This program implements an openMdao component, that optimizes an airfoil for minimum drag while making sure a defined rectangle is still fitting inside it. This rectangle represents the cabin tube of a blended wing body (BwB).

• python:
  • the tested versions are 2.7 and 3.5
  • beside some standard packages openMdao is needed
    • http://openmdao.org/
• su2:
  • https://su2code.github.io/download.html
  • the version used here is: 6.0.0 "Falcon"
• construct2d(recommended):
  • https://sourceforge.net/projects/construct2d/
  • the version used here is: 2.1.4
• or gmsh:
  • http://gmsh.info/
  • the version used here is: 3.7.5

Set the paths to your binaries in config.py. Note, this program is designed for Windows!

use your favourite python editor and open this repo as a new project.

• main.py: the main optimization program
• cfdTestRun.py: simple test script that runs one cfd job with a given input airfoil coordinate file
• airofilAnalysisMach.py: runs analysis on one airfoil, generates drag over mach for one liftcoefficient
• airofilAnalysisPolar.py: runs analysis on one airfoil, generates polar for one mach nr
• cfdConvergenceTest.py: does convergence analysis with different mesh sizes