=float, delimiter=',', unpack=True)
alpha05, G05 = numpy.loadtxt('./Full5ms/05.csv', dtype=float, delimiter=',', unpack=True)
alpha06, G06 = numpy.loadtxt('./Full5ms/06.csv', dtype=float, delimiter=',', unpack=True)
alpha07, G07 = numpy.loadtxt('./Full5ms/07.csv', dtype=float, delimiter=',', unpack=True)
alpha08, G08 = numpy.loadtxt('./Full5ms/08.csv', dtype=float, delimiter=',', unpack=True)
alpha09, G09 = numpy.loadtxt('./Full5ms/09.csv', dtype=float, delimiter=',', unpack=True)
alpha10, G10 = numpy.loadtxt('./Full5ms/10.csv', dtype=float, delimiter=',', unpack=True)

# #lets plot the geometry
%matplotlib inline

#Plotting
size = 10
pyplot.figure(figsize=(size,size))# (y_end-y_start)/(x_end-x_start)*size))
pyplot.grid(True)
pyplot.xlabel('(Alpha) Angle of Attack', fontsize=16)
pyplot.ylabel('(CL) Coefficient of Lift', fontsize=16)
pyplot.title('CL vs Alpha at 5 m/s', fontsize=20)
pyplot.xlim(-3.0, 1.5)
pyplot.ylim(0.0, 0.5)
pyplot.plot(alpha00, G00, label="No Ground Effect",
            color=color05, linestyle='--', linewidth=6);
pyplot.plot(alpha05, G05, label="0.5 m",
            color=color10, linestyle='-', linewidth=4);
pyplot.plot(alpha06, G06, label="0.6 m",
            color=color15, linestyle='-', linewidth=4);
pyplot.plot(alpha07, G07, label="0.7 m",
            color=color20, linestyle='-', linewidth=4);
pyplot.plot(alpha08, G08, label="0.8 m",
            color=color25, linestyle='-', linewidth=4);
pyplot.plot(alpha09, G09, label="0.9 m",
            color=color30, linestyle='-', linewidth=4);
pyplot.plot(alpha10, G10, label="1.0 m",
            color=color35, linestyle='-', linewidth=4);
pyplot.legend(bbox_to_anchor=(1.05, 1), loc=2, borderaxespad=0.);

#reads of the Airfoil geometries from the cvs data files
alpha00, G00 = numpy.loadtxt('./Full10ms/00.csv', dtype=float, delimiter=',', unpack=True)
alpha04, G04 = numpy.loadtxt('./Full10ms/04.csv', dtype=float, delimiter=',', unpack=True)
alpha05, G05 = numpy.loadtxt('./Full10ms/05.csv', dtype=float, delimiter=',', unpack=True)
alpha06, G06 = numpy.loadtxt('./Full10ms/06.csv', dtype=float, delimiter=',', unpack=True)
alpha07, G07 = numpy.loadtxt('./Full10ms/07.csv', dtype=float, delimiter=',', unpack=True)
alpha08, G08 = numpy.loadtxt('./Full10ms/08.csv', dtype=float, delimiter=',', unpack=True)
alpha09, G09 = numpy.loadtxt('./Full10ms/09.csv', dtype=float, delimiter=',', unpack=True)
alpha10, G10 = numpy.loadtxt('./Full10ms/10.csv', dtype=float, delimiter=',', unpack=True)

# #lets plot the geometry
%matplotlib inline

#Plotting
size = 10
pyplot.figure(figsize=(size,size))# (y_end-y_start)/(x_end-x_start)*size))
pyplot.grid(True)
pyplot.xlabel('(Alpha) Angle of Attack', fontsize=16)
pyplot.ylabel('(CL) Coefficient of Lift', fontsize=16)
pyplot.title('CL vs Alpha at 10 m/s', fontsize=20)
pyplot.xlim(-3.0, 5.0)
pyplot.ylim(0.0, 0.7)
pyplot.plot(alpha00, G00, label="No Ground Effect",
            color=color05, linestyle='--', linewidth=6);
pyplot.plot(alpha04, G04, label="0.4 m",
            color=color10, linestyle='-', linewidth=4);
pyplot.plot(alpha05, G05, label="0.5 m",
            color=color15, linestyle='-', linewidth=4);
pyplot.plot(alpha06, G06, label="0.6 m",
            color=color20, linestyle='-', linewidth=4);
pyplot.plot(alpha07, G07, label="0.7 m",
            color=color25, linestyle='-', linewidth=4);
pyplot.plot(alpha08, G08, label="0.8 m",
            color=color30, linestyle='-', linewidth=4);
pyplot.plot(alpha09, G09, label="0.9 m",
            color=color35, linestyle='-', linewidth=4);
pyplot.plot(alpha10, G10, label="1.0 m",
            color=color40, linestyle='-', linewidth=4);
pyplot.legend(bbox_to_anchor=(1.05, 1), loc=2, borderaxespad=0.);

