├── requirements.txt ├── docs ├── tutorial.rst ├── _build │ ├── html │ │ ├── _sources │ │ │ ├── tutorial.txt │ │ │ ├── pyxfoil_doc.txt │ │ │ ├── airfoil_module.txt │ │ │ ├── xfoil_functions.txt │ │ │ ├── xfoil_module.txt │ │ │ ├── main_module.txt │ │ │ ├── aero_doc.txt │ │ │ ├── aero_module.txt │ │ │ └── index.txt │ │ ├── objects.inv │ │ ├── _static │ │ │ ├── down.png │ │ │ ├── file.png │ │ │ ├── logo.png │ │ │ ├── plus.png │ │ │ ├── up.png │ │ │ ├── minus.png │ │ │ ├── comment.png │ │ │ ├── ajax-loader.gif │ │ │ ├── up-pressed.png │ │ │ ├── comment-bright.png │ │ │ ├── comment-close.png │ │ │ ├── down-pressed.png │ │ │ ├── pygments.css │ │ │ ├── doctools.js │ │ │ ├── underscore.js │ │ │ └── alabaster.css │ │ ├── _images │ │ │ └── elliptical_LLT.png │ │ ├── .buildinfo │ │ ├── pyxfoil_doc.html │ │ ├── _modules │ │ │ ├── index.html │ │ │ └── AeroPy.html │ │ ├── search.html │ │ ├── tutorial.html │ │ ├── py-modindex.html │ │ ├── airfoil_module.html │ │ ├── aero_doc.html │ │ ├── searchindex.js │ │ ├── genindex.html │ │ ├── main_module.html │ │ ├── index.html │ │ └── aero_module.html │ └── doctrees │ │ ├── index.doctree │ │ ├── aero_doc.doctree │ │ ├── tutorial.doctree │ │ ├── aero_module.doctree │ │ ├── environment.pickle │ │ ├── main_module.doctree │ │ ├── pyxfoil_doc.doctree │ │ ├── airfoil_module.doctree │ │ ├── xfoil_module.doctree │ │ └── xfoil_functions.doctree ├── images │ ├── logo.png │ ├── elliptical_LLT.png │ └── logo.svg ├── _static │ └── logo.png ├── airfoil_module.rst ├── xfoil_module.rst ├── main_module.rst ├── aero_module.rst ├── index.rst ├── make.bat ├── Makefile └── conf.py ├── pplot.exe ├── pxplot.exe ├── xfoil.exe ├── README.md ├── CST_aerodynamic_performance.py ├── LICENSE ├── plotting.py ├── test_inflections.py ├── .gitignore ├── sampled_airfoil_data.csv ├── shape_study.p └── AeroPy.py /requirements.txt: -------------------------------------------------------------------------------- 1 | numpy 2 | 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https://raw.githubusercontent.com/AeroPython/AeroPy-1/master/docs/_build/doctrees/xfoil_functions.doctree -------------------------------------------------------------------------------- /docs/_build/html/.buildinfo: -------------------------------------------------------------------------------- 1 | # Sphinx build info version 1 2 | # This file hashes the configuration used when building these files. When it is not found, a full rebuild will be done. 3 | config: 43ce4afafbc7b21ca51f3e159561c44c 4 | tags: 645f666f9bcd5a90fca523b33c5a78b7 5 | -------------------------------------------------------------------------------- /docs/airfoil_module.rst: -------------------------------------------------------------------------------- 1 | Airfoil Module Documentation 2 | ********************************* 3 | 4 | The functions herein defined are purposely made for generating NACA airfoils, flapped airfoils and CST airfoils. 5 | 6 | Core Function 7 | =========================== 8 | 9 | Auxiliary Functions 10 | =========================== 11 | 12 | Utility Functions 13 | ==================== 14 | -------------------------------------------------------------------------------- /docs/_build/html/_sources/airfoil_module.txt: -------------------------------------------------------------------------------- 1 | Airfoil Module Documentation 2 | ********************************* 3 | 4 | The functions herein defined are purposely made for generating NACA airfoils, flapped airfoils and CST airfoils. 5 | 6 | Core Function 7 | =========================== 8 | 9 | Auxiliary Functions 10 | =========================== 11 | 12 | Utility Functions 13 | ==================== 14 | -------------------------------------------------------------------------------- /docs/xfoil_module.rst: -------------------------------------------------------------------------------- 1 | Xfoil Module Documentation 2 | ********************************* 3 | 4 | The functions herein defined are purposely made for use with Xfoil. 5 | 6 | Core Function 7 | =========================== 8 | .. autofunction:: xfoil_module.call 9 | 10 | Auxiliary Functions 11 | =========================== 12 | .. automodule:: xfoil_module 13 | :members: 14 | :exclude-members: call, find_alpha_L_0, M_crit, find_coefficients 15 | 16 | Utility Functions 17 | ==================== 18 | .. autofunction:: xfoil_module.find_coefficients 19 | .. autofunction:: xfoil_module.find_alpha_L_0 20 | .. autofunction:: xfoil_module.M_crit 21 | -------------------------------------------------------------------------------- /docs/_build/html/_sources/xfoil_functions.txt: -------------------------------------------------------------------------------- 1 | Documentation for Xfoil Functions 2 | ********************************* 3 | 4 | The functions herein defined are purposely made for use with Xfoil. 5 | 6 | Core Function 7 | =========================== 8 | .. autofunction:: xfoil_tools.call 9 | 10 | Auxiliary Functions 11 | =========================== 12 | .. automodule:: xfoil_tools 13 | :members: 14 | :exclude-members: call, find_alpha_L_0, M_crit, find_coefficients 15 | 16 | Utility Functions 17 | ==================== 18 | .. autofunction:: xfoil_tools.find_coefficients 19 | .. autofunction:: xfoil_tools.find_alpha_L_0 20 | .. autofunction:: xfoil_tools.M_crit -------------------------------------------------------------------------------- /docs/_build/html/_sources/xfoil_module.txt: -------------------------------------------------------------------------------- 1 | Xfoil Module Documentation 2 | ********************************* 3 | 4 | The functions herein defined are purposely made for use with Xfoil. 5 | 6 | Core Function 7 | =========================== 8 | .. autofunction:: xfoil_module.call 9 | 10 | Auxiliary Functions 11 | =========================== 12 | .. automodule:: xfoil_module 13 | :members: 14 | :exclude-members: call, find_alpha_L_0, M_crit, find_coefficients 15 | 16 | Utility Functions 17 | ==================== 18 | .. autofunction:: xfoil_module.find_coefficients 19 | .. autofunction:: xfoil_module.find_alpha_L_0 20 | .. autofunction:: xfoil_module.M_crit 21 | -------------------------------------------------------------------------------- /README.md: -------------------------------------------------------------------------------- 1 | [![DOI](https://zenodo.org/badge/20401/leal26/AeroPy.svg)](https://zenodo.org/badge/latestdoi/20401/leal26/AeroPy) 2 | 3 | # AeroPy 4 | AeroPy is an library for calculating aerodynamic properties. The main feature of this library is the Python interface with XFOIL. The main objective of this library is to be able to use XFOIL via Python iteratively in a total of 4 lines total (one line for most uses). Through this interface coupling with other softwares (Abaqus, Ansys, etc) is possible and iterative processes (optimization, design sensitivity) are possible. For a thorough explanation please check the documentation and the tutorials. For thorough documentation and tutorials please check the [AeroPy website](http://aeropy.readthedocs.org/) 5 | -------------------------------------------------------------------------------- /CST_aerodynamic_performance.py: -------------------------------------------------------------------------------- 1 | import numpy as np 2 | import matplotlib.pyplot as plt 3 | 4 | import xfoil_module as xf 5 | from CST_module import * 6 | from aero_module import Reynolds 7 | from airfoil_module import CST, create_x 8 | 9 | Au = [0.23993240191629417, 0.34468227138908186, 0.18125405377549103, 10 | 0.35371349126072665, 0.2440815012119143, 0.25724974995738387] 11 | Al = [0.18889012559339036, -0.24686758992053115, 0.077569769493868401, 12 | -0.547827192265256, -0.0047342206759065641, -0.23994805474814629] 13 | c_avian = 0.36 #m 14 | deltaz = 0.0093943568219451313*c_avian 15 | 16 | airfoil = 'avian' 17 | x = create_x(1., distribution = 'linear') 18 | y = CST(x, 1., [deltaz/2., deltaz/2.], Au = Au, Al= Al) 19 | # Create file for Xfoil to read coordinates 20 | xf.create_input(x, y['u'], y['l'], airfoil, different_x_upper_lower = False) 21 | print 'Reynolds: ', Reynolds(10000, 30, c_avian) 22 | Data = xf.find_coefficients(airfoil, 2., Reynolds=Reynolds(10000, 30, c_avian), iteration=100, NACA=False) 23 | print Data -------------------------------------------------------------------------------- /docs/main_module.rst: -------------------------------------------------------------------------------- 1 | AeroPy Documentation 2 | ********************* 3 | 4 | This project was elaborated because of the need of optimizing an airfoil 5 | according to its aerodynamic and structural performance (conference paper). 6 | Contrary to available options such as XFLR5, AeroPy aims to be an open source 7 | Python code. It is a quick and easy way to find the aerodynamic pressure and the 8 | drag and lift coefficients through the use of MIT's XFOIL embedded in Python. 9 | Contrary to the other libraries, AeroPy does not have a GUI and is intended 10 | to be used in Python codes for optimizations or any other process that requires 11 | several aerodynamic analysis. 