Current Research 2.1.2006

Since efforts to refine the volume grid around the NACA 0012 wing section have come up short, the decision has been made to go in a slightly differnt direction. Instead of refining in the area of the vortex or the controling the spacing in the boundary layer, refinement will now take place on the suface mesh of the wing. 12 control points have been selected on the wingtip. The spacing at each individual control point will be varied in order to achieve refinement. The control points can be seen below.

Figure 1 Wingtip Control Points

Initially, a spacing of 0.02 will be given to each point and then each point will be perturbed by 0.00001. This makes 13 simulations with on simulation being totally unperturbed. Then, using the steepest descent method outlined in the previous research update, a new set of spacings will be chosen for a new set of iterations. Eventually, a table will be able to be constructed showing each iteration until convergence. The table constructed may be similar to this one below.

Figure 2 Sample Iteration Table

where

and

In addition to this task, an accurate equation/value for the theoretical value of the tangential velocity is needed and is being researched.

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Last modified: Wed Feb 1 14:15:29 CST 2006