#reads of the Airfoil geometries from the cvs data files
alpha00, G00 = numpy.loadtxt('./Full20ms/00.csv', dtype=float, delimiter=',', unpack=True)
alpha04, G04 = numpy.loadtxt('./Full20ms/04.csv', dtype=float, delimiter=',', unpack=True)
alpha05, G05 = numpy.loadtxt('./Full20ms/05.csv', dtype=float, delimiter=',', unpack=True)
alpha06, G06 = numpy.loadtxt('./Full20ms/06.csv', dtype=float, delimiter=',', unpack=True)
alpha07, G07 = numpy.loadtxt('./Full20ms/07.csv', dtype=float, delimiter=',', unpack=True)
alpha08, G08 = numpy.loadtxt('./Full20ms/08.csv', dtype=float, delimiter=',', unpack=True)
alpha09, G09 = numpy.loadtxt('./Full20ms/09.csv', dtype=float, delimiter=',', unpack=True)
alpha10, G10 = numpy.loadtxt('./Full20ms/10.csv', dtype=float, delimiter=',', unpack=True)

# #lets plot the geometry
%matplotlib inline

#Plotting
size = 10
pyplot.figure(figsize=(size,size))# (y_end-y_start)/(x_end-x_start)*size))
pyplot.grid(True)
pyplot.xlabel('(Alpha) Angle of Attack', fontsize=16)
pyplot.ylabel('(CL) Coefficient of Lift', fontsize=16)
pyplot.title('CL vs Alpha at 20 m/s', fontsize=20)
pyplot.xlim(-3.0, 5.5)
pyplot.ylim(0.0, 0.8)
pyplot.plot(alpha00, G00, label="No Ground Effect",
            color=color05, linestyle='--', linewidth=6);
pyplot.plot(alpha04, G04, label="0.4 m",
            color=color10, linestyle='-', linewidth=4);
pyplot.plot(alpha05, G05, label="0.5 m",
            color=color15, linestyle='-', linewidth=4);
pyplot.plot(alpha06, G06, label="0.6 m",
            color=color20, linestyle='-', linewidth=4);
pyplot.plot(alpha07, G07, label="0.7 m",
            color=color25, linestyle='-', linewidth=4);
pyplot.plot(alpha08, G08, label="0.8 m",
            color=color30, linestyle='-', linewidth=4);
pyplot.plot(alpha09, G09, label="0.9 m",
            color=color35, linestyle='-', linewidth=4);
pyplot.plot(alpha10, G10, label="1.0 m",
            color=color40, linestyle='-', linewidth=4);
pyplot.legend(bbox_to_anchor=(1.05, 1), loc=2, borderaxespad=0.);

#George Teel
#4/20/2015
#
#Super basic python script to export vertices of an object,
#In this case our airfoil shape, and export the locations
#so that XFLR5 can import that shape and then analyze the
#airfoils properly.
#
#This code was figured out from random websites and Blender's wikipedia page.
#

#Import What we need
import bpy

#Sets airfoil mesh object
airfoildata = bpy.data.meshes['Wing']

#Open File
myFile = open('D:/School Documents/AeroHydro/Project/Wing.dat','w')

#Cycles through vertices
for vert in airfoildata.vertices:
    myFile.write( '%f %f \n' % (vert.co.x, vert.co.y) )

#Closes File
myFile.close()


#George Teel
#5/4/2015
#
#Super basic python script to export vertices of an object,
#In this case our body shape, and export the locations
#so that XFLR5 can import that shape and then analyze it
#
#This code was figured out from random websites and Blender's wikipedia page.
#

#Import What we need
import bpy

#Sets airfoil mesh object
bodydata = bpy.data.meshes['BodySimple']

#Open File
myFile = open('D:/School Documents/AeroHydro/Project/EkranoBodySimpledata.dat','w')

#Create the intro Info
myFile.write('Ekranoplan SimpleBody\n')
myFile.write(' \n')
myFile.write('Right Surface Points \n')
myFile.write('        x()        y()          z()\n')
#Cycles through vertices
for vert in bodydata.vertices:
    myFile.write( '      %f      %f      %f\n' % (vert.co.x, vert.co.z, vert.co.y) )

#Closes File
myFile.close()

#Still need to modify the data to follow the correct format, but should be easy from there on out.

from IPython.core.display import HTML
def css_styling():
    styles = open('./project.css', 'r').read()
    return HTML(styles)
css_styling()