12 | 13 | AeroPy is separated in three modules: (it is programmed in such a way that a new 14 | module can be easily inserted) 15 | 16 | - xfoil: contains all the functions relating to XFOIL. 17 | - aero: contains all functions related to aerodynamics, but not related to XFOIL. 18 | - AeroPy: imports all functions and acts as the intersection of all different 19 | modules 20 | 21 | Code 22 | ==== 23 | 24 | .. automodule:: AeroPy 25 | :members: 26 | -------------------------------------------------------------------------------- /docs/_build/html/_sources/main_module.txt: -------------------------------------------------------------------------------- 1 | AeroPy Documentation 2 | ********************* 3 | 4 | This project was elaborated because of the need of optimizing an airfoil 5 | according to its aerodynamic and structural performance (conference paper). 6 | Contrary to available options such as XFLR5, AeroPy aims to be an open source 7 | Python code. It is a quick and easy way to find the aerodynamic pressure and the 8 | drag and lift coefficients through the use of MIT's XFOIL embedded in Python. 9 | Contrary to the other libraries, AeroPy does not have a GUI and is intended 10 | to be used in Python codes for optimizations or any other process that requires 11 | several aerodynamic analysis. 12 | 13 | AeroPy is separated in three modules: (it is programmed in such a way that a new 14 | module can be easily inserted) 15 | 16 | - xfoil: contains all the functions relating to XFOIL. 17 | - aero: contains all functions related to aerodynamics, but not related to XFOIL. 18 | - AeroPy: imports all functions and acts as the intersection of all different 19 | modules 20 | 21 | Code 22 | ==== 23 | 24 | .. automodule:: AeroPy 25 | :members: 26 | -------------------------------------------------------------------------------- /LICENSE: -------------------------------------------------------------------------------- 1 | The MIT License (MIT) 2 | 3 | Copyright (c) 2015 leal26 4 | 5 | Permission is hereby granted, free of charge, to any person obtaining a copy 6 | of this software and associated documentation files (the "Software"), to deal 7 | in the Software without restriction, including without limitation the rights 8 | to use, copy, modify, merge, publish, distribute, sublicense, and/or sell 9 | copies of the Software, and to permit persons to whom the Software is 10 | furnished to do so, subject to the following conditions: 11 | 12 | The above copyright notice and this permission notice shall be included in all 13 | copies or substantial portions of the Software. 14 | 15 | THE SOFTWARE IS PROVIDED "AS IS", WITHOUT WARRANTY OF ANY KIND, EXPRESS OR 16 | IMPLIED, INCLUDING BUT NOT LIMITED TO THE WARRANTIES OF MERCHANTABILITY, 17 | FITNESS FOR A PARTICULAR PURPOSE AND NONINFRINGEMENT. IN NO EVENT SHALL THE 18 | AUTHORS OR COPYRIGHT HOLDERS BE LIABLE FOR ANY CLAIM, DAMAGES OR OTHER 19 | LIABILITY, WHETHER IN AN ACTION OF CONTRACT, TORT OR OTHERWISE, ARISING FROM, 20 | OUT OF OR IN CONNECTION WITH THE SOFTWARE OR THE USE OR OTHER DEALINGS IN THE 21 | SOFTWARE. 22 | 23 | -------------------------------------------------------------------------------- /docs/_build/html/_sources/aero_doc.txt: -------------------------------------------------------------------------------- 1 | Documentation for Aerodynamic Functions 2 | *************************************** 3 | 4 | Lifting Line Theory 5 | =================== 6 | If :math:`\theta_0` is an arbitrary span-wise location: 7 | 8 | .. math:: 9 | \alpha (\theta_o)=\frac{2b}{\pi c(\theta_o)} \sum_1^N A_n sin(n \theta_o) + \alpha_{L=0}(\theta_o) + \sum_1^N n A_n \frac{sin(n\theta_o)}{sin(\theta_o)} 10 | :label: LLT_full 11 | 12 | Each equation has :math:`N` unknowns (:math:`A_n`), so if there are N :math:`\theta_o`, we have NxN system, which in Einstein notation can be written as: 13 | 14 | .. math:: 15 | C_{ij}A_{i}=D_{i} 16 | :label: LLT_simple 17 | 18 | where, :math:`i=0,...,N`, :math:`j=0,...,N` and : 19 | 20 | .. math:: 21 | C_{ij}= \left( \frac{2b}{\pi c(j)} + \frac{n}{sin \theta(i)} \right) sin(n \theta(i)) 22 | :label: C 23 | 24 | .. math:: 25 | A_i=A(i) 26 | :label: A 27 | 28 | .. math:: 29 | D_i=\alpha(i)-\alpha_{L=0}(i) 30 | :label: D 31 | 32 | where :math:`n=1,3,5,...,N-1`. Since we are considering a symmetric wing, all of the even terms would cancel each other 33 | 34 | .. figure:: images/elliptical_LLT.png 35 | :align: center 36 | -------------------------------------------------------------------------------- /docs/aero_module.rst: -------------------------------------------------------------------------------- 1 | Aerodynamic Module Documentation 2 | *************************************** 3 | 4 | Lifting Line Theory 5 | =================== 6 | If :math:`\theta_0` is an arbitrary span-wise location: 7 | 8 | .. math:: 9 | \alpha (\theta_o)=\frac{2b}{\pi c(\theta_o)} \sum_1^N A_n sin(n \theta_o) + \alpha_{L=0}(\theta_o) + \sum_1^N n A_n \frac{sin(n\theta_o)}{sin(\theta_o)} 10 | :label: LLT_full 11 | 12 | Each equation has :math:`N` unknowns (:math:`A_n`), so if there are N :math:`\theta_o`, we have NxN system, which in Einstein notation can be written as: 13 | 14 | .. math:: 15 | C_{ij}A_{i}=D_{i} 16 | :label: LLT_simple 17 | 18 | where, :math:`i=0,...,N`, :math:`j=0,...,N` and : 19 | 20 | .. math:: 21 | C_{ij}= \left( \frac{2b}{\pi c(j)} + \frac{n}{sin \theta(i)} \right) sin(n \theta(i)) 22 | :label: C 23 | 24 | .. math:: 25 | A_i=A(i) 26 | :label: A 27 | 28 | .. math:: 29 | D_i=\alpha(i)-\alpha_{L=0}(i) 30 | :label: D 31 | 32 | where :math:`n=1,3,5,...,N-1`. Since we are considering a symmetric wing, all of the even terms would cancel each other 33 | 34 | .. figure:: images/elliptical_LLT.png 35 | :align: center 36 | 37 | The code 38 | ======== 39 | .. automodule:: aero_module 40 | :members: 41 | -------------------------------------------------------------------------------- /docs/_build/html/_sources/aero_module.txt: -------------------------------------------------------------------------------- 1 | Aerodynamic Module Documentation 2 | *************************************** 3 | 4 | Lifting Line Theory 5 | =================== 6 | If :math:`\theta_0` is an arbitrary span-wise location: 7 | 8 | .. math:: 9 | \alpha (\theta_o)=\frac{2b}{\pi c(\theta_o)} \sum_1^N A_n sin(n \theta_o) + \alpha_{L=0}(\theta_o) + \sum_1^N n A_n \frac{sin(n\theta_o)}{sin(\theta_o)} 10 | :label: LLT_full 11 | 12 | Each equation has :math:`N` unknowns (:math:`A_n`), so if there are N :math:`\theta_o`, we have NxN system, which in Einstein notation can be written as: 13 | 14 | .. math:: 15 | C_{ij}A_{i}=D_{i} 16 | :label: LLT_simple 17 | 18 | where, :math:`i=0,...,N`, :math:`j=0,...,N` and : 19 | 20 | .. math:: 21 | C_{ij}= \left( \frac{2b}{\pi c(j)} + \frac{n}{sin \theta(i)} \right) sin(n \theta(i)) 22 | :label: C 23 | 24 | .. math:: 25 | A_i=A(i) 26 | :label: A 27 | 28 | .. math:: 29 | D_i=\alpha(i)-\alpha_{L=0}(i) 30 | :label: D 31 | 32 | where :math:`n=1,3,5,...,N-1`. Since we are considering a symmetric wing, all of the even terms would cancel each other 33 | 34 | .. figure:: images/elliptical_LLT.png 35 | :align: center 36 | 37 | The code 38 | ======== 39 | .. automodule:: aero_module 40 | :members: 41 | -------------------------------------------------------------------------------- /plotting.py: -------------------------------------------------------------------------------- 1 | import numpy as np 2 | import pickle 3 | import math 4 | import matplotlib.pyplot as plt 5 | 6 | from airfoil_module import CST 7 | from xfoil_module import output_reader 8 | 9 | data = pickle.load(open('shape_study.p','rb')) 10 | 11 | n=5 12 | print 'For n=', n, ': ' 13 | print '\t error: ', data['error'][n-1] 14 | print '\t deltaz: ', data['deltaz'][n-1] 15 | print '\t Au: ', data['Au'][n-1] 16 | print '\t Al: ', data['Al'][n-1] 17 | 18 | filename = 'sampled_airfoil_data.csv' 19 | raw_data = output_reader(filename, separator = ', ', header = ['x', 'y']) 20 | 21 | # Rotating airfoil 22 | x_TE = (raw_data['x'][0] + raw_data['x'][-1])/2. 23 | y_TE = (raw_data['y'][0] + raw_data['y'][-1])/2. 24 | 25 | theta_TE = math.atan(-y_TE/x_TE) 26 | 27 | # position trailing edge at the x-axis 28 | processed_data = {'x':[], 'y':[]} 29 | for i in range(len(raw_data['x'])): 30 | x = raw_data['x'][i] 31 | y = raw_data['y'][i] 32 | c_theta = math.cos(theta_TE) 33 | s_theta = math.sin(theta_TE) 34 | x_rotated = c_theta*x - s_theta*y 35 | y_rotated = s_theta*x + c_theta*y 36 | processed_data['x'].append(x_rotated) 37 | processed_data['y'].append(y_rotated) 38 | raw_data = processed_data 39 | 40 | # determine what is the leading edge and the rotation angle beta 41 | processed_data = {'x':[], 'y':[]} 42 | min_x_list = [] 43 | min_y_list = [] 44 | 45 | min_x = min(raw_data['x']) 46 | min_index = raw_data['x'].index(min_x) 47 | min_y = raw_data['y'][min_index] 48 | 49 | chord = max(raw_data['x']) - min(raw_data['x']) 50 | beta = math.atan((y_TE - min_y)/(x_TE - min_x)) 51 | 52 | for i in range(len(raw_data['x'])): 53 | processed_data['x'].append((raw_data['x'][i] - min_x)/chord) 54 | processed_data['y'].append(raw_data['y'][i]/chord) 55 | raw_data = processed_data 56 | 57 | psi = np.linspace(0,1,200) 58 | xi = CST(psi, 1., [data['deltaz'][n-1]/2., data['deltaz'][n-1]/2.], Au = data['Au'][n-1], Al= data['Al'][n-1]) 59 | plt.figure() 60 | plt.plot(psi, xi['u'], psi, xi['l']) 61 | plt.scatter(raw_data['x'], raw_data['y']) 62 | n = 8 63 | plt.xlim(0,1) 64 | x = np.linspace(2,2*n,n) 65 | plt.gca().set_aspect('equal', adjustable='box') 66 | plt.show() 67 | 68 | plt.figure() 69 | plt.plot(x, data['error']) 70 | plt.scatter(x, data['error']) 71 | plt.xlabel('Number of shape functions') 72 | plt.ylabel('Hausdorff distance (adimensional)') 73 | plt.grid() 74 | plt.show() -------------------------------------------------------------------------------- /docs/index.rst: -------------------------------------------------------------------------------- 1 | .. AeroPy Documentation 2 | 3 | .. include xfoil_functions.rsf 4 | 5 | Welcome to AeroPy's, an easy to use aerodynamic tool 6 | ================================================================== 7 | AeroPy is an library for calculating aerodynamic properties. The main feature of 8 | this library is the Python interface with XFOIL. The main objective of this library is to be able 9 | to use XFOIL via Python iteratively in a total of 4 lines total (one line for most uses). 