CODAS is a powerful CFD-based aerodynamic optimisation tool that improves designs and increases design productivity. The tool consists of the following modules:
The designer specifies the number and position of optimisation variables controlling geometric surface design to the code. The optimisation proceeds through iterative changes to the geometry and flow conditions that, for example, optimise a defined cost function (e.g. drag) while satisfying geometric and aerodynamic side constraints (e.g. fuel volume, cruise lift coefficient). When used in combination with NEWPAN, the complete iterative design process for performance optimisation, geometry shaping and CFD analysis may be automated.
Geometry can be optimised for single or multiple flow conditions, including variable geometry. Target pressure distributions can be specified for inverse design, or as a constraint during optimisation of other performance drivers.
Recent applications of NEWPAN-CODAS have included "Aerodynamic Design Optimisation applied to a Formula One Car", presented at the 4th MIRA International Vehicle Aerodynamics Conference, 16-17 October 2002.
The aim of the design exercise was to maximise the downforce coefficient (-CL) from the complete rear wing geometry, subject to the geometric constraints imposed by the current FIA Formula One Technical Regulations. These rules limit the span of the wing assembly, and specify a rectangular box in cross-section within which a maximum of three upper wing elements must lie. The optimisation constraints and variables may be summarised as follows:
Objective Function: Minimise downforce coefficient (-CL)
Geometry constraints:
Each of three upper wing elements constrained to lie within a box of these dimensions in millimetres:
3150 < X < 3500
-500 < Y < 500
600 < Z < 800
The lower wing element was fixed in position and shape.
Aerodynamic constraints:
Specified in this study as maximum permissible boundary layer separations:
Vane element: up to 3% forward of the trailing edge
Main element: up to 3% forward of the trailing edge
Flap element: up to 10% forward of the trailing edge
The boundary layer properties were predicted using PANBL.
Design variables:
For each of the three upper wing elements:
2 camber variables
1 twist variable (applied at the centreline through the quarter chord)
2 rigid body translation variables (X and Z directions)
1 rigid body rotation variable (about Y-axis through quarter chord)
Hence a total of 18 design variables.
CODAS was run for a total of 12 gradient-search cycles, requiring a total of 286 NEWPAN/PANBL calculations. This required 12 hours CPU time on an SGI Origin R1000 195MHz machine, i.e. such an optimisation may be performed comfortably overnight on a desktop workstation. Results demonstrated an increase in downforce whilst avoiding an increase in viscous drag.
Such a study demonstrates the viability of performing complex design optimisations using NEWPAN.