An investigation of design optimization using a 2D viscous flow code with multigrid
Abstract
Computational fluid dynamics (CFD) codes have advanced to the point where they are effective analytical tools for solving flow fields around complex geometries. There is also a need for their use as a design tool to find optimum aerodynamic shapes. In the area of design, however, a difficulty arises due to the large amount of computer resources required by these codes. It is desired to streamline the design process so that a large number of design options and constraints can be investigated without overloading the system. There are several techniques which have been proposed to help streamline the design process. The feasibility of one of these techniques is investigated. The technique under consideration is the interaction of the geometry change with the flow calculation. The problem of finding the value of camber which maximizes the ratio of lift over drag for a particular airfoil is considered. In order to test out this technique, a particular optimization problem was tried. A NACA 0012 airfoil was considered at free stream Mach number of 0.5 with a zero angle of attack. Camber was added to the mean line of the airfoil. The goal was to find the value of camber for which the ratio of lift over drag is a maximum. The flow code used was FLOMGE which is a two dimensional viscous flow solver which uses multigrid to speed up convergence. A hyperbolic grid generation program was used to construct the grid for each value of camber.
 Publication:

In Hampton Univ
 Pub Date:
 September 1990
 Bibcode:
 1990asee.nasa...46D
 Keywords:

 Airfoils;
 Computational Fluid Dynamics;
 Convergence;
 Design Analysis;
 Flow Distribution;
 Grid Generation (Mathematics);
 Multigrid Methods;
 Optimization;
 Two Dimensional Flow;
 Camber;
 Drag;
 Free Flow;
 Shapes;
 Subsonic Speed;
 Viscous Flow;
 Zero Angle Of Attack;
 Fluid Mechanics and Heat Transfer