Department of Aeronautics and Fluid Mechanics, University of Glasgow
Abstract
A vortex panel method has been developed to calculate the potential
flow about an arbitrary two dimensional aerofoil or axisymmetric shape
at fixed incidence in a steady, uniform, irrotational, incompressible
flow.
The procedure replaces the contour by a suitably inscribed polygon,
on which surface vorticity varies linearly and continuously along the
panel and is piecewise continuous at the panel corners.
The Neumann boundary condition is satisfied at control points
situated at the midpoint of each panel and the classical Kutta
condition is specified at the trailing edge by setting the net
vorticity there equal to zero.
This particular algorithm offers much flexibility in the treatment
of a greater range of aerofoil geometries and at higher incidence than
other surface singularity methods.
Programme flow charts and FORTRAN code listings are given in the
User Guide (1)
