Panel Methods -- AIC Matrix
The next step, after dividing the geometry into panels is to compute the
flow pattern at each panel, i, associated with a source or doublet or vortex
of unit strength at panel j. The component of the velocity normal to the
panel is denoted AIC(i,j), an element of the aerodynamic influence coefficient
matrix.
The flow at panel i associated with a singularity of unit strength at panel
j can be computed from the basic singularity solution. The result depends
on the vector distance between the panels, R. More specifically, the vector
from the jth singularity to the control point of panel i (often at the panel
centroid).
The fundamental solution for the flow field some distance from the singularity
is discussed in following sections, but the jth panel usually contains not
just a single point source or vortex or doublet, but several vortex lines
or a distribution of such singularities. The form of this distribution is
one of the things that differentiates various panel methods.
The distribution of singularity strength over a panel may be a constant
value, or may vary linearly or quadratically in both directions. The list
below shows some of the panel codes and the choice of singularity types
and distributions.