10 | Through this interface coupling with other softwares (Abaqus, Ansys, etc) is possible 11 | and iterative processes (optimization, design sensitivity) are possible. 12 | For a thorough explanation please check the documentation and the tutorials. 13 | 14 | Contents: 15 | 16 | .. toctree:: 17 | :numbered: 18 | :titlesonly: 19 | :maxdepth: 2 20 | 21 | main_module 22 | xfoil_module 23 | aero_module 24 | airfoil_module 25 | tutorial 26 | 27 | To Do 28 | ====== 29 | 30 | - Include asymmetric wing 31 | - Create airfoil and wing classes 32 | 33 | Recommended Collaborations 34 | ========================== 35 | 36 | Please use and adapt this library to your needs. There are several 37 | functionalities I wished to implement, but did not have the time. Hence 38 | I am *strongly* recommending the following collaborations: 39 | 40 | - Airfoil generator with a GUI 41 | - Atmospheric module (use the library already available in aero_module) 42 | - Extend aero_module for wings with non-constant cross sections 43 | 44 | Indices and tables 45 | ================== 46 | 47 | * :ref:`genindex` 48 | * :ref:`modindex` 49 | * :ref:`search` 50 | 51 | Examples 52 | ================== 53 | 54 | A simple example demonstrating how to use AeroPy to calculate lift, drag and 55 | moment coefficients for a NACA0012 airfoil at angle of attack of 12 degrees. 56 | 57 | .. code-block:: python 58 | 59 | from AeroPy import find_coefficients 60 | find_coefficients(airfoil='naca0012'alpha=12.) 61 | >>> {'CM': 0.0134, 'CL': 1.2453, 'Top_Xtr': 0.0194, 'CD': 0.01934, 'CDp': 0.01379, 'alpha': 12.0, 'Bot_Xtr': 1.0} 62 | 63 | Another example showing how to use AeroPy to calculate pressure coefficients for a 64 | NACA0012 in viscous flow at Reynolds = 10000000 and angle of attack of 12 degrees 65 | 66 | .. code-block:: python 67 | 68 | from AeroPy import find_pressure_coefficients 69 | find_pressure_coefficients(airfoil='naca0012', Reynolds = 1e6, alpha=12.,NACA=True) 70 | >>> 'y': [0.00126, ..., -0.00126], 'x': [1.0, ..., 1.0], 'Cp': [0.41501, ..., 0.41501]} -------------------------------------------------------------------------------- /docs/_build/html/_sources/index.txt: -------------------------------------------------------------------------------- 1 | .. AeroPy Documentation 2 | 3 | .. include xfoil_functions.rsf 4 | 5 | Welcome to AeroPy's, an easy to use aerodynamic tool 6 | ================================================================== 7 | AeroPy is an library for calculating aerodynamic properties. The main feature of 8 | this library is the Python interface with XFOIL. The main objective of this library is to be able 9 | to use XFOIL via Python iteratively in a total of 4 lines total (one line for most uses). 10 | Through this interface coupling with other softwares (Abaqus, Ansys, etc) is possible 11 | and iterative processes (optimization, design sensitivity) are possible. 12 | For a thorough explanation please check the documentation and the tutorials. 13 | 14 | Contents: 15 | 16 | .. toctree:: 17 | :numbered: 18 | :titlesonly: 19 | :maxdepth: 2 20 | 21 | main_module 22 | xfoil_module 23 | aero_module 24 | airfoil_module 25 | tutorial 26 | 27 | To Do 28 | ====== 29 | 30 | - Include asymmetric wing 31 | - Create airfoil and wing classes 32 | 33 | Recommended Collaborations 34 | ========================== 35 | 36 | Please use and adapt this library to your needs. There are several 37 | functionalities I wished to implement, but did not have the time. Hence 38 | I am *strongly* recommending the following collaborations: 39 | 40 | - Airfoil generator with a GUI 41 | - Atmospheric module (use the library already available in aero_module) 42 | - Extend aero_module for wings with non-constant cross sections 43 | 44 | Indices and tables 45 | ================== 46 | 47 | * :ref:`genindex` 48 | * :ref:`modindex` 49 | * :ref:`search` 50 | 51 | Examples 52 | ================== 53 | 54 | A simple example demonstrating how to use AeroPy to calculate lift, drag and 55 | moment coefficients for a NACA0012 airfoil at angle of attack of 12 degrees. 56 | 57 | .. code-block:: python 58 | 59 | from AeroPy import find_coefficients 60 | find_coefficients(airfoil='naca0012'alpha=12.) 61 | >>> {'CM': 0.0134, 'CL': 1.2453, 'Top_Xtr': 0.0194, 'CD': 0.01934, 'CDp': 0.01379, 'alpha': 12.0, 'Bot_Xtr': 1.0} 62 | 63 | Another example showing how to use AeroPy to calculate pressure coefficients for a 64 | NACA0012 in viscous flow at Reynolds = 10000000 and angle of attack of 12 degrees 65 | 66 | .. code-block:: python 67 | 68 | from AeroPy import find_pressure_coefficients 69 | find_pressure_coefficients(airfoil='naca0012', Reynolds = 1e6, alpha=12.,NACA=True) 70 | >>> 'y': [0.00126, ..., -0.00126], 'x': [1.0, ..., 1.0], 'Cp': [0.41501, ..., 0.41501]} -------------------------------------------------------------------------------- /test_inflections.py: -------------------------------------------------------------------------------- 1 | import numpy as np 2 | import matplotlib.pyplot as plt 3 | 4 | import xfoil_module as xf 5 | from CST_module import * 6 | from aero_module import Reynolds 7 | from airfoil_module import CST, create_x 8 | 9 | Au = [0.23993240191629417, 0.34468227138908186, 0.18125405377549103, 10 | 0.35371349126072665, 0.2440815012119143, 0.25724974995738387] 11 | Al = [0.18889012559339036, -0.24686758992053115, 0.077569769493868401, 12 | -0.547827192265256, -0.0047342206759065641, -0.23994805474814629] 13 | c_avian = .36 #m 14 | deltaz = 0.0093943568219451313*c_avian 15 | 16 | airfoil = 'avian' 17 | x = create_x(c_avian, distribution = 'linear') 18 | y = CST(x, c_avian, [deltaz/2., deltaz/2.], Au = Au, Al= Al) 19 | # Create file for Xfoil to read coordinates 20 | xf.create_input(x, y['u'], y['l'], airfoil, different_x_upper_lower = False) 21 | 22 | Data = xf.find_coefficients(airfoil, 2., Reynolds=Reynolds(10000, 30, c_avian), iteration=100, NACA=False) 23 | print Data 24 | 25 | 26 | psi_u_inflection, psi_l_inflection = find_inflection_points(Au, Al) 27 | print 'upper: ', psi_u_inflection 28 | print 'lower: ', psi_l_inflection 29 | psi = np.linspace(0.001,0.999,100) 30 | xi = CST(psi, 1, [deltaz/2., deltaz/2.], Au, Al) 31 | plt.plot(psi, xi['u'], 'b', label = 'Upper outer mold line') 32 | plt.plot(psi, xi['l'],'b--', label = 'Lower outer mold line') 33 | 34 | xi_u_inflection = CST(psi_u_inflection, 1, [deltaz/2., deltaz/2.], Au, Al) 35 | plt.scatter(psi_u_inflection, xi_u_inflection['u']) 36 | 37 | xi_l_inflection = CST(psi_l_inflection, 1, [deltaz/2., deltaz/2.], Au, Al) 38 | plt.scatter(psi_l_inflection, xi_l_inflection['l']) 39 | plt.xlabel('$\psi$', fontsize = 40) 40 | plt.ylabel(r'$\xi$', fontsize = 40) 41 | plt.grid() 42 | # plt.show() 43 | 44 | # plt.figure() 45 | # plt.plot(psi,dxi_u(psi,Au, deltaz), 'g', label = r'$d\xi_u$') 46 | # plt.plot(psi,dxi_l(psi,Al,deltaz), 'g--', label = r'$d\xi_l$') 47 | 48 | plt.plot(psi,ddxi_u(psi,Au), 'r', label = 'Upper second derivative') 49 | plt.plot(psi,ddxi_l(psi,Al), 'r--', label = 'Lower second derivative') 50 | 51 | # Plot camber 52 | camber = calculate_camber(psi, Au, Al, deltaz/c_avian) 53 | plt.plot(psi,camber, 'k', label = 'camber') 54 | psi_camber, xi_camber = calculate_max_camber(Au, Al, deltaz/c_avian) 55 | print psi_camber, xi_camber, type(psi_camber), type(xi_camber) 56 | print 'average camber: ', calculate_average_camber( Au, Al, deltaz/c_avian) 57 | plt.scatter(psi_camber, xi_camber, label = 'Inflection points') 58 | plt.ylim([-0.1,0.1]) 59 | plt.legend(loc='best') 60 | plt.show() 61 | -------------------------------------------------------------------------------- /docs/_build/html/pyxfoil_doc.html: -------------------------------------------------------------------------------- 1 | 3 | 4 | 5 | 6 | 7 | 8 | 9 | 3. pyxfoil_doc — pyXFOIL 0.0.1 documentation 10 | 11 | 12 | 13 | 14 | 23 | 24 | 25 | 26 | 27 | 28 | 29 | 30 | 31 | 32 | 33 | 34 | 35 | 36 |
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The functions herein defined are purposely made for generating NACA airfoils, flapped airfoils and CST airfoils.

