mesnardo / automan-example

Toy problem using automan framework

aeropython example using automan framework

The present repository was created as part of the review of manuscript CiSESI-2018-02-0013 for Computing in Science and Engineering.

It contains an toy example using the automan framework. automan is a Python-based framework to help researchers automate their computational workflows. Here, we use a small in-house Python package, aeropython, to compare the surface pressure coefficients from multiple NACA airfoils at various angles of attack. aeropython implements a simple two-dimensional panel method, using source and vortex sheets, to solve steady, inviscid, and irrotational flow.

Files of interest:

• panelmethod.py: script to solve the panel method, compute and write the surface pressure coefficient for an airfoil.
• automan_example.py: automan framework to compute a series of problems and to generate figures.
• Dockerfile: set of instructions used to build the Docker image mesnardo/aeropython:0.1.1-lite, publicly available on DockerHub.

The Docker image capturing the working environment was built and pushed to DockerHub:

docker build --tag aeropython:0.1.1-lite .
docker tag aeropython:0.1.1-lite mesnardo/aeropython:0.1.1-lite
docker push mesnardo/aeropython:0.1.1-lite

Run the example

Pull the DockerHub image and run a container:

docker pull mesnardo/aeropython:0.1.1-lite
docker run -it --name automan_example mesnardo/aeropython:0.1.1-lite /bin/bash

Once inside the container, clone the present repository and change directory to it:

cd
git clone https://github.com/mesnardo/automan-example.git
cd automan-example

To run the simulations and create the figures using automan:

python automan_example.py

The simulation data are stored in the folder data. The figures are in the folder manuscript/figures.

Here are the two figures generated by the present example:

Figure 1: Surface pressure coefficient for different NACA airfoils immersed in a freestream with a zero-degree angle of incidence. (Solid line for the upper surface of the airfoil; dash line for the lower surface.)

Figure 2: Surface pressure coefficient on the NACA0012 airfoil with different angles of incidence for the freestream flow. (Solid line for the upper surface; dash line for the lower surface.)