Calculates and plots pressure distribution across an diamond shaped airfoil at specified free stream pressure and mach, wedge angle, and angle of attack. Furthermore, it saves the property changes in a .csv-file.
Example output:
- Python 3.
With
- Anaconda (for Python 3.6)
Or
- numpy
- matplotlib
- seaborn
- scipy
In order for the program to run, aerodynamics.py and diamond_airfoil.py have to be in the same folder. The easiest way to do that is to clone the repositiory.
The only script that needs to be called is diamond_airfoil.py.
$ python3 diamond_airfoil.py 3 5 -aoa 6 -ipres 1.5
It's command line input arguments are:
- Mach number of the incoming flow.
- Half-wedge angle of the incoming flow in degrees.
- (Optional) Angle of attach of flow to airfoil in degrees. The default is 0 degrees.
- (Optional) The freestream pressure of the incoming flow in atm. The default is 1 atm.
For additional documentation use -h.