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4.1. Core Function

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4.2. Auxiliary Functions

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If \(\theta_0\) is an arbitrary span-wise location:

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Each equation has \(N\) unknowns (\(A_n\)), so if there are N \(\theta_o\), we have NxN system, which in Einstein notation can be written as:

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121 | 122 | 123 | 124 | 125 | 126 | -------------------------------------------------------------------------------- /docs/_build/html/searchindex.js: -------------------------------------------------------------------------------- 1 | Search.setIndex({envversion:46,filenames:["aero_module","airfoil_module","index","main_module","tutorial","xfoil_module"],objects:{"":{AeroPy:[3,0,0,"-"],aero_module:[0,0,0,"-"],xfoil_module:[5,0,0,"-"]},AeroPy:{find_3D_coefficients:[3,1,1,""]},aero_module:{LLT_calculator:[0,1,1,""],Reynolds:[0,1,1,""],air_properties:[0,1,1,""],calculate_moment_coefficient:[0,1,1,""],pressure_shell_2D:[0,1,1,""]},xfoil_module:{M_crit:[5,1,1,""],alfa_for_file:[5,1,1,""],call:[5,1,1,""],create_input:[5,1,1,""],create_x:[5,1,1,""],file_name:[5,1,1,""],find_alpha_L_0:[5,1,1,""],find_coefficients:[5,1,1,""],find_pressure_coefficients:[5,1,1,""],output_reader:[5,1,1,""],prepare_xfoil:[5,1,1,""]}},objnames:{"0":["py","module","Python module"],"1":["py","function","Python 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Aerodynamic Module Documentation","4. Airfoil Module Documentation","Welcome to AeroPy’s, an easy to use aerodynamic tool","1. AeroPy Documentation","5. Tutorial","2. Xfoil Module Documentation"],titleterms:{"function":[1,5],aerodynam:[0,2],aeropi:[2,3],airfoil:1,auxiliari:[1,5],code:[0,3],collabor:2,core:[1,5],document:[0,1,3,5],easi:2,exampl:2,indic:2,lift:0,line:0,modul:[0,1,5],recommend:2,tabl:2,theori:0,tool:2,tutori:4,util:[1,5],welcom:2,xfoil:5}}) -------------------------------------------------------------------------------- /docs/images/logo.svg: -------------------------------------------------------------------------------- 1 | 2 | 3 | 4 | 21 | 23 | 27 | 31 | 35 | 36 | 46 | 56 | 59 | 65 | 66 | 67 | 85 | 87 | 88 | 90 | image/svg+xml 91 | 93 | 94 | 95 | 96 | 97 | 101 | 107 | 117 | 118 | 119 | -------------------------------------------------------------------------------- /docs/make.bat: -------------------------------------------------------------------------------- 1 | @ECHO OFF 2 | 3 | REM Command file for Sphinx documentation 4 | 5 | if "%SPHINXBUILD%" == "" ( 6 | set SPHINXBUILD=sphinx-build 7 | ) 8 | set BUILDDIR=_build 9 | set ALLSPHINXOPTS=-d %BUILDDIR%/doctrees %SPHINXOPTS% . 10 | set I18NSPHINXOPTS=%SPHINXOPTS% . 11 | if NOT "%PAPER%" == "" ( 12 | set ALLSPHINXOPTS=-D latex_paper_size=%PAPER% %ALLSPHINXOPTS% 13 | set I18NSPHINXOPTS=-D latex_paper_size=%PAPER% %I18NSPHINXOPTS% 14 | ) 15 | 16 | if "%1" == "" goto help 17 | 18 | if "%1" == "help" ( 19 | :help 20 | echo.Please use `make ^` where ^ is one of 21 | echo. html to make standalone HTML files 22 | echo. dirhtml to make HTML files named index.html in directories 23 | echo. singlehtml to make a single large HTML file 24 | echo. pickle to make pickle files 25 | echo. json to make JSON files 26 | echo. htmlhelp to make HTML files and a HTML help project 27 | echo. qthelp to make HTML files and a qthelp project 28 | echo. devhelp to make HTML files and a Devhelp project 29 | echo. epub to make an epub 30 | echo. latex to make LaTeX files, you can set PAPER=a4 or PAPER=letter 31 | echo. text to make text files 32 | echo. man to make manual pages 33 | echo. texinfo to make Texinfo files 34 | echo. gettext to make PO message catalogs 35 | echo. changes to make an overview over all changed/added/deprecated items 36 | echo. xml to make Docutils-native XML files 37 | echo. pseudoxml to make pseudoxml-XML files for display purposes 38 | echo. linkcheck to check all external links for integrity 39 | echo. doctest to run all doctests embedded in the documentation if enabled 40 | echo. coverage to run coverage check of the documentation if enabled 41 | goto end 42 | ) 43 | 44 | if "%1" == "clean" ( 45 | for /d %%i in (%BUILDDIR%\*) do rmdir /q /s %%i 46 | del /q /s %BUILDDIR%\* 47 | goto end 48 | ) 49 | 50 | 51 | REM Check if sphinx-build is available and fallback to Python version if any 52 | %SPHINXBUILD% 2> nul 53 | if errorlevel 9009 goto sphinx_python 54 | goto sphinx_ok 55 | 56 | :sphinx_python 57 | 58 | set SPHINXBUILD=python -m sphinx.__init__ 59 | %SPHINXBUILD% 2> nul 60 | if errorlevel 9009 ( 61 | echo. 62 | echo.The 'sphinx-build' command was not found. 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The XML files are in $(BUILDDIR)/xml." 188 | 189 | pseudoxml: 190 | $(SPHINXBUILD) -b pseudoxml $(ALLSPHINXOPTS) $(BUILDDIR)/pseudoxml 191 | @echo 192 | @echo "Build finished. The pseudo-XML files are in $(BUILDDIR)/pseudoxml." 193 | -------------------------------------------------------------------------------- /docs/_build/html/genindex.html: -------------------------------------------------------------------------------- 1 | 2 | 4 | 5 | 6 | 7 | 8 | 9 | 10 | Index — AeroPy 0.0.2 documentation 11 | 12 | 13 | 14 | 15 | 24 | 25 | 26 | 27 | 28 | 29 | 30 | 31 | 32 | 33 | 34 | 35 | 36 |
37 |
38 |
39 |
40 | 41 | 42 |

Index

43 | 44 |
45 | A 46 | | C 47 | | F 48 | | L 49 | | M 50 | | O 51 | | P 52 | | R 53 | | X 54 | 55 |
56 |

A

57 | 58 | 68 | 78 |
59 | 60 |
aero_module (module) 61 |
62 | 63 | 64 |
AeroPy (module) 65 |
66 | 67 |
69 | 70 |
air_properties() (in module aero_module) 71 |
72 | 73 | 74 |
alfa_for_file() (in module xfoil_module) 75 |
76 | 77 |
79 | 80 |

C

81 | 82 | 92 | 102 |
83 | 84 |
calculate_moment_coefficient() (in module aero_module) 85 |
86 | 87 | 88 |
call() (in module xfoil_module) 89 |
90 | 91 |
93 | 94 |
create_input() (in module xfoil_module) 95 |
96 | 97 | 98 |
create_x() (in module xfoil_module) 99 |
100 | 101 |
103 | 104 |

F

105 | 106 | 120 | 130 |
107 | 108 |
file_name() (in module xfoil_module) 109 |
110 | 111 | 112 |
find_3D_coefficients() (in module AeroPy) 113 |
114 | 115 | 116 |
find_alpha_L_0() (in module xfoil_module) 117 |
118 | 119 |
121 | 122 |
find_coefficients() (in module xfoil_module) 123 |
124 | 125 | 126 |
find_pressure_coefficients() (in module xfoil_module) 127 |
128 | 129 |
131 | 132 |

L

133 | 134 | 140 |
135 | 136 |
LLT_calculator() (in module aero_module) 137 |
138 | 139 |
141 | 142 |

M

143 | 144 | 150 |
145 | 146 |
M_crit() (in module xfoil_module) 147 |
148 | 149 |
151 | 152 |

O

153 | 154 | 160 |
155 | 156 |
output_reader() (in module xfoil_module) 157 |
158 | 159 |
161 | 162 |

P

163 | 164 | 170 | 176 |
165 | 166 |
prepare_xfoil() (in module xfoil_module) 167 |
168 | 169 |
171 | 172 |
pressure_shell_2D() (in module aero_module) 173 |
174 | 175 |
177 | 178 |

R

179 | 180 | 186 |
181 | 182 |
Reynolds() (in module aero_module) 183 |
184 | 185 |
187 | 188 |

X

189 | 190 | 196 |
191 | 192 |
xfoil_module (module) 193 |
194 | 195 |
197 | 198 | 199 | 200 |
201 |
202 |
203 | 232 |
233 |
234 |
235 | ©2015, Pedro Leal. 236 | 237 | | 238 | Powered by Sphinx 1.3.1 239 | & Alabaster 0.7.6 240 | 241 |
242 | 243 | 244 | 245 | Fork me on GitHub 246 | 247 | 248 | 249 | 250 | 251 | -------------------------------------------------------------------------------- /docs/_build/html/main_module.html: -------------------------------------------------------------------------------- 1 | 3 | 4 | 5 | 6 | 7 | 8 | 9 | 1. AeroPy Documentation — AeroPy 0.0.2 documentation 10 | 11 | 12 | 13 | 14 | 23 | 24 | 25 | 26 | 27 | 28 | 29 | 30 | 31 | 32 | 33 | 34 | 35 | 36 | 37 |
38 |
39 |
40 |
41 | 42 |
43 |

1. AeroPy Documentation

44 |

This project was elaborated because of the need of optimizing an airfoil 45 | according to its aerodynamic and structural performance (conference paper). 46 | Contrary to available options such as XFLR5, AeroPy aims to be an open source 47 | Python code. It is a quick and easy way to find the aerodynamic pressure and the 48 | drag and lift coefficients through the use of MIT’s XFOIL embedded in Python. 49 | Contrary to the other libraries, AeroPy does not have a GUI and is intended 50 | to be used in Python codes for optimizations or any other process that requires 51 | several aerodynamic analysis.

52 |

AeroPy is separated in three modules: (it is programmed in such a way that a new 53 | module can be easily inserted)

54 |
    55 |

  • xfoil: contains all the functions relating to XFOIL.

    56 |
    • 57 |

  • aero: contains all functions related to aerodynamics, but not related to XFOIL.

    58 |
    • 59 |
  • 60 |
    AeroPy: imports all functions and acts as the intersection of all different
    61 |

    modules

    62 |
    63 |
    64 |
    • 65 |
66 |
67 |

1.1. Code

68 |

Created on Sun Aug 16 20:59:22 2015

69 |

@author: Pedro

70 |
71 |
72 | AeroPy.find_3D_coefficients(airfoil, alpha, Reynolds=0, iteration=10, NACA=True, N=10, span=10.0, taper=1.0, chord_root=1, alpha_root=1.0, velocity=1.0)[source]
73 |

Calculate the 3D distribution using the Lifting Line Theory.

