caeroc's Introduction

caeroc

Compressible Aerodynamics Calculator for Python

A python package for compressible flows. A dynamic toolkit which enables you to make use of the formulae governing compressible flows.

Requirements

Python 2.7, >=3.4
pylab (numpy, scipy and matplotlib)
ashwinvis/scikit-aero >= 0.2
PyQt5 / PySide (optional, but recommended for GUI)
pandas (optional: for making tables)
colorlog (optional: for coloured log)

Installation

To install from PyPI:

pip install -e git+https://github.com/AeroPython/scikit-aero.git#egg=scikit-aero

# Any of the following
pip install caeroc
pip install caeroc[pyqt]
pip install caeroc[pyside]

To install development versions of caeroc and scikit-aero

pip install pipenv
pipenv install -e git+https://github.com/ashwinvis/caeroc.git#egg=caeroc

If the current configuration of the GUI does not work for you, regenerate it by running:

cd caeroc/gui
./configure

Launch

Simply run in your terminal

caeroc-app

Features

[x] Command-line tool which opens a Qt based GUI calculator

In development
[ ] Save data as a database
[ ] Plotting graphs
[ ] Generate gas tables
[ ] Calculate flow characteristics: Coefficient of pressure, lift and drag for basic profiles.

Courtesy

The idea for a compressible aerodynamics calculator in the form an online JS tool had been implemented by William Devenport here. This project is pushing more functionalities as an offline tool and allowing users to dynamically use the formulae for specific cases.
Thanks to the scikit-aero team for being the backend

caeroc's People

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caeroc's Issues

Implement simple 1-D solvers for basic geometries

See caeroc/profiles module

Normal shock mode : better error handling required when illegal values are entered

Should not get core dumped. Will have to be dealt in scikit-aero/skaero/gasdynamics/isentropic.py or in caeroc.

DEBUG:caeroc-app:MODE: Normal shock relations
INFO:caeroc-app:{'M_1': 0.9}
CRITICAL:caeroc-app:Mach number must be supersonic
Traceback (most recent call last):
  File "/scratch/avmo/opt/caeroc-r8bspf19/src/scikit-aero/skaero/gasdynamics/isentropic.py", line 54, in mach_angle
    mu = np.arcsin(1 / M)
FloatingPointError: invalid value encountered in arcsin

During handling of the above exception, another exception occurred:

Traceback (most recent call last):
  File "/home/avmo/src/caeroc/caeroc/gui/runtime.py", line 214, in on_qpb_calculate_released
    self.mode.calculate(**kwargs)
  File "/home/avmo/src/caeroc/caeroc/formulae/shock.py", line 89, in calculate
    self.store(key, getattr(self, key))
  File "/scratch/avmo/opt/caeroc-r8bspf19/src/scikit-aero/skaero/gasdynamics/shocks.py", line 219, in M_2
    M_2 = self.M_2n / np.sin(self.beta - self.theta)
  File "/scratch/avmo/opt/caeroc-r8bspf19/src/scikit-aero/skaero/gasdynamics/shocks.py", line 194, in theta
    if self.beta == mach_angle(self.M_1) or self.beta == np.pi / 2:
  File "/scratch/avmo/opt/caeroc-r8bspf19/src/scikit-aero/skaero/gasdynamics/isentropic.py", line 56, in mach_angle
    raise ValueError("Mach number must be supersonic")
ValueError: Mach number must be supersonic
[1]    11343 abort (core dumped)  caeroc-app