The ADODG was formed to establish a set of benchmark aerodynamic design optimization problems that could be used to compare methods between different researchers. At the time of this writing, there are 6 benchmark problems. This page contains data related to some of the problems that have been investigated by the MDO Lab.

The objective of this problem is to minimize the drag of a NACA 0012 airfoil in transonic, inviscid flow.

The objective of this problem is to minimize the drag of an RAE 2822 airfoil in transonic, turbulent flow.

The objective of this problem is to minimize the drag of a rectangular wing with NACA 0012 cross-sections in subsonic, inviscid flow.

This page contains the optimized geometry and grid file of the Common Research Model (CRM) wing optimization case for AIAA Aerodynamic Design Optimization Discussion Group (ADODG). Please see the paper 1 for more information.

For a summary of aerodynamic shape optimization in the MDO Lab, see this page.

Baseline 28M grid in block-structured CGNS format:

http://mdolab.engin.umich.edu/sites/default/files/Lyu-etal-CRM-baseline-28M.cgns

Baseline 3M grid in block-structured CGNS format:

http://mdolab.engin.umich.edu/sites/default/files/Lyu-etal-CRM-baseline-3M.cgns

Optimized geometry extracted from the 28.8M grid in PLOT3D format:

http://mdolab.engin.umich.edu/sites/default/files/Lyu-etal-CRM-wing-optimized-geometry.xyz

Optimized 28M grid in block-structured CGNS format:

http://mdolab.engin.umich.edu/sites/default/files/Lyu-etal-CRM-optimized-28M.cgns

Optimized 3M grid in block-structured CGNS format:

http://mdolab.engin.umich.edu/sites/default/files/Lyu-etal-CRM-optimized-3M.cgns

**Flow conditions:**

Reynolds Number: 5.0 million

Mach number: 0.85

Movies of the optimization history

This problem takes the wing from Problem 3 and increases the number of design variables to allow a very large degree of flexibility in the parametrization. The problem description is available in the attachments at the bottom of this page.

- 1. . Aerodynamic Shape Optimization Investigations of the Common Research Model Wing Benchmark. AIAA Journal. 2015 ;53(4):968--985.