74 | 75 | 76 | 77 | 78 | 100 | 101 | 102 |
Parameters:
    79 |
  • airfoil – if NACA is false, airfoil is the name of the plain 80 | filewhere the airfoil geometry is stored (variable airfoil). 81 | If NACA is True, airfoil is the naca series of the airfoil 82 | (i.e.: naca2244). By default NACA is False.
    • 83 |
  • Reynolds – Reynolds number in case the simulation is for a 84 | viscous flow. In case not informed, the code will assume 85 | inviscid. (Use the aero_module function to calculate reynolds)
    • 86 |
  • alpha – list/array/float/int of angles of attack.
    • 87 |
  • iteration – changes how many times XFOIL will try to make the 88 | results converge. Specialy important for viscous flows
    • 89 |
  • NACA – Boolean variable that defines if the code imports an 90 | airfoil from a file or generates a NACA airfoil.
    • 91 |
  • N – number of cross sections on the wing
    • 92 |
  • span – span in meters
    • 93 |
  • taper – unidimendional taper (This options is still not 100% 94 | operational)
    • 95 |
  • chord_root – value of the chord at the the root
    • 96 |
  • alpha_root – angle of attack of the chord at the root (degrees)
    • 97 |
  • velocity – velocity in m/s
    • 98 |
99 |
103 |
104 | 105 |
106 |
107 | 108 | 109 |
110 |
111 |
112 | 155 |
156 |
157 |
158 | ©2015, Pedro Leal. 159 | 160 | | 161 | Powered by Sphinx 1.3.1 162 | & Alabaster 0.7.6 163 | 164 | | 165 | Page source 167 |
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Rp156 314 | ag3 315 | (g7 316 | S'f>\xe3(\x06Z\xd3?' 317 | p157 318 | tp158 319 | Rp159 320 | ag3 321 | (g7 322 | S'\xd0P\x9a\x1f\t\xbb\xcb?' 323 | p160 324 | tp161 325 | Rp162 326 | ag3 327 | (g7 328 | S'\xe2\xcf\x8e\x9b\xe9\x19\xdb?' 329 | p163 330 | tp164 331 | Rp165 332 | ag3 333 | (g7 334 | S"\xe0'\x1f\xdd\xc6o\xba?" 335 | p166 336 | tp167 337 | Rp168 338 | ag3 339 | (g7 340 | S'\n$\xc2\xe0\xe3\xd7\xd1?' 341 | p169 342 | tp170 343 | Rp171 344 | ag3 345 | (g7 346 | S'\xaatI54\xcf\xd6?' 347 | p172 348 | tp173 349 | Rp174 350 | ag3 351 | (g7 352 | S'\xc4\xeb\xac\xf0\xc7P\xb7?' 353 | p175 354 | tp176 355 | Rp177 356 | aasS'Al' 357 | p178 358 | (lp179 359 | (lp180 360 | g3 361 | (g7 362 | S'\x18\x17\x19\xcc/\x1c\xa8?' 363 | p181 364 | tp182 365 | Rp183 366 | ag3 367 | (g7 368 | S'Q\x93\x80{E\x97\xd7\xbf' 369 | p184 370 | tp185 371 | Rp186 372 | aa(lp187 373 | g3 374 | (g7 375 | S'\xc9\x0c]f\x12|\xc3?' 376 | p188 377 | tp189 378 | Rp190 379 | ag3 380 | (g7 381 | S'\xc2\xe6[\x114\xb3\xdb\xbf' 382 | p191 383 | tp192 384 | Rp193 385 | ag3 386 | (g7 387 | S'\xc6@\x06\xc4\xf3\xf5\xa4\xbf' 388 | p194 389 | tp195 390 | Rp196 391 | aa(lp197 392 | g3 393 | (g7 394 | S'C_m]\x84\xe7\xc4?' 395 | p198 396 | tp199 397 | Rp200 398 | ag3 399 | (g7 400 | S'\xea\xc3\x91\xf0\xdf\xce\xd3\xbf' 401 | p201 402 | tp202 403 | Rp203 404 | ag3 405 | (g7 406 | S'\xa9\x0f\xe9\xa2K\xbc\xc3\xbf' 407 | p204 408 | tp205 409 | Rp206 410 | ag3 411 | (g7 412 | S'\x89!\x94\x06h\x89\xcd\xbf' 413 | p207 414 | tp208 415 | Rp209 416 | aa(lp210 417 | g3 418 | (g7 419 | S'\xb3W\xc3y\x9e\x82\xc6?' 420 | p211 421 | tp212 422 | Rp213 423 | ag3 424 | (g7 425 | S'\xe1Ml\xcaX\x86\xd0\xbf' 426 | p214 427 | tp215 428 | Rp216 429 | ag3 430 | (g7 431 | S'\x86\xc3\xf3\xd4S\x7f\xa2\xbf' 432 | p217 433 | tp218 434 | Rp219 435 | ag3 436 | (g7 437 | S'%\xf7j\x15CY\xdc\xbf' 438 | p220 439 | tp221 440 | Rp222 441 | ag3 442 | (g7 443 | S'1U3{\xd2q\x95?' 444 | p223 445 | tp224 446 | Rp225 447 | aa(lp226 448 | g3 449 | (g7 450 | S'=\x12\xde\xd8<7\xc8?' 451 | p227 452 | tp228 453 | Rp229 454 | ag3 455 | (g7 456 | S'\x97\x89\x91\xd6Z\xc6\xcf\xbf' 457 | p230 458 | tp231 459 | Rp232 460 | ag3 461 | (g7 462 | S'$\xb1c\x1c\xb9\xb4\xb2?' 463 | p233 464 | tp234 465 | Rp235 466 | ag3 467 | (g7 468 | S'*\x98\xe6!\xd9<\xe1\xbf' 469 | p236 470 | tp237 471 | Rp238 472 | ag3 473 | (g7 474 | S"N\x88\x84\xa9']\x84\xbf" 475 | p239 476 | tp240 477 | Rp241 478 | ag3 479 | (g7 480 | S'\xa3\xd1\xd4BV\x9a\xce\xbf' 481 | p242 482 | tp243 483 | Rp244 484 | aa(lp245 485 | g3 486 | (g7 487 | S'JU`\x8bo\x83\xc9?' 488 | p246 489 | tp247 490 | Rp248 491 | ag3 492 | (g7 493 | S'\x7f7\xe1f\xb9y\xcf\xbf' 494 | p249 495 | tp250 496 | Rp251 497 | ag3 498 | (g7 499 | S'\x05\x1fX~\xb1\x95\xc7?' 500 | p252 501 | tp253 502 | Rp254 503 | ag3 504 | (g7 505 | S'\xf7\x06\x93\xbe@!\xe3\xbf' 506 | p255 507 | tp256 508 | Rp257 509 | ag3 510 | (g7 511 | S'\x9eLjw:\xf8\xa9?' 512 | p258 513 | tp259 514 | Rp260 515 | ag3 516 | (g7 517 | S'\x02\x9b\rp\x18\x9d\xd6\xbf' 518 | p261 519 | tp262 520 | Rp263 521 | ag3 522 | (g7 523 | S'\xfb\xe9"3\x14\x87\x9a\xbf' 524 | p264 525 | tp265 526 | Rp266 527 | aa(lp267 528 | g3 529 | (g7 530 | S':\x9d\x8d\xdf0]\xca?' 531 | p268 532 | tp269 533 | Rp270 534 | ag3 535 | (g7 536 | S'\x9b(\xc1\x0b-k\xcd\xbf' 537 | p271 538 | tp272 539 | Rp273 540 | ag3 541 | (g7 542 | S'J 3 | 4 | 5 | 6 | 7 | 8 | 9 | AeroPy — AeroPy 0.0.2 documentation 10 | 11 | 12 | 13 | 14 | 23 | 24 | 25 | 26 | 27 | 28 | 29 | 30 | 31 | 32 | 33 | 34 | 35 | 36 |
37 |
38 |
39 |
40 | 41 |

Source code for AeroPy

 42 | # -*- coding: utf-8 -*-
 43 | """
 44 | Created on Sun Aug 16 20:59:22 2015
 45 | 
 46 | @author: Pedro
 47 | """
 48 | from aero_module import *
 49 | from xfoil_module import *
 50 | 
 51 | 
[docs]def find_3D_coefficients(airfoil, alpha, Reynolds=0, iteration=10, NACA=True,
 52 |                          N=10, span=10., taper=1., chord_root=1, alpha_root=1.,
 53 |                          velocity=1.):
 54 |     """ Calculate the 3D distribution using the Lifting Line Theory.
 55 |     
 56 |     :param airfoil: if NACA is false, airfoil is the name of the plain
 57 |            filewhere the airfoil geometry is stored (variable airfoil).
 58 |            If NACA is True, airfoil is the naca series of the airfoil
 59 |            (i.e.: naca2244). By default NACA is False.
 60 | 
 61 |     :param Reynolds: Reynolds number in case the simulation is for a
 62 |           viscous flow. In case not informed, the code will assume
 63 |           inviscid. (Use the aero_module function to calculate reynolds)
 64 |           
 65 |     :param alpha: list/array/float/int of angles of attack.
 66 | 
 67 |     :param iteration: changes how many times XFOIL will try to make the
 68 |           results converge. Specialy important for viscous flows
 69 | 
 70 |     :param NACA: Boolean variable that defines if the code imports an
 71 |           airfoil from a file or generates a NACA airfoil.
 72 |     
 73 |     :param N: number of cross sections on the wing
 74 |     
 75 |     :param span: span in meters
 76 |     
 77 |     :param taper: unidimendional taper (This options is still not 100%
 78 |             operational)
 79 |     
 80 |     :param chord_root: value of the chord at the the root
 81 |     
 82 |     :param alpha_root: angle of attack of the chord at the root (degrees)
 83 | 
 84 |     :param velocity: velocity in m/s
 85 | 
 86 | """
 87 |     coefficients = find_coefficients(airfoil, alpha, Reynolds, iteration,
 88 |                                      NACA)
 89 |     alpha_L_0_root = find_alpha_L_0(airfoil, Reynolds, iteration, NACA)
 90 |     return LLT_calculator(alpha_L_0_root, coefficients['CD'], N, span, taper, chord_root,
 91 |                           alpha_root, velocity)
 92 | 
 93 | 

 94 | if __name__ == '__main__':
 95 |     print find_3D_coefficients(airfoil='naca0012', alpha=1.)
 96 |
97 | 98 |
99 |
100 |
101 | 129 |
130 |
131 |
132 | ©2015, Pedro Leal. 133 | 134 | | 135 | Powered by Sphinx 1.3.1 136 | & Alabaster 0.7.6 137 | 138 |
139 | 140 | 141 | 142 | Fork me on GitHub 143 | 144 | 145 | 146 | 147 | 148 | -------------------------------------------------------------------------------- /docs/_build/html/index.html: -------------------------------------------------------------------------------- 1 | 3 | 4 | 5 | 6 | 7 | 8 | 9 | Welcome to AeroPy’s, an easy to use aerodynamic tool — AeroPy 0.0.2 documentation 10 | 11 | 12 | 13 | 14 | 23 | 24 | 25 | 26 | 27 | 28 | 29 | 30 | 31 | 32 | 33 | 34 | 35 | 36 |
37 |
38 |
39 |
40 | 41 |
42 |

Welcome to AeroPy’s, an easy to use aerodynamic tool

43 |

AeroPy is an library for calculating aerodynamic properties. The main feature of 44 | this library is the Python interface with XFOIL. The main objective of this library is to be able 45 | to use XFOIL via Python iteratively in a total of 4 lines total (one line for most uses). 46 | Through this interface coupling with other softwares (Abaqus, Ansys, etc) is possible 47 | and iterative processes (optimization, design sensitivity) are possible. 48 | For a thorough explanation please check the documentation and the tutorials.

49 |

Contents:

50 |
51 | 66 |
67 |
68 |
69 |

To Do

70 |
    71 |
  • Include asymmetric wing
    • 72 |
  • Create airfoil and wing classes
    • 73 |
74 |
75 | 86 |
87 |

Indices and tables

88 | 93 |
94 |
95 |

Examples

96 |

A simple example demonstrating how to use AeroPy to calculate lift, drag and 97 | moment coefficients for a NACA0012 airfoil at angle of attack of 12 degrees.

98 | 
from AeroPy import find_coefficients
 99 | find_coefficients(airfoil='naca0012'alpha=12.)
100 | >>> {'CM': 0.0134, 'CL': 1.2453, 'Top_Xtr': 0.0194, 'CD': 0.01934, 'CDp': 0.01379, 'alpha': 12.0, 'Bot_Xtr': 1.0}
101 |
102 |
103 |

Another example showing how to use AeroPy to calculate pressure coefficients for a 104 | NACA0012 in viscous flow at Reynolds = 10000000 and angle of attack of 12 degrees

105 | 
from AeroPy import find_pressure_coefficients
106 | find_pressure_coefficients(airfoil='naca0012', Reynolds = 1e6, alpha=12.,NACA=True)
107 | >>> 'y': [0.00126, ..., -0.00126], 'x': [1.0, ..., 1.0], 'Cp': [0.41501, ..., 0.41501]}
108 |
109 |
110 |
111 | 112 | 113 |
114 |
115 |
116 | 159 |
160 |
161 |
162 | ©2015, Pedro Leal. 163 | 164 | | 165 | Powered by Sphinx 1.3.1 166 | & Alabaster 0.7.6 167 | 168 | | 169 | Page source 171 |
172 | 173 | 174 | 175 | Fork me on GitHub 176 | 177 | 178 | 179 | 180 | 181 | -------------------------------------------------------------------------------- /docs/_build/html/aero_module.html: -------------------------------------------------------------------------------- 1 | 3 | 4 | 5 | 6 | 7 | 8 | 9 | 3. Aerodynamic Module Documentation — AeroPy 0.0.2 documentation 10 | 11 | 12 | 13 | 14 | 23 | 24 | 25 | 26 | 27 | 28 | 29 | 30 | 31 | 32 | 33 | 34 | 35 | 36 | 37 |
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39 |
40 |
41 | 42 |
43 |

