You are here

Aerodynamic Design Optimization Discussion Group (ADODG)

Introduction

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.

Problem 1: Inviscid drag minimization of a symmetric airfoil

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

Problem 2: Viscous drag minimization of an RAE 2822 airfoil

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

Problem 3: Subsonic, inviscid drag minimization of simple wing

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

Problem 4: Drag minimization of CRM wing

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

Problem 5: (Needs description)

 

Problem 6: Multimodality study of simple wing

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.

AttachmentSize
PDF icon ADODG6_Problem_Definition.pdf213.13 KB