The AIAA Aerodynamic Design Optimization Discussion Group (ADODG) was formed to address the need for aerodynamic design optimization benchmarks that could be used to compare methods between different researchers. There are 6 benchmark cases.
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. The geometry and grid files are available on Mendeley Data.
Flow conditions:
Reynolds Number: 5.0 million
Mach number: 0.85
This problem considers the full CRM wing-body-tail configuration instead of the wing alone. See the ADODG problem definition file at the bottom of this page for more details and this paper for results.
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. Z. Lyu, Kenway, G. K. W., and Martins, J. R. R. A., “Aerodynamic Shape Optimization Investigations of the Common Research Model Wing Benchmark”, AIAA Journal, vol. 53, no. 4, p. 968–985, 2015.
| Attachment | Size |
|---|---|
| ADODG6_Problem_Definition.pdf | 213.13 KB |