3. Aerodynamic Module Documentation

44 |
45 |

3.1. Lifting Line Theory

46 |

If \(\theta_0\) is an arbitrary span-wise location:

47 |
48 | (1)\[\alpha (\theta_o)=\frac{2b}{\pi c(\theta_o)} \sum_1^N A_n sin(n \theta_o) + \alpha_{L=0}(\theta_o) + \sum_1^N n A_n \frac{sin(n\theta_o)}{sin(\theta_o)}\]
49 |

Each equation has \(N\) unknowns (\(A_n\)), so if there are N \(\theta_o\), we have NxN system, which in Einstein notation can be written as:

50 |
51 | (2)\[C_{ij}A_{i}=D_{i}\]
52 |

where, \(i=0,...,N\), \(j=0,...,N\) and :

53 |
54 | (3)\[C_{ij}= \left( \frac{2b}{\pi c(j)} + \frac{n}{sin \theta(i)} \right) sin(n \theta(i))\]
55 |
56 | (4)\[A_i=A(i)\]
57 |
58 | (5)\[D_i=\alpha(i)-\alpha_{L=0}(i)\]
59 |

where \(n=1,3,5,...,N-1\). Since we are considering a symmetric wing, all of the even terms would cancel each other

60 |
61 | _images/elliptical_LLT.png 62 |
63 |
64 |
65 |

3.2. The code

66 |

Current funcionatilities: 67 | - Lifting line theory 68 | - generate field pressures for Abaqus or other softwares 69 | - air properties calculator 70 | - Reynolds calculator 71 | Created on Mon Jul 20 17:26:19 2015

72 |

@author: Pedro Leal

73 |
74 |
75 | aero_module.LLT_calculator(alpha_L_0_root, c_D_xfoil, N=10, b=10.0, taper=1.0, chord_root=1, alpha_root=0.0, V=1.0)[source]
76 |

Calculate the coefficients for a Wing. 77 | TODO : - Include elliptical wing

78 |
79 |
    80 |
  • When alpha_L_0_root = zero, nan!
    • 81 |
  • Include non rectangular wings
    • 82 |
  • something else?
    • 83 |
84 |
85 |
86 | 87 |
88 |
89 | aero_module.Reynolds(height, V, c)[source]
90 |

Simple function to calculate Reynolds for a given height.

91 |

@author: Pedro Leal 92 | Created in Jul 17 2015

93 |
94 | 95 |
96 |
97 | aero_module.air_properties(height, unit='feet')[source]
98 |

Function to calculate air properties for a given height (m or ft).

99 |
100 |
Sources:
101 |
105 |
106 |
107 |

Created on Thu May 15 14:59:43 2014 108 | @author: Pedro Leal

109 |
110 | 111 |
112 |
113 | aero_module.calculate_moment_coefficient(x, y, Cp, alpha, c=1.0, x_ref=0.0, y_ref=0.0)[source]
114 |

Calculate the moment coeffcient. Inputs are x and y coordinates, and 115 | pressure coefficients (Cp). Inputs can be in a list in xfoil format 116 | (counterclockwise starting from the trailing edge, in case necessary, 117 | check create_input function from xfoil_module) or dictionaries with 118 | ‘upper’ and ‘lower’ keys.

119 |
120 | 121 |
122 |
123 | aero_module.pressure_shell_2D(Data, chord, thickness, half_span, height, Velocity, N, txt=False)[source]
124 |

Calculate pressure field for a 2D Shell.

125 |
126 | 127 |
128 |
129 | 130 | 131 |
132 |
133 |
134 | 178 |
179 |
180 |
181 | ©2015, Pedro Leal. 182 | 183 | | 184 | Powered by Sphinx 1.3.1 185 | & Alabaster 0.7.6 186 | 187 | | 188 | Page source 190 |
191 | 192 | 193 | 194 | Fork me on GitHub 195 | 196 | 197 | 198 | 199 | 200 | -------------------------------------------------------------------------------- /docs/conf.py: -------------------------------------------------------------------------------- 1 | # -*- coding: utf-8 -*- 2 | # 3 | # pyXFOIL documentation build configuration file, created by 4 | # sphinx-quickstart on Tue Aug 11 23:35:51 2015. 5 | # 6 | # This file is execfile()d with the current directory set to its 7 | # containing dir. 8 | # 9 | # Note that not all possible configuration values are present in this 10 | # autogenerated file. 11 | # 12 | # All configuration values have a default; values that are commented out 13 | # serve to show the default. 14 | 15 | import sys 16 | import os 17 | import shlex 18 | import alabaster 19 | 20 | from mock import Mock # To include C dependent libs in ReadtheDocs 21 | 22 | # If extensions (or modules to document with autodoc) are in another directory, 23 | # add these directories to sys.path here. If the directory is relative to the 24 | # documentation root, use os.path.abspath to make it absolute, like shown here. 25 | #sys.path.insert(0, os.path.abspath('.')) 26 | sys.path.insert(0, os.path.abspath('..')) 27 | 28 | # -- General configuration ------------------------------------------------ 29 | 30 | # If your documentation needs a minimal Sphinx version, state it here. 31 | #needs_sphinx = '1.0' 32 | 33 | # Add any Sphinx extension module names here, as strings. They can be 34 | # extensions coming with Sphinx (named 'sphinx.ext.*') or your custom 35 | # ones. 36 | extensions = [ 37 | 'sphinx.ext.autodoc', 38 | 'sphinx.ext.intersphinx', 39 | 'sphinx.ext.todo', 40 | 'sphinx.ext.mathjax', 41 | 'sphinx.ext.viewcode', 42 | 'alabaster' 43 | ] 44 | 45 | # Add any paths that contain templates here, relative to this directory. 46 | templates_path = ['_templates'] 47 | 48 | # The suffix(es) of source filenames. 49 | # You can specify multiple suffix as a list of string: 50 | # source_suffix = ['.rst', '.md'] 51 | source_suffix = '.rst' 52 | 53 | # The encoding of source files. 54 | #source_encoding = 'utf-8-sig' 55 | 56 | # The master toctree document. 57 | master_doc = 'index' 58 | 59 | # General information about the project. 60 | project = u'AeroPy' 61 | copyright = u'2015, Pedro Leal' 62 | author = u'Pedro Leal' 63 | 64 | # The version info for the project you're documenting, acts as replacement for 65 | # |version| and |release|, also used in various other places throughout the 66 | # built documents. 67 | # 68 | # The short X.Y version. 69 | version = '0.0.2' 70 | # The full version, including alpha/beta/rc tags. 71 | release = '0.0.2' 72 | 73 | # The language for content autogenerated by Sphinx. Refer to documentation 74 | # for a list of supported languages. 75 | # 76 | # This is also used if you do content translation via gettext catalogs. 77 | # Usually you set "language" from the command line for these cases. 78 | language = None 79 | 80 | # There are two options for replacing |today|: either, you set today to some 81 | # non-false value, then it is used: 82 | #today = '' 83 | # Else, today_fmt is used as the format for a strftime call. 84 | #today_fmt = '%B %d, %Y' 85 | 86 | # List of patterns, relative to source directory, that match files and 87 | # directories to ignore when looking for source files. 88 | exclude_patterns = ['_build'] 89 | 90 | # The reST default role (used for this markup: `text`) to use for all 91 | # documents. 92 | #default_role = None 93 | 94 | # If true, '()' will be appended to :func: etc. cross-reference text. 95 | #add_function_parentheses = True 96 | 97 | # If true, the current module name will be prepended to all description 98 | # unit titles (such as .. function::). 99 | #add_module_names = True 100 | 101 | # If true, sectionauthor and moduleauthor directives will be shown in the 102 | # output. They are ignored by default. 103 | #show_authors = False 104 | 105 | # The name of the Pygments (syntax highlighting) style to use. 106 | pygments_style = 'sphinx' 107 | 108 | # A list of ignored prefixes for module index sorting. 109 | #modindex_common_prefix = [] 110 | 111 | # If true, keep warnings as "system message" paragraphs in the built documents. 112 | #keep_warnings = False 113 | 114 | # If true, `todo` and `todoList` produce output, else they produce nothing. 115 | todo_include_todos = True 116 | 117 | 118 | # -- Options for HTML output ---------------------------------------------- 119 | 120 | # The theme to use for HTML and HTML Help pages. See the documentation for 121 | # a list of builtin themes. 122 | html_theme = 'alabaster' 123 | 124 | # Theme options are theme-specific and customize the look and feel of a theme 125 | # further. For a list of options available for each theme, see the 126 | # documentation. 127 | html_theme_options = {'logo': 'logo.png', 128 | 'description': 'An easy to use aerodynamic tool', 129 | 'github_user': 'leal26', 130 | 'github_repo': 'AeroPy', 131 | 'logo_name': 'AeroPy', 132 | 'github_banner': True} 133 | 134 | # Add any paths that contain custom themes here, relative to this directory. 135 | html_theme_path = [alabaster.get_path()] 136 | 137 | # The name for this set of Sphinx documents. If None, it defaults to 138 | # " v documentation". 139 | #html_title = None 140 | 141 | # A shorter title for the navigation bar. Default is the same as html_title. 142 | #html_short_title = None 143 | 144 | # The name of an image file (relative to this directory) to place at the top 145 | # of the sidebar. 146 | html_logo = 'images/logo.png' 147 | 148 | # The name of an image file (within the static path) to use as favicon of the 149 | # docs. This file should be a Windows icon file (.ico) being 16x16 or 32x32 150 | # pixels large. 151 | #html_favicon = None 152 | 153 | # Add any paths that contain custom static files (such as style sheets) here, 154 | # relative to this directory. They are copied after the builtin static files, 155 | # so a file named "default.css" will overwrite the builtin "default.css". 156 | html_static_path = ['_static'] 157 | 158 | # Add any extra paths that contain custom files (such as robots.txt or 159 | # .htaccess) here, relative to this directory. These files are copied 160 | # directly to the root of the documentation. 161 | #html_extra_path = [] 162 | 163 | # If not '', a 'Last updated on:' timestamp is inserted at every page bottom, 164 | # using the given strftime format. 165 | #html_last_updated_fmt = '%b %d, %Y' 166 | 167 | # If true, SmartyPants will be used to convert quotes and dashes to 168 | # typographically correct entities. 169 | #html_use_smartypants = True 170 | 171 | # Custom sidebar templates, maps document names to template names. 172 | #html_sidebars = {} 173 | 174 | # Additional templates that should be rendered to pages, maps page names to 175 | # template names. 176 | #html_additional_pages = {} 177 | 178 | # If false, no module index is generated. 179 | #html_domain_indices = True 180 | 181 | # If false, no index is generated. 182 | #html_use_index = True 183 | 184 | # If true, the index is split into individual pages for each letter. 185 | #html_split_index = False 186 | 187 | # If true, links to the reST sources are added to the pages. 188 | #html_show_sourcelink = True 189 | 190 | # If true, "Created using Sphinx" is shown in the HTML footer. Default is True. 191 | #html_show_sphinx = True 192 | 193 | # If true, "(C) Copyright ..." is shown in the HTML footer. Default is True. 194 | #html_show_copyright = True 195 | 196 | # If true, an OpenSearch description file will be output, and all pages will 197 | # contain a tag referring to it. The value of this option must be the 198 | # base URL from which the finished HTML is served. 199 | #html_use_opensearch = '' 200 | 201 | # This is the file name suffix for HTML files (e.g. ".xhtml"). 202 | #html_file_suffix = None 203 | 204 | # Language to be used for generating the HTML full-text search index. 205 | # Sphinx supports the following languages: 206 | # 'da', 'de', 'en', 'es', 'fi', 'fr', 'hu', 'it', 'ja' 207 | # 'nl', 'no', 'pt', 'ro', 'ru', 'sv', 'tr' 208 | #html_search_language = 'en' 209 | 210 | # A dictionary with options for the search language support, empty by default. 211 | # Now only 'ja' uses this config value 212 | #html_search_options = {'type': 'default'} 213 | 214 | # The name of a javascript file (relative to the configuration directory) that 215 | # implements a search results scorer. If empty, the default will be used. 216 | #html_search_scorer = 'scorer.js' 217 | 218 | # Output file base name for HTML help builder. 219 | htmlhelp_basename = 'AeroPydoc' 220 | 221 | # -- Options for LaTeX output --------------------------------------------- 222 | 223 | latex_elements = { 224 | # The paper size ('letterpaper' or 'a4paper'). 225 | #'papersize': 'letterpaper', 226 | 227 | # The font size ('10pt', '11pt' or '12pt'). 228 | #'pointsize': '10pt', 229 | 230 | # Additional stuff for the LaTeX preamble. 231 | #'preamble': '', 232 | 233 | # Latex figure (float) alignment 234 | #'figure_align': 'htbp', 235 | } 236 | 237 | # Grouping the document tree into LaTeX files. List of tuples 238 | # (source start file, target name, title, 239 | # author, documentclass [howto, manual, or own class]). 240 | latex_documents = [ 241 | (master_doc, 'AeroPy.tex', u'AeroPy Documentation', 242 | u'Pedro Leal', 'manual'), 243 | ] 244 | 245 | # The name of an image file (relative to this directory) to place at the top of 246 | # the title page. 247 | #latex_logo = None 248 | 249 | # For "manual" documents, if this is true, then toplevel headings are parts, 250 | # not chapters. 251 | #latex_use_parts = False 252 | 253 | # If true, show page references after internal links. 254 | #latex_show_pagerefs = False 255 | 256 | # If true, show URL addresses after external links. 257 | #latex_show_urls = False 258 | 259 | # Documents to append as an appendix to all manuals. 260 | #latex_appendices = [] 261 | 262 | # If false, no module index is generated. 263 | #latex_domain_indices = True 264 | 265 | 266 | # -- Options for manual page output --------------------------------------- 267 | 268 | # One entry per manual page. List of tuples 269 | # (source start file, name, description, authors, manual section). 270 | man_pages = [ 271 | (master_doc, 'aeropy', u'AeroPy Documentation', 272 | [author], 1) 273 | ] 274 | 275 | # If true, show URL addresses after external links. 276 | #man_show_urls = False 277 | 278 | 279 | # -- Options for Texinfo output ------------------------------------------- 280 | 281 | # Grouping the document tree into Texinfo files. List of tuples 282 | # (source start file, target name, title, author, 283 | # dir menu entry, description, category) 284 | texinfo_documents = [ 285 | (master_doc, 'AeroPy', u'AeroPy Documentation', 286 | author, 'AeroPy', 'One line description of project.', 287 | 'Miscellaneous'), 288 | ] 289 | 290 | # Documents to append as an appendix to all manuals. 291 | #texinfo_appendices = [] 292 | 293 | # If false, no module index is generated. 294 | #texinfo_domain_indices = True 295 | 296 | # How to display URL addresses: 'footnote', 'no', or 'inline'. 297 | #texinfo_show_urls = 'footnote' 298 | 299 | # If true, do not generate a @detailmenu in the "Top" node's menu. 300 | #texinfo_no_detailmenu = False 301 | 302 | 303 | # Example configuration for intersphinx: refer to the Python standard library. 304 | intersphinx_mapping = {'https://docs.python.org/': None} 305 | 306 | # For importing C dependent Libraries 307 | class m_Mock(Mock): 308 | @classmethod 309 | def __getattr__(cls, name): 310 | return m_Mock() 311 | 312 | MOCK_MODULES = ['numpy'] #'pygtk', 'gtk', 'gobject', 'argparse', 'numpy', 'pandas' 313 | sys.modules.update((mod_name, m_Mock()) for mod_name in MOCK_MODULES) 314 | -------------------------------------------------------------------------------- /AeroPy.py: -------------------------------------------------------------------------------- 1 | # -*- coding: utf-8 -*- 2 | """ 3 | Created on Sun Aug 16 20:59:22 2015 4 | 5 | @author: Pedro 6 | """ 7 | import aero_module as ar 8 | import xfoil_module as xf 9 | import airfoil_module as af 10 | 11 | def find_3D_coefficients(airfoil, alpha, Reynolds=0, iteration=10, NACA=True, 12 | N=10, span=10., taper=1., chord_root=1, alpha_root=1., 13 | velocity=1.): 14 | """ Calculate the 3D distribution using the Lifting Line Theory. 15 | 16 | :param airfoil: if NACA is false, airfoil is the name of the plain 17 | filewhere the airfoil geometry is stored (variable airfoil). 18 | If NACA is True, airfoil is the naca series of the airfoil 19 | (i.e.: naca2244). By default NACA is False. 20 | 21 | :param Reynolds: Reynolds number in case the simulation is for a 22 | viscous flow. In case not informed, the code will assume 23 | inviscid. (Use the aero_module function to calculate reynolds) 24 | 25 | :param alpha: list/array/float/int of angles of attack. 26 | 27 | :param iteration: changes how many times XFOIL will try to make the 28 | results converge. Specialy important for viscous flows 29 | 30 | :param NACA: Boolean variable that defines if the code imports an 31 | airfoil from a file or generates a NACA airfoil. 32 | 33 | :param N: number of cross sections on the wing 34 | 35 | :param span: span in meters 36 | 37 | :param taper: unidimendional taper (This options is still not 100% 38 | operational) 39 | 40 | :param chord_root: value of the chord at the the root 41 | 42 | :param alpha_root: angle of attack of the chord at the root (degrees) 43 | 44 | :param velocity: velocity in m/s 45 | 46 | """ 47 | coefficients = xf.find_coefficients(airfoil, alpha, Reynolds, iteration, 48 | NACA) 49 | alpha_L_0_root = xf.find_alpha_L_0(airfoil, Reynolds, iteration, NACA) 50 | return ar.LLT_calculator(alpha_L_0_root, coefficients['CD'], N, span, taper, chord_root, 51 | alpha_root, velocity) 52 | 53 | def calculate_flap_moment(x, y, alpha, x_hinge, deflection, 54 | unit_deflection = 'rad'): 55 | """For a given airfoil with coordinates x and y at angle of attack 56 | alpha (degrees), calculate the moment coefficient around the joint at x_hinge 57 | and deflection in radians (unit_deflection = 'rad') or degrees 58 | (unit_deflection = 'deg')""" 59 | 60 | # If x and y are not dictionaries with keys upper and lower, make them 61 | # be so 62 | if type(x) == list: 63 | x, y = af.separate_upper_lower(x, y) 64 | #Because parts of the program use keys 'u' and 'l', and other parts use 65 | #'upper' and 'lower' 66 | if 'u' in x.keys(): 67 | upper = {'x': x['u'], 'y': y['u']} 68 | lower = {'x': x['l'], 'y': y['l']} 69 | elif 'upper' in x.keys(): 70 | upper = {'x': x['upper'], 'y': y['upper']} 71 | lower = {'x': x['lower'], 'y': y['lower']} 72 | 73 | hinge = af.find_hinge(x_hinge, upper, lower) 74 | 75 | if deflection > 0: 76 | upper_static, upper_flap = af.find_flap(upper, hinge) 77 | lower_static, lower_flap = af.find_flap(lower, hinge, 78 | extra_points = 'lower') 79 | elif deflection < 0: 80 | upper_static, upper_flap = af.find_flap(upper, hinge, 81 | extra_points = 'upper') 82 | lower_static, lower_flap = af.find_flap(lower, hinge) 83 | else: 84 | upper_static, upper_flap = af.find_flap(upper, hinge, 85 | extra_points = None) 86 | lower_static, lower_flap = af.find_flap(lower, hinge, 87 | extra_points = None) 88 | 89 | upper_rotated, lower_rotated = af.rotate(upper_flap, lower_flap, 90 | hinge, deflection, 91 | unit_theta = unit_deflection) 92 | 93 | flapped_airfoil, i_separator = af.clean(upper_static, upper_rotated, lower_static, 94 | lower_rotated, hinge, deflection, N = None, 95 | return_flap_i = True) 96 | 97 | #~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ 98 | #Third step: get new values of pressure coefficient 99 | xf.create_input(x = flapped_airfoil['x'], y_u = flapped_airfoil['y'], 100 | filename = 'flapped', different_x_upper_lower = True) 101 | 102 | Data = xf.find_pressure_coefficients('flapped', alpha, NACA = False) 103 | 104 | 105 | x, y, Cp = af.separate_upper_lower(x = Data['x'], y = Data['y'], 106 | Cp = Data['Cp'], i_separator = i_separator) 107 | 108 | #At the hinges, the reaction moment has the opposite sign of the 109 | #actuated torque 110 | Cm = - ar.calculate_moment_coefficient(x, y, Cp, alpha = alpha, c = 1., 111 | x_ref = x_hinge, y_ref = 0., 112 | flap = True) 113 | return Cm 114 | 115 | def calculate_flap_coefficients(x, y, alpha, x_hinge, deflection, Reynolds = 0,): 116 | """For a given airfoil with coordinates x and y at angle of attack 117 | alpha, calculate the moment coefficient around the joint at x_hinge 118 | and deflection """ 119 | 120 | def separate_upper_lower(x, y, Cp = None, i_separator=None): 121 | """Return dictionaries with upper and lower keys with respective 122 | coordiantes. It is assumed the leading edge is frontmost point at 123 | alpha=0""" 124 | #TODO: when using list generated by xfoil, there are two points for 125 | #the leading edge 126 | def separate(variable_list, i_separator): 127 | if type(i_separator) == int: 128 | variable_dictionary = {'upper': variable_list[0:i_separator+1], 129 | 'lower': variable_list[i_separator+1:]} 130 | elif type(i_separator) == list: 131 | i_upper = i_separator[0] 132 | i_lower = i_separator[1] 133 | 134 | variable_dictionary = {'upper': variable_list[0:i_upper], 135 | 'lower': variable_list[i_lower:]} 136 | return variable_dictionary 137 | #If i is not defined, separate upper and lower surface from the 138 | # leading edge 139 | if i_separator == None: 140 | i_separator = x.index(min(x)) 141 | 142 | if Cp == None: 143 | x = separate(x, i_separator) 144 | y = separate(y, i_separator) 145 | return x, y 146 | else: 147 | x = separate(x, i_separator) 148 | y = separate(y, i_separator) 149 | Cp = separate(Cp, i_separator) 150 | return x, y, Cp 151 | # If x and y are not dictionaries with keys upper and lower, make them 152 | # be so 153 | if type(x) == list: 154 | x, y = separate_upper_lower(x, y) 155 | 156 | upper = {'x': x['upper'], 'y': y['upper']} 157 | lower = {'x': x['lower'], 'y': y['lower']} 158 | 159 | #Determining hinge 160 | hinge = af.find_hinge(x_hinge, upper, lower) 161 | 162 | upper_static, upper_flap = af.find_flap(upper, hinge) 163 | lower_static, lower_flap = af.find_flap(lower, hinge, lower = True) 164 | 165 | upper_rotated, lower_rotated = af.rotate(upper_flap, lower_flap, hinge, deflection) 166 | 167 | flapped_airfoil, i_separator = af.clean(upper_static, upper_rotated, lower_static, 168 | lower_rotated, hinge, deflection, N = 5, 169 | return_flap_i = True) 170 | 171 | #~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~~ 172 | #Third step: get new values of pressure coefficient 173 | xf.create_input(x = flapped_airfoil['x'], y_u = flapped_airfoil['y'], 174 | filename = 'flapped', different_x_upper_lower = True) 175 | Data = xf.find_coefficients('flapped', alpha, NACA = False, 176 | Reynolds = Reynolds, iteration=500) 177 | 178 | return Data 179 | 180 | 181 | if __name__ == '__main__': 182 | 183 | import numpy as np 184 | import matplotlib.pyplot as plt 185 | import math 186 | 187 | # print find_3D_coefficients(airfoil='naca0012', alpha=1.) 188 | alpha = 0. 189 | x_hinge = 0.25/0.6175 190 | deflection = -math.pi/2. #0.17453292519943295 #0.0010573527055 191 | 192 | # generate original airfoil 193 | airfoil = "naca0012" 194 | xf.call(airfoil, output='Coordinates') 195 | filename = xf.file_name(airfoil, output='Coordinates') 196 | Data = xf.output_reader(filename, output='Coordinates', header = ['x','y']) 197 | 198 | Cm = calculate_flap_moment(Data['x'], Data['y'], alpha, x_hinge, deflection) 199 | 200 | 201 | V = 10 202 | altitude = 10000 #feet 203 | 204 | Reynolds = ar.Reynolds(altitude, V, 1.0) 205 | 206 | deflection_list = list(np.linspace(5,30,4)) 207 | alpha_list = list(np.linspace(0,15,20)) 208 | 209 | # Calculate coefficients for without flap 210 | CL_list = [] 211 | CD_list = [] 212 | ratio_list = [] 213 | CM_list = [] 214 | 215 | for alpha_i in alpha_list: 216 | Data_0 = xf.find_coefficients('naca0012', alpha_i, Reynolds = Reynolds, 217 | iteration = 200) 218 | CL_list.append(Data_0['CL']) 219 | CD_list.append(Data_0['CD']) 220 | ratio_list.append(Data_0['CL']/Data_0['CD']) 221 | CM_list.append(Data_0['CM']) 222 | All_data = {0:{r'$c_m$': CM_list, r'$c_l$':CL_list, 223 | r'$c_d$': CD_list, 224 | r'$c_l/c_d$': ratio_list}}#:Data_0['CL']/Data_0['CD']}} 225 | 226 | # Calculate foeccifient when using flap 227 | for deflection_i in deflection_list: 228 | CL_list = [] 229 | CD_list = [] 230 | ratio_list = [] 231 | CM_list = [] 232 | for alpha_i in alpha_list: 233 | flap_data = calculate_flap_coefficients(Data['x'], Data['y'], alpha_i, x_hinge, 234 | deflection_i, Reynolds = Reynolds) 235 | CL_list.append(flap_data['CL']) 236 | CD_list.append(flap_data['CD']) 237 | ratio_list.append(flap_data['CL']/flap_data['CD']) 238 | CM_list.append(flap_data['CM']) 239 | All_data[deflection_i] = {r'$c_m$' : CM_list, r'$c_l$': CL_list, 240 | r'$c_d$' : CD_list, r'$c_l/c_d$': ratio_list} 241 | for key in [r'$c_m$', r'$c_l$', r'$c_d$', r'$c_l/c_d$']: 242 | plt.figure() 243 | for deflection_i in [0] + deflection_list: 244 | plt.plot(alpha_list, All_data[deflection_i][key], label = r'$\theta$ = %.0f' % deflection_i) 245 | plt.legend(loc = "best") 246 | plt.xlabel(r'$\alpha$', fontsize = 22) 247 | plt.ylabel(key, fontsize = 22) 248 | plt.grid() 249 | 250 | plt.figure() 251 | for deflection_i in [0] + deflection_list: 252 | plt.plot(All_data[deflection_i][r'$c_d$'], 253 | All_data[deflection_i][r'$c_l$'], 254 | label = r'$\theta$ = %.0f' % deflection_i) 255 | plt.legend(loc = "best") 256 | plt.xlabel(r'$c_d$', fontsize = 22) 257 | plt.ylabel(r'$c_l$', fontsize = 22) 258 | plt.grid() 259 | 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21 | 22 | body { 23 | font-family: 'goudy old style', 'minion pro', 'bell mt', Georgia, 'Hiragino Mincho Pro', serif; 24 | font-size: 17px; 25 | background-color: white; 26 | color: #000; 27 | margin: 0; 28 | padding: 0; 29 | } 30 | 31 | div.document { 32 | width: 940px; 33 | margin: 30px auto 0 auto; 34 | } 35 | 36 | div.documentwrapper { 37 | float: left; 38 | width: 100%; 39 | } 40 | 41 | div.bodywrapper { 42 | margin: 0 0 0 220px; 43 | } 44 | 45 | div.sphinxsidebar { 46 | width: 220px; 47 | } 48 | 49 | hr { 50 | border: 1px solid #B1B4B6; 51 | } 52 | 53 | div.body { 54 | background-color: #ffffff; 55 | color: #3E4349; 56 | padding: 0 30px 0 30px; 57 | } 58 | 59 | div.footer { 60 | width: 940px; 61 | margin: 20px auto 30px auto; 62 | font-size: 14px; 63 | color: #888; 64 | text-align: right; 65 | } 66 | 67 | div.footer a { 68 | color: #888; 69 | } 70 | 71 | 72 | div.relations { 73 | display: none; 74 | } 75 | 76 | 77 | div.sphinxsidebar a { 78 | color: #444; 79 | text-decoration: 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margin-left: 0; 176 | width: 50%; 177 | } 178 | 179 | /* -- body styles ----------------------------------------------------------- */ 180 | 181 | a { 182 | color: #004B6B; 183 | text-decoration: underline; 184 | } 185 | 186 | a:hover { 187 | color: #6D4100; 188 | text-decoration: underline; 189 | } 190 | 191 | div.body h1, 192 | div.body h2, 193 | div.body h3, 194 | div.body h4, 195 | div.body h5, 196 | div.body h6 { 197 | font-family: 'Garamond', 'Georgia', serif; 198 | font-weight: normal; 199 | margin: 30px 0px 10px 0px; 200 | padding: 0; 201 | } 202 | 203 | div.body h1 { margin-top: 0; padding-top: 0; font-size: 240%; } 204 | div.body h2 { font-size: 180%; } 205 | div.body h3 { font-size: 150%; } 206 | div.body h4 { font-size: 130%; } 207 | div.body h5 { font-size: 100%; } 208 | div.body h6 { font-size: 100%; } 209 | 210 | a.headerlink { 211 | color: #DDD; 212 | padding: 0 4px; 213 | text-decoration: none; 214 | } 215 | 216 | a.headerlink:hover { 217 | color: #444; 218 | 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text-decoration: none; 420 | font-size: 0.7em; 421 | vertical-align: top; 422 | border-bottom: 1px dotted #004B6B; 423 | } 424 | 425 | a.footnote-reference:hover { 426 | border-bottom: 1px solid #6D4100; 427 | } 428 | 429 | a:hover tt, a:hover code { 430 | background: #EEE; 431 | } 432 | 433 | 434 | @media screen and (max-width: 870px) { 435 | 436 | div.sphinxsidebar { 437 | display: none; 438 | } 439 | 440 | div.document { 441 | width: 100%; 442 | 443 | } 444 | 445 | div.documentwrapper { 446 | margin-left: 0; 447 | margin-top: 0; 448 | margin-right: 0; 449 | margin-bottom: 0; 450 | } 451 | 452 | div.bodywrapper { 453 | margin-top: 0; 454 | margin-right: 0; 455 | margin-bottom: 0; 456 | margin-left: 0; 457 | } 458 | 459 | ul { 460 | margin-left: 0; 461 | } 462 | 463 | .document { 464 | width: auto; 465 | } 466 | 467 | .footer { 468 | width: auto; 469 | } 470 | 471 | .bodywrapper { 472 | margin: 0; 473 | } 474 | 475 | .footer { 476 | width: auto; 477 | } 478 | 479 | .github { 480 | display: none; 481 | } 482 | 483 | 484 | 485 | } 486 | 487 | 488 | 489 | @media screen and (max-width: 875px) { 490 | 491 | body { 492 | margin: 0; 493 | padding: 20px 30px; 494 | } 495 | 496 | div.documentwrapper { 497 | float: none; 498 | background: white; 499 | } 500 | 501 | div.sphinxsidebar { 502 | display: block; 503 | float: none; 504 | width: 102.5%; 505 | margin: 50px -30px -20px -30px; 506 | padding: 10px 20px; 507 | background: #333; 508 | color: #FFF; 509 | } 510 | 511 | div.sphinxsidebar h3, div.sphinxsidebar h4, div.sphinxsidebar p, 512 | div.sphinxsidebar h3 a { 513 | color: white; 514 | } 515 | 516 | div.sphinxsidebar a { 517 | color: #AAA; 518 | } 519 | 520 | div.sphinxsidebar p.logo { 521 | display: none; 522 | } 523 | 524 | div.document { 525 | width: 100%; 526 | margin: 0; 527 | } 528 | 529 | div.footer { 530 | display: none; 531 | } 532 | 533 | div.bodywrapper { 534 | margin: 0; 535 | } 536 | 537 | div.body { 538 | min-height: 0; 539 | padding: 0; 540 | } 541 | 542 | .rtd_doc_footer { 543 | display: none; 544 | } 545 | 546 | .document { 547 | width: auto; 548 | } 549 | 550 | .footer { 551 | width: auto; 552 | } 553 | 554 | .footer { 555 | width: auto; 556 | } 557 | 558 | .github { 559 | display: none; 560 | } 561 | } 562 | 563 | 564 | /* misc. */ 565 | 566 | .revsys-inline { 567 | display: none!important; 568 | } 569 | 570 | /* Make nested-list/multi-paragraph items look better in Releases changelog 571 | * pages. Without this, docutils' magical list fuckery causes inconsistent 572 | * formatting between different release sub-lists. 573 | */ 574 | div#changelog > div.section > ul > li > p:only-child { 575 | margin-bottom: 0; 576 | } 577 | 578 | /* Hide fugly table cell borders in ..bibliography:: directive output */ 579 | table.docutils.citation, table.docutils.citation td, table.docutils.citation th { 580 | border: none; 581 | /* Below needed in some edge cases; if not applied, bottom shadows appear */ 582 | -moz-box-shadow: none; 583 | -webkit-box-shadow: none; 584 | box-shadow: none; 585 | } --------------------------------------------------------------------------------